Transcript for:
Red Eagle Finals Presentation - Note Summary

so I'd like to welcome you all to the finals of the Red Eagle competition there are originally 15 teams we down selected to 5 finalists who are here today to present their designs for a Lander that can deliver 10 ton payload to the Martian surface okay the assumption is you've already been delivered on trans-mars injection and you're approaching Mars and now you have to get 10 tonnes to the Martian surface we have five teams are the red movies with France here over there okay is Argo Nova from Germany and Sweden here over there okay is good Yahoo from India and Italy here okay it's Icarus from the United States here over there and project Eagle from Poland okay so all five teams are here so each team is gonna have a total of 40 minutes but you should try to wrap it up in 30 so there's ten for questions and in any case no more than 35 so at least five minutes for questions which will be from the judges now we actually have quite an eminent panel of judges we have Paul Worcester who is one of the principal engineers at SpaceX is here Tony Muscatello spent many years at NASA Kennedy Space Center Tara I forget your last name what holes Paul Paul's bro okay she's from Marshall Space Flight Center we have Hobby Price who's from Jet Propulsion lab and we have max thank you yes and I believe he's with mating space at the moment mckay which is a private space entrepreneurial company not one of these corporate giants like SpaceX but B okay so and then you're gonna be judged 20 points for cost 20 points for overall technical the design 20 points for minimizing total mass 20 points for operational simplicity 20 points for schedule didn't we give you a date that we wanted this thing to be available by what was it by 2026 so we cannot use levitation and stuff like that to land you got it okay something that that would be available by the middle of the next decade in terms of instruction the judges the teams may say what their cost is but it is up to you to decide what you think the development cost of the technology is likely to be okay they may make their suggestion but you know you can decide what you think is realistic and which cost less than each other okay because some teams might give a more optimistic estimate and it's your estimate that counts so the order is going to be first we're going to have the red movers from France then the Argo Nova from Germany and Sweden then girl Yahoo aho whatever how do you pronounce it Kershaw from India and Italy Ikaros from the United States and project Eagleton Poland so without further ado let's have the French team [Applause] okay hello everybody and thanks for having us so we are movers we're the team from France and this is gonna be our take on trying to land ten tons on Mars so only three working on this project so to take a little moment just to talk about who we are we are three aerospace engineering students that come from the same school that it's called EPSA which is in Paris and we're really interested and we try to be involved as much as possible in in space so here are just an example of some of the things we've done a little pod has won a European contest of making a balloon on Mars and I myself has worked as a scientific host explaining rocket science to the general public and well we took apart into this contest because we really won't be a part of the exploration of Mars we were too young when there were the Apollo missions and we were kids when the Space Shuttle was retired we really want to see the next big thing which is sending humans to Mars we really want to be a part of that and so we'd like to take a moment just to thank the Mars Society for having this contest and allowing us to come come here launched by 2026 we have to make it as cheap as possible possibly insane humans and we have to make the mass lower as possible so we will present her project in frost step first we start by the technical aspect on what the what is the choice what we did do to arrive at with a wizard and second time we speak about this query and at the same time the budget and before to conclude we speak we give some information with the limitation of a project due to the but we are just free students so to start off the aim is to the land tenten's on mars so the choice that we take took sorry it was to take the Space Launch System to be able to put those 10 tonnes so from the information we have an SLS launch would be half a billion about and so to put 10 tons of payload we're gonna need to send much more than that with the mass of the lander the issue is to be able to land 10 tonnes we're gonna need the SLS block to and from what we saw it's only available in 2029 for the first launch and we want to go there for 2026 so the idea we had is actually to make another Lander the same one but a smaller version that's gonna be able to launch to land six tons on Mars for a fraction of the cost the launch cost is 150 million and so we're gonna develop two Landers one heavy for 10 tonne so that we're in the rules of the contest and it's smaller it's gonna be able to learn to land sorry 6 tonnes on the surface of Mars so you can see a to view of each Tundras on the left path zealanders for Falcon even on the white for SLS it's the same design in the same architecture the only difference is the size and by comparison with the over spacecraft cargo we find that for 6 ton of payload we need 45 cubic metre for the payload of 610 and for the paid out of 10 ton we should need 80 a cubic meter for the position we chose to put the payload in the center of the lander to have the door closes possible of the guan 212 an easy access to the mass mass 1 so we're just gonna take a moment to take a look at our lander how it how it is so this is one we're starting starting EDL as you can see we have an inflatable heat shield it's a hypersonic so high ad there are lots of benefits to this we have a higher surface area so it creates more drag and it's inflatable so that it actually fits in the fairing on the sides you can see some solar panels that are going to provide all the electrical needs during the six-month flight there we we would we were thinking of jettison them just before landing so that's we don't have that much weight well that's less weight to reduce the landing legs well we took a little bit from what SpaceX does you saw the picture just before on when they were deployed and you can see some RCS packs those are just for attitude control what's interesting about those is that you have to at the bottom yeah I'm sorry for at the bottom and for at top and those at the top are inclined in 45 degrees so that when the heat shield is deployed the ejection the gas ejector doesn't hit the heat shield so we still remain we still have attitude control once the heat shield is deployed which we're gonna need further on that will explain a bit later today now under we had to take account the center of gravity with the best mass distribution as possible so we should to put the propellants on the top of our lambda we know it's not that easier why for development but it's better for the center of gravity we not we have not to to put the center of gravity Laurette and up to three meters on the falcone be so to the lunch the lander is upside down so the the center of gravity is lower the three metals and then after lunch the the first part of the propellant is for the burning burning captured burn sorry and the second part is for the landing burn and then when the lander lands on Mars the propellant is empty cells they are just below the pilot so the center of gravity is lower as possible so what are the benefits of such choice why why did we take one lander and make two versions out of it when we just were asked to make one well the first one is we still respect the rules of the contest obviously we're still able to land 10 tons but we thought it's actually cheaper to do it this it's a bit more technical because instead of having one version we're gonna have two one for Tenten and one for six tons but it's cheaper as we're gonna see later for the same cost as we estimated it we can do one launched with SLS land ten tonnes with SLS or to launch two launches sorry with Falcon Heavy and since one of the ideas to having such a heavy Lander was sending lots of Rovers to Mars in the first time to be able to explore Mars and giving ability for people for example see Mars in VR for the same cost either we can send ten tons at one point or twelve at one point or even six and six are two different points so we can have Rovers on different parts of Mars for the exact same cost so this gives us more flexibility and this is why we did it like that to design her Lander we use Freeman software the first cub our space program it's initially a game but we had some extension developed by aerospace engineer who give a really good estimation of the trajectory for the mass approach on especially the L working phases in the second time for the mass atmosphere country we use iOS it's a software developed by French engineer especially for the mass society which specialized in the atmosphere on three on Mars so first to vist to software cab a space program on ours we can simulate all the phases of a flight and at the end we use insist free and with the CFD software to find the parameter of parent of our design so this drug coefficient on lift coefficient our name it's our SLS lambda you can initially send 40 turns on Mars and at the length you can put 10 ton payload on visit perhaps you can see the situation during the atmosphere aren't we so on the Left graph it's the altitude in function of the time on the white dwarf is the situation if instead of the time so you can see at eight kilometer we stop the deceleration when we drop the shield and so the lander start to accelerate and before the last suicide burn so you can see we are always above minus two G of this situation except posit ten last seconds when we have a - 5 g of deceleration during the suicide burn so it's to be possible for you months our second venture version named Calibri it mean hummingbirds it but in falco Navy it can initially send sixteen and all turns and Italians can practice 6:10 pilot one of the requirements was to try lowering the mass as much as possible this has multiple benefits either you can put a bigger payload or it's cheaper and we went for the bigger payload so we're gonna do a we want to do an arrow braking maneuver especially for the Falcon Heavy launched spacecraft the aerobraking maneuver the way it's going to go is first we're gonna do a circular eyes burn so this puts us in a highly elliptical orbit and at the apogee of that orbit we're gonna lower the perigee into the Martian atmosphere at about 100 kilometers and that's where the arrow breaking is actually going to start each time we're gonna pass into the Martian atmosphere so we deploy the heat shield at that moment we're going to there's going to be drag that's going to be created this is going to lower our speed and lower Apogee and this is why we need the RCS at 45 degrees because our design is unstable and so if we want to be able to perform our braking correctly we're gonna need to have a lot of attitude control and we really depend on the RCS just to keep the attitude correctly and shields pointed towards the atmosphere and finally we are going to continue that our braking maneuver until the lander falls onto Mars and then we're going to perform EDL we could have done an arrow capture but we thought this was technically more complicated as it's never been done before so we we prefer to stay on something more reliable that has already been done before aerobraking has been performed by four probes up to now to lower an altitude it's never been done for a lander yet but we think it would be it would be easily possible to actually learn something like this and with the aerobraking maneuver we gained about 1,000 meters per second of Delta V so that's a lot of fuel and we didn't do this for the crude versions well because we don't really want our astronauts to spend some extra time in space there are gonna already already gonna be there for six months so air breaking its it actually means less stress on the vehicle because we're entering the atmosphere you can see it on the graph on the left at about 100 kilometers we're going at mark 20 and on the other graph for a dynamic pressure you can see that there's basically no no stress on the heat shield most of it is during the descent and we can we have a lot of control during the air breaking and then we can do the EDL as smooth as we want so now it is same phases for the tour under we start the atmosphere on three so for this we use an impersonal inflatable aerodynamic shield we use it above 80 meter and we drop it at each limiter of altitude before to start the suicide burn on the last patrol propulsion phases and we need to find to land under 0-2 meter of altitude so it's yellow blue and dark blue part on this map to have enough atmosphere density and enough time to to to decelerate and to learn safety on us so we're just gonna walk you through the EDL this is the colibri lander so the one that has performed the aerobraking maneuver it would have been the same with proven the heavier one we would just have performed a burn to enter the Martian atmosphere instead of air breaking so at about 90 kilometres our entire orbit is inside the Martian atmosphere if we can still call that an orbit so we're gonna slowly enter the denser parts of the atmosphere and about 55 kilometers the is where the heat shield is actually going to start doing all the work at about 40 kilometres this is where there's going to be maximum thermal flux and until we reach 20 kilometres this is where we're gonna reach max Q maximum dynamic pressure at about 8 kilometers of altitude the heat shield is not gonna stop us much and so it's just basically deadweight so we don't want to slow that down anymore so we're gonna just jettison the heat shield so that we have the minimum mass we need to slow down and I just forgot to mention we have already separated the solar panels just to get the minimum weight to slow down and finally at about zero kilometers of altitude at the very last moment we want to perform a suicide burns so this is the most efficient way to land so we're going to deploy the legs the suicide burn is a great way to land something but it's pretty risky so just to make sure that we don't blow up or anything we went for more human sorry we took a fuel margin of about 50% of the fuel requirement we need to do the suicide burn so that we have a bigger margin to land and so that we can land safely and finally we land at about zero kilometers or underneath to have enough time to perform the partner our deadline is 2026 until these dates the best lunch windows is on November of to 20 26 if we begin in - in 2019 we have seven years to develop our Lander it's similar to to MSL mission which spend eight years so we decide to based on this timeline and which curiosity is the biggest pilot span on Mars optional so we know that MSL mission of a two years delay when we analyze more person precisely we can see that palin needs a long time delay represented by the red line our line is other of the line i'll negligible beside the red line payload so we decided to put two years and all for the design and the the other years force developments assembly and test to develop other parts separately and then assembly until the launch in november 20 26 and six months after the lander landing on mars so now we're gonna talk about our cost estimates based on what we saw and the other projects that have been done so these are mostly MSL and from what we've seen the cost development we think would be of about 1 billion dollars once that is done we can start sending the landers and this is where our two configurations come into play either we have gullibly sent with falcon heavy we just estimated that the lander would cost about 300 million to build and with the launch cost of about 150 million so this means at the end we can land six tons for about 450 million dollars and on the other side to be able to land 10 tons we have premium sent by SLS which is going to cost a bit more because it's bigger so there's more structure and more fuel and this would be about 400 million that's what we estimated and the launch would be about half a billion so we can put 10 tons for a 900 million this is this is the reason why we wanted to do it if we want to send like a return vehicle or a very big hab that is 10 tons then the SLS launch is is the option to go for but if we have smaller payloads that can be broken down into things that can fit in six tons then it's more cost-effective to send them with the Falcon Heavy and if for the same amount of money again we can have two launches so 12 times in total or 10 tonnes so this budget is dispatched on seven years by on three phases design development on operations is for the first on the second launch we just have development and operational operational phases so it's 1 billion um if we take for example the International Cooperation across the International Space Station we can imagine what NASA just have to participate at 80 percent and 10 percent pollution agency on 5.5 percent for the European agency so if we if we have gen sorry if you have only 80 percent of the cost provide by NASA it will represent a tonne with millions so 800 minutes on 7 years it's only 0.5% of the NASA budget by ear so it's quite reasonable for space project we'd like to take a moment to talk about the limits of this project this was a lot of work obviously for us and we think it's just fair to talk about what we think are the limits because that means we can show you what we're more confident about and something like this obviously has limits the first thing is there's not that much studies out there that talk about sending big payloads to Mars and most of the studies are actually done before MSL so before we had even sent one ton to Mars on the technical standpoint this is a very general concept obviously and we were just three our calculations are based on assumptions and approximations we are we feel confident about the approximations that we have shown you but again these are not super detailed we have to use student accessible tools obviously this is why the software will use our only student versions so we didn't go really into details because we just couldn't and we we couldn't do any hardware tests or anything everything is based simulations we tried to cross the planet the different softwares we had so that we are sure that the simulations we have done are reliable because we have the same results on multiple platforms and one of the biggest components that we use is the inflatable heat shield and this is currently under development it has never been flight proven so we think it's gonna work people are really working hard on it but it's never been fly proven so that's a big question mark about it but it should be fine by 2026 it's no super future high-tech hardware and finally on the schedule and budget well there's no comparison never nobody has ever landed ten tons on Mars yet and while we're engineers we are engineering students were no financial experts or anything so we think the cost estimations we have done are pretty good but again were no experts so now to sum up our project before the conclusion we can say we designed to endure two possibility 1 4 6 10 we can send to for the same parts right one for 10 tons we used 2 different lenders thanks to the technical shows but we did we have a simple solution the same design same architecture between the two Lander just a question of size and it will cost 1 billion and the advantage of this 2 solution was but we are really adaptable for help so first gem Danielle for his knowledge who news program heiress then Guillaume Duchenne for his knowledge on high-speed and then he shared man on this room for is the knowledge and all his advice for our project we just like to conclude saying that well just first of all thank you for having us here and we really like we really like to see people on Mars and we also want to be a part of the people that help send people there or even actually go there ourselves so thank you very much for your attention and if you have any questions we'd gladly like to answer to them [Applause] okay I've got a couple of questions I'll answer all es come both than you answer one is a simple question what kind of rocket delta-v do you need to land falling from eight kilometers to the surface two to deal with that but then also the other question I had which was on your vehicle the plume the small small one that was the 6-ton Lander it seemed like you had a rather long Lander behind a relatively small Aero shell and then for the heavy Lander you had a rather short Lander behind a bigger Aero shell my concern my question is what calculations did you do to make sure that the heat that is the the hot gas that is coming behind the aeroshell does not hit the lander in cooking so that's why it's totally doable for humans and 200 250 metres of second of delta v of fuel so that we can have a total of seven hundred eight hundred meters per second of Delta V fuel and the second question the answer most of the dimensioning was done on CFD so we didn't look exactly into the heat that would be generated on top of the on top of the lander but from the results we have on the CFD there were not that much air that was going back up there was deep pressure like lower pressure zone that was totally encapsulating the the liner so we did not do any particular thermal test on the whole lander but based on the CFT we saw that it would still be in a very low pressure zone I don't know if that answers your question first for the capture of the larger vehicle did you say that was repulsive capture with no aerobraking okay and then I just want to clarify that one or the the studies you did did you look at direct entry I say you ruled out aerocapture because it had not been done before but wondering if he also looked at direct entry and how that we're comparing your trade and that's what we gained with the air braking and then the idea is pretty much the same so we just did the calculations with a smaller the sorry bigger lander but as the pretty much same trajectory as the one that would use the arrow braking the only difference being how we slow down but then the EDL is pretty much the same other than the cost of the rocket how did you come up with the cost of the development of the lander itself both together cost we saw mostly on the scheduled costs of MSL and we try to scale them up a bit but it's we're not creating the payload we're just doing the lander so we took the cost estimates that were given by the just making the lander on msl which is not that easy to find because they just put everything together and we just try to scale that up a bit and this is pretty much approximate for the Landers we tried crossing different things on the HTV for example how much that would cost how much the other capsules would have cost and again trying to average that out and see how much it would cost about that thank you so for human missions it's kind of a unique case where you'll have multiple Landers going to the same landing site or same general vicinity so detaching portions of the heat shield and jettisoning and can result in some risk exposure that you might hit something on the surface but there are plenty of ways to target those disposal maneuvers safely but I was just curious how are you separating away from the heat shield so you've got a fairly lightweight heat shield and a heavy vehicle behind it we just propulsively yeah so that it just Falls and we don't fall with it you can see it on all the pictures we just burn so there's a difference of speed we didn't really look into um so the three reasons why this type of trajectory that you that you assumed are typically not done our long duration which isn't a problem here um difficulty of precision landing which is not a problem here and thermal soak this type of entry with a very shallow approach an extended run-up tends to thermally overload the vehicle even if you have a very low peak heating so have you conducted an analysis that your I ad which is not a very big thermal mass is going to be able to sustain the extended thermal soak of this extended aerobraking and very shallow ETL process before being jettisoned right on the tests that have been done and so we didn't do the the calculations about that we just refer to the literature and what we found in the studies of eye ads that are currently under development and even them are not exactly sure on what materials to use for example that's not that's why we didn't go into details about how to make that one but from what they're saying it should be most of the studies are actually trying to land 40 tons so that's much bigger those studies typically assume direct entry where thermal soak it's not quite as much of a problem okay thank you for your 10 ton Lander roughly what do what was the entry mass when you enter the atmosphere to land the 10 ton payload I don't recall I think okay so so 18.5 ton entry mass to land the the 10 ton payload yeah and then so then then what was what is your launch mass for the 10 ton Lander when you launch it okay so so so you're launching 40 tons towards Mars and but the the mass of what's entering is 18.5 tons yes okay all right thanks thank you very much for your attention [Applause] any further questions a little bit okay I guess that's it thank you thank you very much next team is the good afternoon everybody we are team yoga Nava we are a team composed of nine students from all different backgrounds and all over the world and we are kind of exciting master in space science actually not technology at the University of Ljubljana in Sweden so here with us today the Gabrielle Felix Sam well Flo and myself Antonella so today we're gonna go through the mission design the spatial design the project management and we're gonna do a brief conclusion about our spacecraft our canola studying with the mission design so we were given some requirements first of all we had to be able to run a time entry time payload on the surface of Mars it had to be safe for humans the meaning that means we're gonna be within the 5g limit additionally he had to be cost effective and he had to be ready to launch by 2026 we've faced some some challenges first of all the payload given to us was 10 times heavier than anything ever landed so far on the surface of Mars we have a time-critical descent given that the entry descent landing phase only lasts a couple of minute meaning every face has to be very accurate the Martian atmosphere is thin meaning that we don't have a very drug force on a spacecraft to slow it down but it's also thick enough to create heat and thermal thermal stresses or spacecraft and we have unpredictable any windows mean either when we go to a parking orbit we don't know if we're gonna find us turns or what kind of weather we're gonna find to actually safely land a space work on the line is I given so the mission field and the mission face is our first one is our orbital phase so as an initial assumption we are given that a spacecraft is an actor volley trajectory of three kilometer besides our the my sphere of influence the orbital phase include a my sculpture and and afterwards after we capture Mars we have to lower it our orbit to reach a low circular orbit in which we kind of purpose please practice some system check if we have a crew actually we can also do a health check on them and also find the best landing window afterwards we can a detached flip and stabilize in this phase we're going to detach the propulsion system using for the capture state we kind of sleep if needed in order for the heat shield to actually point in the right direction and we're gonna stabilize the spacecraft afterwards we cannot have the heat she deployment the entry in the atmosphere we're gonna also descend through the atmosphere of course afterwards we cannot detach the heat shield to start a supersonic retropropulsion deceleration to actually hopefully successfully land on the surface of Mars if everything goes to plan but where do we land for the land inside choice we went through a 2020 Mars landing workshop evaluation that was carried out and the selection were based on some criteria what was actually considered for us the most important one was if any of the land inside could have a possible scientific discoveries and also since we always had in mind to possibly have humans landing on Mars if any of the lands I could actually have some water resources that's we decided the two best optimal and inside so far it was first one the j0 crater and the other one was the NCATS both of them are actually very close to each other being under latitude of about 18 degrees and they have an altitude of roughly pi minus 2 kilometers but how do we get to the land inside for the trajectory we actually through went through a narrow braking and a propulsive capture analysis for the arrow breaking the target RB is slowly reached by the atman mainly reached by at the atmosphere drop meaning a spacecraft is actually gonna be lighter meaning cheaper the problem is that it's the length is too high for aerobraking maneuver if we're considering humans on board on the other side for a proposal capture yes it is too fast it is very fast but the Delta be required is solely provided by the propulsion system meaning a spacecraft is actually going to be heavier and more expensive for the first one for the aerobraking we first are gonna insert ourself into a highly elliptical air eccentric orbit we decided to have an inclination on 90 degrees for the aerobraking case because we want to take advantage of a higher density of my son atmosphere at the port afterwards we use another general mission analysis tool to actually simulate the orbital we're gonna whether we would before and this is what it would look like after the other theme we can into a highly elliptical orbit we actually study aerobraking phase in which we wanna know where the RB to around 110 kilometers and then start DDL phase for the other braking phase we are we brought a MATLAB code in which we simulated being aerobraking phase calculating the Delta B for every single orbit and to find the total time required and the total Delta V and we found out the dust of your aerobraking were roughly B minus 1.24 kilometer per second and it would take us two hundred and twenty days for the propulsive capture we decided we have to do a man sculpture and it's completely done by the propulsive system and we cannot do an impulsive burn at the periapsis of the upper-body country trajectory and again we want to lower the Mars DM we want to lower the space kohlrabi to have a circular orbit of around 110 kilometers from this we used again NASA to simulate our orbit and we were able to find the Delta V required and the inclination the thrust is given by the characteristic of our propulsion system the Delta P required is roughly two point 27 kilometer per second we chose the inclination to be lower than the 90 degrees because we wanna and to be 35 degrees because we actually want to use the Ahmad we won we'll use the Martian rotational speed to give us some help and reduce some propulsion way and also it had to be higher than our land I'd like to do about 18 degrees and this is what our simulation for the trajectory looks like for the propulsive culture afterwards we carried out a trade off between the aerobraking and the propulsive captures trajectory as you can see from the table the aerobraking would take us 228 days but we would consume around 23 tons less of fuel so it was always in our mind that we want to land humans on Mars so what we did more important was the human factor meaning we wanted a very fast entry so we chose the propulsive capture because the aerobraking would takes 228 days if you are the six months of interplanetary travel we exist heavily the limit for asteroids exposure to radiation and weightless condition the aerobraking trajectory would be good if you were all listening if you had in mind only a cargo mission of 10 tons on Mars and now talk a bit about the spacecraft design so here we see an overall picture of the organ of design design consists of two main stages an outer capture stage and then the central Lander stage we chose this because we want to reduce the actual mass landed on the surface so the landing stage consists of the payload and everything required to bring this payload safely from a Martian orbit to the Martian surface additionally we have a capture stage which serves only to go from interplanetary approach to the Martian orbit and in between the two stages we have an intersect release mechanism and attached to the lander stages and hid which will be dropped before landing and we'll go into more detail on that just now so this capture stage this is what it looks like it consists of four yeses two engines and 37 tons of total fuel nitrogen tetroxide and mmh and this these are the main components and they're enclosed in a structural frame and then in a 20-millimeter shell all around we didn't do a very detailed design on this capture stage as it's a basic rocket stage we focus our efforts on the lander stage the lander stage and in yellow I think pointer this is the payload at the bottom and below the payload we have thrusters you can see one year there's a true that brings of thrusters which are for the final descent and above the payload we have a central platform and above that the fuel for these thrusters from fuel tanks and here we have landing legs in the deployed final position now how do we get this this is a four scale roughly what it would look like this is about five meters from here to here and how do we land this craft safely on Mars now there's several deceleration technologies possible to lose the Delta V of about three and a half kilometers from the Martian orbit to the surface traditionally parachutes is the go do you think the problem on mass of course is that it's we are certain if you have such a big payload the parachutes become so big oh no it's about 27 meters would be required and this is problematic because it hasn't been achieved before and there's stability issues with such big parachutes and they become very heavy if we try to use a single solid heat shield and turns out this also becomes very very large for such a big payload and one of the problems is it won't fit in the launch vehicle we launched from Earth we have one solid heat shield it won't fit and oh we could use supersonic retropropulsion all the way from orbit and here the issue is with a halo you need a lot of fuel and the more fuel you had the heavier becomes more fuel you need the rocket equation is not kind in this regard it should not be very cheap so NASA is a way of all these problems and has been in research in the last decades what else we can use and one interesting field as we have seen before is and these inflatable aerodynamic decelerator z' particularly we looked at a hypersonic inflatable decelerator in hid which consists of an inflatable structure and covered in a thermal protection system and this is basically a heat shield that you can blow when you need it I'm showing here's the Erb III am hid that has been tested on earth there's been some test flights every three are before but it hasn't been tested on Mars however the technology has been investigated for a long time and is quite feasible we believe therefore we chose to use an hid for these raishin now we cannot use the hid all the way to the surface we will have to have propulsion for the last section but we want to maximize the amount of Delta V we lose from the drag of the shield therefore we want to be in the atmosphere as long as possible so to do this we need to have lift we don't want to come down straight we want to come down and to gain each other high L over D ratio lift of a drag which we can achieve by modulating our angle of attack normally we do this with the shape of the vehicle but that means we have to change the design of actual structure instead we investigated the use of an isometric hid so this means we shift the central axis of the hid to make one side longer and the drag is a symmetric and the more you shifted different characteristics are achieved it modulates the angle of attack which in turn lets us control by the amount of shift that is desirable to maximize and it is the benefit as I said of keeping the vehicle symmetric on the aerodynamics on the Left we see the effects on angle of attack and led of the different shifts and looking at this we decided to go for a 40% drifted hid it also has effects on the stability of the craft and the red line is the line of force through the center of gravity so the optimum case for our lander turn out to be a 40% shifted hid we can see that the line of force is quite in the middle which is good so it means the marching will so be central and symmetric to the vehicle finally this is what a design looks like we have the third version and marching and then it's deployed it will look like this once it's inflated and the best diameter is 15 meter and the nose current is 9 meter diameter launch vehicle and now the surface and we'll then use the thrusters at the bottom for final which is full supersonic but a final propulsive landing now we will hear a bit more about this landing thank you okay then for the proper design for the propulsion design we faced with you had to decide what kind of field we'll use and then between the three types of chemical thruster in the market we decided we propellant because they give really really good thrust with icy storage so for the second that decision will we choose a fifth type of pressure feed system we tell you within you that gives a constant profile with different we start with circle restart and a lower complexity then between the thrust that we decided that it's state has different thruster for that reason for the capture stage is a single plan that comes last several minutes so the thrush is not so important but we really want us a specific input because we want to lower the the mass of the fuel the mass and the of the thruster is not so important because it can be neglected to the mass of the total of the mass of the stage then as a final decision we decided I stood two thruster that has been already proved testing with the Ariane 5 program and enough it is a really high specific input of 340 340 circles then for the under state the situation completely opposite we want to get reduce the velocity of 345 meter per second in a very short time period of time for the reason we need really high flush of the of the rocket and we also want to minimize the mass on the side to reduce the mass of the the state then I saw that as a final decision with we decided the SpaceX super Drago because it was really high thrust with really small size it's also allows to make a smooth landing and then the last set of thruster that we use is the RCS and for them the main concern we took into mine it was to send the same propellant and fit system as the London thruster so we don't have to crystal weight or the complexity of the London stage then the rescission world a special drug that it's used the same propellants and the same system only changing the bars and it's also a really good thrust to vessel size ratio then solar simulation will run and to decide how many first we need for these states for the capsule state we are we only need four thruster and we will use a square configuration then for the primary for the primary thruster that are the ones that using the landing we used to consent agrees of plates and face roster regarding issues of stability and bloom cleaning and the interactionism plans that we will talk about later to finish the RCS control we decided to use a twelve twelve rush them with force for flag for symmetrical structure in each side as we can see in the report on and two two sites okay and to finish I want to make a breakdown of the fuel fuel that we can see that the main part of the fuel is in the culture state that we need thirty six point seventy five strands of view that with a Manning of two thousand kilograms this man is very thin because a bit very tight because the manual is really straightforward and we and rockets are being tested and then for the London stage we need to the fuel have to be necessary enough to to perform all the maneuvers like leaving the party Norman orientation and control and landing in this in the London state the margin is high because we need because because of the mission mission critical nature of the London among people and also to cater with contingency scenarios so we can see that in total we need a 46 tons of you roughly ok and then I'm going to let my colleague to talk about a structure Thank You Samuel I'll continue about the mechanical system overview of the land itself so we have to land the payload somehow it's 10 tonnes that's what we know we decided to go with the disk as a shape Wanda meter height 1 meter height and a density of about 1 metric tonne per cubic metre the structure is designed around the payload and of course also about the propulsive system the lander structure it's a blunt body entry profile so we have more resistance to break we have to minimize the thermal loads and the center of mass and tent of pressure is almost the same so we have more stability during descent that's also because of the payload being relatively near to the bottom of the whole lander we have a lightweight design we used a frame with two decks so that one is here deck to here and we will talk about this in a second and we use our main materials are aluminium and titanium alloy which are both space grade metals so they are available and tested next of course we have to take a look at the most critical parts of the lander so we have a central plate and we have the frame first central pride we use a honeycomb centered structure to be very stiff and [Music] also light we did a simulation for natural frequency allowances so we have the first and the second mode on the left first mode on the right the second mode of those frequencies to analyze the actual stress of the whole central plate for aluminium we exceeded the displacement and stress by power so we can't use aluminium at all for this central plate so we have to each other me titanium for the time the maximum displacement is only 0.136 millimeters at a frequency of about 45 Hertz it's absolutely acceptable therefore tettemer is required for the frame we did a simulation with the maximum load of five g's and we saw that the stresses limit the the stress and displacement limits exceed the stresses of aluminium by far so for the frame we also have to use titanium so we have a structure analysis so let's continue with thermal analysis for thermal analysis we know that the planetary and aerodynamical loads heat loads are much much higher than the space environmental loads therefore we simulate for the most extreme case in the final landing where we just detached the hid from the lander itself so we get the hype supersonic air flow or atmosphere flow from Mars to the lander while we are still thrusting with our thrusters therefore we have a radiation profile of 718 watts we found out in our simulations which equivalent to a temperature of 69 degrees Celsius maximum on the outer shell of our Lander therefore passive controls absolutely sufficient with 12 to 15 layers of captain MLI which is a pretty standard in space so next I will talk about the challenges with the plumes so what's a plume in this case the plume is a hot stream of gas coming from the engine exhaust so why is it important well we don't want to land on unstable environment so we want to be safe and land safe we could land on icy surface which would melt or the heat of the exhaust would melt the icy surface so the icy surface would supplement we could land on a sandy surface which would create a crater as you can see in the pictures or would crystallize the sand itself which would be unstable or we could land on the rocky surface which could eventually create as a dress projectiles for the legs for the lander itself this all has to be considered and there for optimal aeration is needed for thrusters and their landing gear coming to the thrusters so we want to minimize the overlap of the inner plumes in our design to minimize the pressure that is overall in the Blues here in this picture you can see the red dots are all the thrusters itself so we have to as I mentioned was mentioned before we have to raise our thrusters one outer and one inner ring the blue and green circles represent the diameter of the plume the maximum diameter actually in mass Martian atmosphere with this we have the optimal engine arrangement for our case the maximum bloom radius or actual diameter is four five point three six meters so the legs have to be outside of this radius and the legs are designed accordingly so speaking of the legs we have four actuated spider legs of course with dampers arranged in a ninety degree angle and at a diameter of 6.5 meters so we have even more buffer to the actual proved to be safe next I want to speak about the LCS and communications so for IO CS we have a low pointing a currency requirement so we can use Star Trek as Sun sensors IMU and B RCS thrusters with their redundancy of course I am you because it's critical because of the timing it has hot redundancy for communications because it's pretty standard what we can use for this mission because quite near we designed from heritage for the capture stage we have a direct link to elf for the land that we had in UHF relay to the satellite which will then relay it to earth for the power systems since we have a very short mission of 336 hours and we're starting from the mass capture we can use we can use only batteries for this stage and our main batteries in total we'll have 52 kilowatts per everything shut down alright so speaking of batteries we have them battery capacity a total battery capacity of Lander and capture stage of 52 kilowatts kilowatt hours and a mass of 104 in kilogram but the batteries are mainly into in the capture stage so we can actually we don't have to land it so as you can see we only have 0.6 kilograms on our lander itself doesn't have very low requirements for the whole battery next we have our design we land on Mars but we now want to know if it's actually correct so Kepler will continue with simulations and the proof that it's actually possible and use to the equations of motion and the first thing we had to ask ourselves okay the atmosphere is the critical components we looked at different models from you from NASA and we picked three models in the end which is basic model one that's simply a fit from data from an actual on mission and a scale height model and there we said okay density as the most critical component we want to be conservative in the assumption first so we took the model with the lowest density in the higher altitudes which is model two in that case why is the lower altitude not that important because there we will be thrusting so the thrust will be defining design training in any case quick analysis with different models and showed that with all three it's still possible and really the most conservative is possible then we also had to characterize the HIIT I've seen before in the slide rather complicated this is just for the 40% shifted these are the characteristics we could use and we wanted to use an L over D of about 0.2 75 according to a study that we found so this is where we ended up with and this is also in accordance with the minus 20 degrees angle of attack that we get from the shifted hid design we also were concerned how stable is the hid how long can we use that and we found a study that shows that the aerodynamic coefficient down until mass of about let's say 1.5 1.4 so around here you can definitely use so we used Mach 1.7 so we use our age HIV until Mach 1.7 to have a bit of margin to mass 1.5 then we can look at the decent trajectory and the standard graph that's always shown is all the truth versus velocity and as you can see this is comparable to current characteristics due to the hid and also the two-dimensional trajectory what strikes in the first place is we can see that there's the region where most speed is decelerated we could move that into the atmosphere every dynamic deceleration so we did achieve what we wanted to with the hid and it's still a rather small portion of the actual trajectory interestingly then we also see the start of the frosting phase which is at around 345 meters per second which we need to decelerate only by thrusting in the trajectory this scene here we don't see any like harsh Nicks harsh dancing there it's really just nearly vertically going down to the ground in total we move about 700 kilometers above ground as can be seen here in the graph and then we also looked at the aerothermodynamic loads first we looked at the pressure loads actually which gave us the the G loads we had a hard limit of 5 cheese but we ended up actually at minus 3.5 cheese as a maximum load which is favourable considering especially human exploration again which was always the case for our study then you also have the thrusting phase which can be easily seen here it's also just half a G as we assumed currently worst case again rather continuous thrusting instead of just a suicide burn to lower the effect on human bodies then we also looked at the heat flux which we used a sudden grace model for and we see that a maximum heat flow of 35 kilowatts per square meter is there which the H I candy can easily take because it's actually normally designed for direct entry and our heat loads will be lower due to the low mass orbit we enter before and then I want to briefly talk about project management so we first looked at the schedule as we can see the Draco is already available the driving factors are actually the hie D which has to be developed and the landing legs because it's a mechanism that has to be developed the other custom parts are also rather late in the design because they have to be developed to but are not that critical all other components that are not shown are assumed to be commercial off-the-shelf components so it is not that critical as we can see the lanyard stage should be assembled by 2024 so we should have a two-year margin actually to our launch date of 2026 then we did a risk analysis we could identify 11 sources of failure and then we narrowed it down to three major sources of here which are the hid the landing and the software and hid in landing is simply because this has never been done before in that manner so there is a huge risk attached to it because there is no experience there for heavy testing is required on earth which drives the cost HEC later and software is also a point as we looked at other missions and have seen their software often has caused issues at least then we looked at the cost as you can see power communications and control as we have rather standard things we have extremely cheap subsystems in that respect the main cost drivers will be the structure thermal and Mission Operations structure in thermal mostly as I said it's its special design and we have to develop it newly Mission Operations is assumed to be as high because for the first time when we want to launch so this is mostly for the initial launch for the first mission it's critical to have a lot of manpower on ground is for a human Mars mission so in total we add up at 2.6 billion dollars then we have a mass budget there we want to focus on the most important things which are the capture stage with a dry mass of 12 tons and the lanyard structure with a dry mass of 16 tonnes we always assumed according to ISA standards 20% margin Rock so far because they are newly developed newly developed subsystems all the other subsystems don't add too much to the mass budget so we end up at a total dry mass of the lander of 30 34 tons of the total of 34 tons and when adding the propellant we end up at 18 1 tons in Martian orbit and 10 tons on ground in the end so in conclusion we have a vehicle that's going propulsively and we captured into the Martian orbit it's consisting of two spacecraft I kept it parts at capture stage in the lanyard stage this allows us a highly flexible architecture in fact as we focused so far on human exploration but if we want to do a cargo mission we could easily the propellant heavy capture stage to a more lightweight era breaking stage or aerocapture stage even also we will use a shifted HIV as we have a natural stability considering having our L over D of 0.275 and flying through through the atmosphere we will be using supersonic retropropulsion mostly for the human factor again as we want to have precision landing and again as I said already human exploration was our focus the design also can use though for cargo missions thank you very much for your attention and we're glad to answer any questions we have eight minutes for questions you mentioned a payload density of one ton per cubic meter wondering if you've done anything to other payloads and very extensive analysis covered a lot of ground can you explain why you use two different reference orbits in gmat when you were trading off direct versus a versus aerocapture [Music] thanks to Jima we could actually have the Delta B's and also we can we've run a lot of simulation to actually find which would give us about that IV we also were aiming to have a flight path angle entry of about five degrees so we Jima we could actually do that in it is a it's a little bit limited well regarding to the atmosphere but since I was we just wanted to put it in a parking RV for now it actually gives a pretty sensory trajectory analysis for preliminary analysis that we'd like we did but there were two different orbits you had one for a direct capture and one for a narrow break can you explain why you use two different reference orbits [Music] you mean yeah for your your arrow breaking case you had a high inclination high approach and for your directed for your direct descent you came in North Victoria yeah breaking we had an high inclination cause we wanted to pass through the poles because we we wanted to periapsis to actually pass through the poles the South Pole in that case because we wanted to have higher drug Y for the arrow capture one we had a lower inclination because we wanted to you also use the rotation on Mars speed of Mars and yeah thank you so if I understand your your mass list correctly and that was a great mass list the the amount of mass that you're launching to Mars is 81 tons is that correct so so how do you launch that much mass is at two separate launches yeah that is we did ask about constraints in the in the competition and we were told that we only need to consider starting from the sphere of influence of Mars right so we did not like this was out of the scope of our analysis we are aware of the high mass right but the amount of useful payload master landing on Mars it is ten tons okay all right thank you um can you talk a little bit more about your schedule you know how long each phase is gonna take hope I can talk a little bit more about it sadly the experts who did it is not here today so the idea was to first find the most driving factors the most driving constraints which is as I already mentioned the hid and the custom parts we did not include so all that is mentioned up here is technologies or are technologies that are either in development or have been developed to some extent already or tested not necessarily exactly in the configuration we would want them but at least let's say TRL 60 are around that TRL should be about right as we did as there have been tests again for example landing legs is a concept that is not has not been used so far but we can test it on ground and can be developed hid is it has been tested at NASA but obviously not attached to our spacecraft so that would be testing when in principle it has been there - still it's completely new it has never been done before so testing is I have heavy driver exactly our hid will be a bit bigger than what has been tested so far for components like electronics like communication power we we do not require very special components in that respect so we did not assume that they will be driving the design and therefore we came to the - to this schedule yeah one more question um you had the payload pretty low in the vehicle and I think you mentioned that this was to help lower the CG as your earning a propellant towards the end we're just curious did you guys spend any time thinking about how you would deploy the payload if it was something that needed to be taken off the vehicle yes you know mechanical design we have an access back to the payload it's not easy to see but there's a kind of a door but we envisioned this being part of a bigger program to land on Mars with many vehicles many Landers and we assumed that you would open the door and we don't question you rejected aerobraking because of the long amount of time to execute the capture why did you reject direct entry okay yet because we are tearing humans and we don't know how it's done much fear I mean we don't have a really good simulation of the most fear and if we go die rolling through into the atmosphere and suddenly the rosetta stone we don't know what can happen so we want it to a stop in a part in orbit so we can just like see what is happening from them and then decide ok this is a safe window to par to land and then we arrive to the place we want thank you I believe that's their time all right thank you very quickly there was also the consideration we can do final systems check especially in the human exploration mission we can also check through health status again after spending the time in interplanetary flight and if necessary we do not need to go down on the surface we we would we would have simply time to consider okay does the crew is the crew able to withstand it would it need some let's say training additionally to build up some muscle mass again not favourable all of it but we simply wanted to have kind of a security layer in the in the architecture of the mission with the intermediate stage of the parking orbit right thank you very much the next team is Virchow from India and Italy good afternoon my name is Chris and I am here representing team dojo and I'd like to present our design for the Red Eagle Mars Lander design competition the thing that struck us when we read the competition briefing was the statement the requirement is to design a 10 metric ton payload capacity Mars Lander that can be designed built and launched no later than 2026 as cheaply safely and simply as possible now cheaply safely simply so basically we aim to use heritage technologies we have especially taken inspiration from the Apollo missions we also considered other [Music] research technologies such as the morphing wing technology that you can see in the lower left of the slide and also reusable mass ferries that you see on the lower right unfortunately these technologies are not a sufficiently high TRL technological readiness level so we decided not to opt for those so what did we opt for well more on that later ok well first we decided to select the entry trajectory since we have been given a deadline of 2026 and Mars has a cyanotic period of 2.1 years so every other year there is no solution for the launch deadline given by the competition practically every NASA mission to Mars uses direct transfer so our mission will also follow the same trajectory however we have a problem Mars has a regula dust storm season and in this table you can see the predictions of the future dust storm season start dates and end dates these dates are based on historical data they also include sufficient margin the global dust storm season and mass it usually takes place from the northern hemisphere spring equinox of mass degrees now typically we don't want to learn any kind of human crew on mass during the dust home because Martian dust is bad for health in addition we cannot take high-resolution pictures of the surface when a dust storm is covering mass so our mission has to avoid the seasons completely this we can do by forming one of two options we can enter the mass of it and wait there until the storm is over or we can use an interplanetary trajectory that arrives after the dust storm season ends now often the Mars Landers enter the Martian atmosphere immediately without going into the orbit first so often the second approach is followed so we see that the 20:26 transfer in the previous slide it has its it has its arrival date just before the dust storm season so the arrival date is 3rd September and the dust storm season starts on 18 October 2027 same year so you have to arrive after the dust storm season ends that's first July 2028 so we are going to accomplish this by doing one full orbit around the Sun before we arrive at Mars so our launch date is now 5th July 2026 so yes how transfer time takes a full two years we we have we have chosen aerocapture for inserting our data into the orbit around Mars after the L capture propulsive maneuvers we'll insert our Lander into an acceptable parking orbit and then we D orbit the vehicle when it's ready to descend after ever capital we do an Delta V at the apoapsis to raise the periapsis and we establish an electrical parking orbit and the lander will remain here until it's ready to descend and additionally we can put other orbiting assets like a vehicle to take back a human crew back to Earth from Mars from the soffit another propulsive Delta V is used to deal with the craft such that it will meet our three kilometer per second entry velocity and we will have a peak deceleration of five G the reason we have chosen of five of G constrained it's because it's the maximum deceleration that a human crew can tolerate for a short duration after the lifting entry the capsule will continue to decelerate until our profile civ descent phase begins and it will continue till the lander safely touches down on the Martian surface this slide gives us a good look at the EDL entry descent landing trajectory of okay now we move on to the flight systems as I said we have chosen heritage technology so we have decided to go in for an expendable type of lander with an Apollo type of blunt bodies now how do we size this well as for the competition briefing we are supposed to be able to carry a maximum of thirty Mars exploration Rovers Amyas so from the internet I found out that MEA our dimensions are basically 1.5 meter height by 2.3 meter width and 1.6 meter length so we arranged the rover's you know five points five by six array and we have seen that they can fit into a 15 meter and I am it a vehicle but you have to keep in mind that this capsule is larger than any that has ever been used in addition we have selected L by D ratio of 0.3 because although we could go for larger values then we have a decrease in drag rather than an increase in lift and this can pose a serious problem on Mars where the atmospheric density is low and it is difficult to decelerate the vehicle to proper velocity before it hits the surface or exits the atmosphere so we have stuck to the maximum limit of L by D is equal to 0.3 and so vehicle height L is just 4.5 meters okay from various research that has already been done we can see that for an L by D that's point three and diameter of 15 meters and payload mass of 10 metric tonnes it will correspond to a little more than of 50 metric tonnes of initial mass and but given the high degree of uncertainty in how our subsystem masses may change as design develops and matures so we put a little bit of a mass contingency and we assume that our actual mass of the land including our payload will be 60 metric tonnes and as you can see on the slide we have also obtained the mass breakdown for our Lander and its various subsystems now let us move on to the various subsystems of our lambda let's start with the thermal protection system we have decided to go in for phenolic impregnated carbon ablator pika for short now due to manufacturing constraints we can have only a maximum thickness of one millimeter and so we have put one millimeter thick panels over fiber foam again due to manufacturing constraints we can't manufacture heat shield as a single piece it has to be in a form of tiled panels and you can see the configuration as on the slide the back shell of our vehicle is integral it's not discarded instead it's made up sides are basically in the form of three petals in the form of a tetrahedron and we will also be using small Ram plaits which are basically little ramps made of a Vectra cloth which are also connected to these three petals they will fan out and create driving surfaces for the rowers to exit the lander when it arrives on the Martian surface and now we move on to the propulsion system and it has created a significant number of interesting challenges we have decided to go in for a four engine configuration as you can see on the slide because it creates the largest amount of useful area for both the payload and the propellant tanks we have also decided to go in for existing technologies namely liquid rifle foreign engines using meeting and liquid oxygen there's also a huge advantage through using this system for mass missions because carbon dioxide in the Martian atmosphere can be converted easily to methane using a chemical reaction called the Sabatier reaction the methane produced at mass through this process can be used as a propellant for the Mars ascent vehicle or others devices like liquid oxygen ch4 fuel cells in addition we have decided to use propellant tanks of titanium for would you do the high-strength weight we show okay we as you've seen earlier we use a parachute system for deceleration we go in for an existing technology once again this cap band partial of diameter 30 meters the reason we have limited it to 30 meters is because there are concerns regarding material strength stability and fabrication the parachute will also be deployed by motor at Mach 2 again we can't go beyond this because otherwise it will get subject to error heating and also oscillation problems for the orbital thruster and reaction control systems we have gone in for the same configuration that was used by Apollo 12 roster configuration we also use a hyperbolic system using monomethylhydrazine mmh and in 204 again because of its simplicity and reliability moving on to the C 3 system command control and communications we envision that our land of they'll have two amplifiers two transponders one primary highly an antenna to smaller low-gain antennas again during the descent we will be relying on radar as you have seen during the EDL sequence Rob Nevada and also vision based navigation in the form of cameras this way we can send we can also avoid hazards on the surface for direct to earth communication we'll be making use of x-band antennas and UHF antennas in case there are local orbiters for transmitting engineering data during the EDL sequence please note that in case of human crew we may require a higher data rate in addition to what we are already using for the move on to the power system you know we have decided to make use of fuel cells using locks and me else why liquid oxygen and methane there provide power after separation but prior to entry we will be making use of lithium ion batteries for the EDF in case of the landing technology since we are using this land of may carry human crew and other sensitive equipment we have chosen landing gear instead of airbags or crushable material so far the randoms that have been applied by NASA predominantly used airbags but that won't be suitable for a human crew in the case of our Lando we keep our landing gear and a followed condition within the heat shield until the power descent and landing phase during our ETL sequence okay now we move on to the concept of operations Lando can be used both as a carrier for multiple robots we can use it as accommodation for human crew and the delivery system for a Mars ascent vehicle now for as a ruble Lander well I've already mentioned we have a five by six array of Rovers each Rover is held in place by bolts and special knots these are released after landing with small explosives [Music] basically the deployment sequence is the same as what is currently followed by M ers of NASA as a final step the M EOS will drive off the lander deck and onto the surface of Mars keep in mind that at the end of at this point the lambda is basically a lifeless shell it has served its purpose in protecting and delivering the Rovers for as a human crew accommodation well in the slide you can see how our Lander has been adapted for a manned mission to Mars due to its sloped sidewalls there's going to be a payment volume restriction in fact for 15 meter diameter capsule usable floor area works out to be only roughly 23 square meters that sufficient only for crew of two people so my living floor space some four years ago I believe there was an omission competition titled inspiration mass held by the mass society and this can be used for such a mission in addition it can also be used to land a larger inflatable have separately now finally it can also be used as a Mars ascent vehicle a mass ascent vehicle is a fully fueled single stage vehicle that can deliver the human crew from the Martian surface to a circular low Martian orbit and the pre deployed booster stage will lift them ma V and it screws to a high Martian orbit and thus the true can be sent on a vehicle to take them back home to earth now we move on to the schedule estimation we append as mentioned earlier we have selected a fixed launch date of July 2026 and so we have to set defined schedule now keep in mind since our Lander is adaptable for human use the tasks with the longest deviation are the ones concerned with the detail design and as well as the testing of both the hardware as well as the final assembly ok now the next slide it was a bit difficult so we have obtained information on cost estimation from online sources we have obtained it entirely in US dollars NASA estimated that the launch vehicle transportation would be approximately 100 Nola's v6 said 36 billion dollars the mass society also estimated around 30 billion dollars we decided to be a little more optimistic and go with SpaceX and so the launch vehicle transportation works out to be 36 billion dollars and the Mars Lander is a hundred and fifty million dollars according to SpaceX we are assuming there's only one and two and service provider namely SpaceX and okay now assuming that it's some kind of public-private partnership and so tax breaks government subsidies etc are involved so the cost may be borne entirely by the taxpayers keep in mind this is just for the launch vehicle transportation and the Mars Landers not for the Rovers so the US taxpayer population was approximately a hundred and thirty eight point three million individuals so the average cost for individual American taxpayer worked out to be less than three hundred dollars but you have to admit that this amount isn't that expensive because a single mass mission gets spread out over many years so in conclusion we have designed a lander that's a 15 meter diameter and weighs 60 tons to carry a payload of 10 metric tons so this meets our computation requirements especially since it can be carried launch date by the end of 2026 in future maybe Landers with other shapes can be investigated because they may provide better packaging for larger payloads over the longer term concepts write fully reusable Landers and more fingering technologies can be developed and implemented in order to improve the long-term sustainability of Mars explore by eliminating waste because you have to keep in mind that at the end of each mission the Mars Lander is basically junk left on the Martian surface so thank you for listening to me so I have actually a couple of questions one is you seem to have done a pretty extensive review and synthesis of existing literature and the course developing this so it's wondering if there are particular references or other aspects that you would see as being most relevant to the work that you've done here online Institute of Technology with NASA okay and then the other question I had was you decided to use aerocapture and yet also use the two-year transfer trajectory to Mars I was wondering in terms of some of the issues related to dust storms what your thoughts are on how going into orbit first might mitigate concerns their transfer takes a long time is we are just trying to avoid that dust storm season that's all because in case of a human crew Martian dust will be hazardous to their health and in case of robust they won't get good pictures out of it so when you're doing your assessment of ETL performance I noticed you had curves for using a parachute and for not using a parachute and so you ended up deciding to pick a 30 meter diameter parachute that you're gonna deploy at Mach 2 did you really get much of a benefit from using the parachute versus not using the parachute the advantage is really slight I mean did you think it was still worth you thought it was still worth carrying the parachute okay even with the mass and complexity the parachute and then to deploy the parachute you know I see you are trying to follow some parameters that we currently have used parachutes and so you're deploying it at Mach 2 how are you going to get your vehicle down to Mach 2 to be able to ployed the parachute were you thinking that we just couldn't happen aerodynamically using the heat shield okay all right thank you what was the source of the numbers in your flight systems mass budget please remember to cite or give credit to your sources unless your generators part of the competition you remind me what your total mass was again for the lander the total mass including the payload is 60 metric tons six zero okay thank you um I have a question since you're capturing into Mars orbit and before you land which would allow you to wait out a dust storm why did you decide to do a full orbit around the Sun before you go to Mars over concern of such thing that seems like that precaution is is greater than the waiting time you would be in Mars orbit to have a dust storm go away okay the usual procedure is the Mars Lander and does the Martian orbit immediately so I and does the Martian atmosphere immediately without entering the Mars orbit first so I chose to instead use a trajectory that arrives after the strong are there any further questions no okay so I'd like to take a five-minute break and we'll restart at three o'clock with the American team [Applause] my name is shir Mikan my name is Giovanna good afternoon my name is Josephine hello my name is Nani hi my name is Javed my name is Diego and this team is called Icarus from Cerritos High School and Cal State University of Long Beach and this is our 2018 Red Eagle international design competition proposal to restate our mission objective it is to design a lander or Lando Lander of carrying a ton metric ton payload with the crew to safely land on the surface of Mars by the year 2026 and by doing this we want to provide crucial information for exploration and development as well as to recapture the interest of the public for space exploration and research so for presentation we want to break this into two segments the first segment talking about our lander so what is made of its mass that is convertible and the second half of presentation is the mission itself so how are we going to enter how are we lent so for our lander we break it down into three systems our primary system our subsystem and our protection systems our primary systems consist of the Lander its fuel the engines and the payload subsystems consist of power the navigation computer communications and the RCS system and the protection consists of heating micrometeorite and radiation protection and so in the primary system our Landers Dakers stands 85 feet tall or 25 point nine meters tall with a 90 meter diameter and has a payload volume of 413 cubic meters and now we will talk about the engines that we considered to our Icarus so we'll start off with the vicus 4b engine that is a hypergolic engine then there's our L 10 b2 which is manufactured by Aerojet Rocketdyne and then finally spacex is merlin 1d and currently in development the raptor engines that are planned to be used by SpaceX is VFR rocket so for Micah's Ford be it fuel is you h25 with oxidizer of n2o4 and has a specific impulse of 296 point to the RL 10 B has a liquid hydrogen fuel and a liquid oxygen oxidizer and it's specific impulse is 465 point five the merlin 1d has rocky grade kerosene or rp1 and has an oxidizer of again liquid oxygen it specific impulse is 275 and finally there is the Raptor which plans to use liquid methane and has a specific impulse of 334 so some things that we want to go over is that you age 25 and is is a chemical and this fuel can stay stable at room temperature however if there's a weak and if the crew is in contact with it it can be deadly and then there's also the look at hydrogen it's highly efficient engine but the one main issue is that the propellant must remain liquid at the whole time that it's in transit to Mars and that would be quite difficult because the temperatures reach down to negative 259 degrees Celsius to 252 two resources for those hydrogen and oxygen as well the RP one is another choice that we considered however the oxidizer must be super chilled at negative 340 degrees Celsius the propellant also great degrades over time as it mentioned it is rocket get great kerosene and finally with the Raptor we decided not to go with that because it is still in development and the engine has not it is still going it is still going through some testing but we aren't confident in using that yet and so we'll run down through the masses so Vikas 4b has around 900 - 900 kilograms thrust gives about I had you 800 and 5,000 Newtons and the thruster ratio is 894 the ar-10 v2 has massive 301 kilograms its thrust is 110,000 Newtons and that gives our thrust to mass ratio of about 365 merlin 1d is about 470 kilograms and a thrust is about 930 4,000 Newtons and that ratio is about 1900 and again the Raptor we can't really give any specific numbers on that so with all that in mind we find out what the optimal amount of engines for our engine for our ladder is and we decided to go with the thickest because as mentioned before the engine the Merlin the RL 10 b2 and the Raptor all have to keep the oxidizer and fuel at a very low temperature and I would require a lot of energy so we just decided to go with a hypergolic suspension instead and also with amicus the three Vikings for be vacuum engines all three engines are capable of gimbley so in case of descent one inch and should fail but in the two of them two other engines are capable of compensating for the failed engine now we will talk about the subsystems one of the main subsystems is the navigation and before we go into the Mars margin atmosphere the spacecraft can use something called the deep space navigation used by NASA to navigate and communicate throughout space however once it goes inside the margin atmosphere the deep space navigation will not no longer be available to navigate through Mars so we will use the terrain relative navigation this was proposed by Mars 2020 Rover and basically it uses the synthetic aperture radar and cameras to map the surface of Mars and by using the data gathered by the sensors and comparing them out with the original course the spacecraft can decide whether to divert the course if necessary to to safely go and land now on to communication we will use an HRT for fully expand highway transmitter which is designed by General Dynamics this will be able to transmit a minimum of 25 kilobytes per second of data at a frequency of 8200 point five megahertz megahertz three antennas will be present on the land Lander - Wow it is in transit to Mars which will then detach as the lander enters its ever breaking phase and one which will extend once the lander has actually landed on the surface of Mars these Landers these antennas will communicate with the most Reconnaissance Orbiter and you should act as a relay to earth however should the MRO be unfunctional or should a accident happen the experiment video transmitters will still be able to communicate with earth but at the lower transmit speed now on to the reaction control system we will be using 18 or 40 thrusters in the same configuration as the Dragon capsule these thrusters will have 35 kilograms of fuel stored on board in four tanks with a total burn time of approximately 11 minutes which is well over what we need for this type of mission and then and this entire system have a dry mass of just over 97 kilograms going on to our power considerations will be using two mega flex solar arrays each with a diameter of five point five meters which this will provide approximately 25 kilowatts of power at the Martian sphere of influence which is five kilometres versus five kilowatts over the recommended amount by NASA and this will be complemented by five lithium sulfur batteries providing a total of 125 kilowatt hour storage capacity and these batteries will have a mass of 150 Co of 150 kilograms and as you can see by our power breakdown with the community the communication systems will be using the minimum amount of power power most of it will be going into the support systems such as such as thermal protection lighting hygiene and spacecraft kin control systems will use a also a large percentage of the of the power followed by the terrain navigation equipment and this will leave leave us with a few kilowatts of extra power as a redundancy in case more power it needs to be diverted to a certain system or where the solar panels get damaged in any way and onto the protection systems so first we will talk about the heat shield that will be used we will you we will be using the pica-x heat tiles these are SpaceX's variant of a coat the pica heat tiles and they can experience up to a temperature of 1600 degrees Celsius then furthermore we do have space the space shuttle's heat blankets that will be lined inside the craft and these will be used to absorb the heat and can observe up to 3000 degrees Fahrenheit or 16 almost up to 16 degrees Celsius and also with micrometeorite protection their earths we considered three types of these and these are using the ISS we decided to go with nasa's configuration where it's basically gonna have two aluminum plates that will be offset from the liners walls and in between those aluminum plates there will be Kevlar and Nextel and Emily they will be spaced apart and told the total spacing will be about thirteen point eleven point four centimeters for protection we decided to go a lighter magic lighter hydrogen based almonds instead of heavier mass elements like LED but we went with water you know in our materials research we found that some time use of water we're able to have radiations going through it and doing some portions our limits were 5 centimeters and few centimeters for design then we ended up going with 4 centimeters of water which would drop the radiates the incoming radiation by about 28 and a half percent and this system would allow for about point 18 sieverts of radiation being applied to the astronauts in a six-month journey and without it it would only be as a safety feature like this is only to increase the safety rocker and so now that we've complete all three sections of our Lander we're gonna move on with the mass breakdown so the primary system cylinder at the shell currently weighs about 12,000 kilograms our fuel is seventy-six thousand kilograms are three vikas for vacuum engines are 2700 kilograms and the Tenkiller the 10-ton payload of 10,000 kilograms for our subsystems the entire power power system will be approximately 450 kilograms the terrain navigation system would weigh approximately 200 kilograms the communication systems 130 kilograms and the reaction control system will also have a mass of 130 kilograms making our total nine hundred and ten kilograms approximately then finally we have the mass breakdown for the protection of the lander the radiation protection will be will be about nine thousand seven hundred kilograms the heat shielding in total for both the pica-x tiles and the heat blankets will come up to three thousand kilograms and finally with the mitre micrometeorite protection it will come up to about 110 kilograms giving us the total for protection to be about twelve thousand one hundred twelve thousand eight hundred and ten kilograms and so taking the primary subsystems and protection systems that will give our Lander a total of 114 thousand kilograms and so we'll go into our build schedule the first point of the build schedule will consist of the planning and design stage this will take approximately six months and will involve deciding on the window to launch as well as all other data needed to be compiled and to build spacecraft such a lot successful autistics and other types of planning and then for tech development there are a lot of unknowns involved in making into making this Lander for one there isn't a lander that is available in current in the commercial market for use does there needs to be a way to figure what justments must be needed to ensure the lander will probably function and prevent tragedies from happening one example would be figuring how to place if you get exhales integral into a configuration that will cover the Icarus in addition there needs to be development of the terrain navigation system to ensure that our craft will be able to fire at the right amount of thrust at a certain time if too little is put into the wrong height the lander will face her in trouble as a result the extensive amount of time is needed to develop the technology for Icarus once the design is proved to be safe and fast I'll review such as critical design review the systems including electronic communications navigation the engines landing systems would be tested to ensure that software and hardware operates without any kind of malfunction and during the testing phase of our technology we will begin the construction of three things the simulation or flight test article and the production model the simulation and the flight test article will then be tested with technology moving on and once that's been cleared it will move on to the production model so moving on to the spacecraft testing phase this would be going on from March 26 2024 to June 15 20 20 20 26 and what this is is we want to make sure we're sending people down on the surface and we want to make sure that they're gonna have a safe chance so everything is going to be tested to its limits just to make extra sure that they're gonna be okay after the completion of the simulator and the flight test article the technology is going to be installed for the final months of the schedule the final testing of all software and hardware will be finalized and the payload will be moved to the launching site now so for the mission debrief so our mission is going to be in four steps it's going to be in a aerobraking maneuver for a direct descendent free entry and then during that reentry we will have a power descent into landing so air working you're probably wondering why aerobraking well primarily this strategy saves us about one hundred and fifteen thousand kilograms worth of fuel decreasing our mass by 52 percent it also has a surprisingly minimal G load on the crew because a maxi celebration they will experience will be less than 10 percent of 1g when people think of air braking I know sometimes they can think of minecraft slamming into the atmosphere but it's more of a gradual pass through in order to slow it down this is the equation we use it's called the forget aerobraking equation and what it is is it tells you how much Delta V the craft gets slowed down by after one pass around them around the atmosphere it can apply to anybody and in this case it's the atmosphere of Mars which even though it's not very dense is actually suitable for an air braking maneuver so some numbers for you we chose the magic number for the periapsis at 98.6 86 kilometers we wrote a program based off of that equation and did a series of guests and check calculations and narrowed it down so that we would find the right height where the velocity where the Delta V that's shed off after one aerobraking pass at that altitude matches the Delta V that's needed to get to an orbit at that altitude and so the velocity when I would get there coming on from its hyperbolic trajectory will be five point seven eight six km/s the delta T from the arrow breaking into two point two eight eight two point two eight eight kilometers per second this would bring the craft an orbital velocity of approximately three point four nine eight kilometers per second also we have an extra two hundred meters per second of fuel that can be used as a to give us a nine percent margin of error because coming from the 2.2 million kilometers per second I get shot at home off then in addition this is just kind of an extra safety net although it's most likely not going to be necessary because we're going to put the Icarus and a 90-degree polar orbit which will give us the most accurate Delta V calculations keep in mind that aerobraking it's not completely accurate but this way we can ensure that it will be especially because the Martian atmosphere can vary also any future craft can choose any part of Mars to land on we chose help Lanisha specifically we'll go into that more later but this is just for future missions here's the graph showing that that the error as you approach 90 and 90 degree in click inclination you can see we chose the the red line is the equation we use it's the simple one with a non non rotating atmosphere and originally we were thinking of just doing a pretty flat equatorial orbit but we saw that the error was more than 5% and we didn't like that so 90 degrees it's not exactly zero but it hovers in the two percent range the next phase is the descent of surface so after a reentry we began a coasting face this is a parametric Perish equation graph representing altitude versus horizontal distance traveled as a function of time and I wrote a algorithm on my computer that calculates its position off its last known coordinates so how its altitude and its distance traveled and I can explain later but this equation will map the first 194 seconds of descent next we need next used to figure out a place to line our spacecraft and we chose to help sunny show region on Mars for a few reasons first this relatively flat and is situated inside a 2 kilometer deep depression inside Mars which gives us more time to slow down in in addition it's one of the warmest parts on Mars and as you can see by the graph during the summer the temp can approach roughly 30 degrees 30 degrees Fahrenheit and when when considering the average temperature of Mario's this is extremely warm and will be and will be an incredibly habita place for any human crew in addition the hallucinatory region has been theorized to have glaciers made of ice underneath its surface as well as accessible lava tubes for these astronauts and so we feel that this is the best place to launch an expedition to Mars as it could provide the most scientific date data as well as the best chance chances for human crew to set up a vacation and so during our planning we were trying to figure out which is the best way to descend and we figured that you could either be parachute aerobatic or powered descent so for these are all based on the Mars Curiosity rover and initially we thought we could use a parachute and then powered descent however with further calculations we found out that the air on Mars is way too thin and the we would not be able to slow it down in enough time we also considered air bags because the Curiosity rover landed with the assistance of air bags however we realized that bouncing around with these air bags being inflated would cause more stress on our human crew and it would also be expensive and a lot of labor to put it into the craft therefore we opted for powered descent instead and it's often well it's optimal because it slows down in enough time with our engines and we'll go into cost breakdown we'll first go over the advance mission cost model and then go into winter cost so we received this question the system cost from the Johnson Space Center for the advanced machines cost model we think quality of a quantity of six so that includes one engineering developing unit one a mock-up one simulator one ground test article one flight test article and one production vehicle with and also the this also requires the knowledge of the dry mass the vehicle in pounds and then the constant of which we are a planetary Lander so two point four six the first year of which the system is operation 2027 and since this is the first iteration of this model is currently block one and as this mission has never been ever done before we gave this a difficulty of two and a half which is the maximum on the scale and after plugging in these numbers and constants given to us the price for this is one hundred and twenty seven billion dollars but this price also includes everything so this includes all the subsystems of protection systems of being installed in the lander all the man hours required for research and development every small cost outside of the field and the Rockets going back to that while this may seem like an extremely large costs but out will be eight years then the average NASA but the average NASA budget would only need to rise to approximately seven point six percent of the entire US budget so it's relatively cheap and this is and compare this to the cost of the Apollo program with the average tune that NASA budget before the first moon landing was approximately three percent so so when when complain comparing this by the cost of overall percentage of our u.s. budget is actually one third as cheap as the Apollo program and so I was mentioned before the lander is expensive however that does go over the cost in designing and then making further Corrections and it does include such systems and protection systems the fuel we counted to about 1.3 million and finally each of the rocket engines we found out so the biggest for be each costs 10 million u.s. dollars so total of 30 million dollars and that brings our total to about 127 billion 31 million dollars to summarize their presentation the total mass of our Lander is 114 thousand kilograms and many of many of our parts are proven to be successful because they will be used and have been used before the year of 2026 such as the terrain relative navigation and the launch vehicle for like us for B and for our operations we have two main steps which are aerobraking and powered descent this will all cost 127 billion dollars and finally we will be able to create a working production model within eight years before 2026 this has been our presentation and thank you for listening [Applause] so this stone for question I've got a question can you tell me how you calculated your propellant mass so what was your Delta V that you assumed her descent in the rocket equation we used a Delta V of 3500 meters per second for the when you're talking about aerobraking does that include going from the trans-mars injection trajectory into an orbit around Mars or was it totally after you got into an orbit and then bringing that down right so with with the arrow breaking it's basically just we're going from the hyperbolic trajectory going setting our periapsis at 98 kilometers and making one pass and that's gonna give us an orbit it's not gonna be a perfectly perfectly circular orbit because it doesn't have to dip below the 98 kilometers but it's it's gonna be pretty rough and it's just it's gonna get us there that's the that's the point okay yeah that that's often called aerocapture but understood and then it sounds like you know based on Tara's question you were assuming no aerodynamic deceleration from orbit we were just taking the orbital velocity to compute the Delta B sorry could you repeat that I it sounded like your Delta V was three and a half kilometers per second so the Delta V from the aero break is about sorry after oh yeah that orbital velocity is gonna be at three about three point five kilometers per second okay so you did you take a look at whether you could use continued aerodynamic deceleration to decrease that do you mean like just coasting down that was fear yeah yeah that we're pretty much gonna do that with the power descent cuz the heat shield the the shape of it and the fact that it's gonna be going backwards is gonna help us slow down a little bit it's not gonna do as much as the arrow breaking but it's that's gonna be part of it yeah so I have a question so then the attitude that your vehicle is entering it is with a rocket engines going first going into the atmosphere and so that would be the area that you have to do aerodynamic braking yes they would be going backwards and at a zero degree angle of attack okay one thing we didn't mention was that we would also we considered having a rotating having our craft rotate sort of like cooking a chicken so that the heat wouldn't build up too much and that you could spread it around so uh do you have do you have thermal protection material on their engine and where is that located yeah that was the the pica-x tiles okay so the pkx tiles are only on there on the bottom of the vehicle they're not on the sides of the vehicle is that correct we are using the keep link it's used okay okay I think I understand now okay thanks I have two questions one how did you figure out how much water to use for radiation shielding so we going go ahead and answer that one things so when I wasn't researching the materials I found that I had to sacrifice the mass like the I had to use had to sacrifice the mass in order to get within the requirements of the competition so first I have wanted to go with the lead but the Knights do that that's fine yes so my final option was to try to research a lighter material and I stumbled upon water it was a as if there was a form that had calculations about how you can get it I can get it so that got to cosmic radiation can be about the same radiation as you experience on earth and I found that seven centimeters of water gave me half radiation have them their radiation going through okay good and secondly and maybe this is out of the scope but do you have something that could launch your payload your your spacecraft for a hundred and fourteen thousand kilograms is there a launcher capable of that did you address that in the plan for this project we were told we are entering the Martian sphere of influence with a speed of 3 kilometers per second so it was not given to us to include a launcher for this mission I like that in that I'm sure by the year 2026 we'll have heavier capabilities like the Space Launch System currently being developed by NASA or the VFR by SpaceX as you were considering the radiation shielding given that both that's water and it's really only of relevance for the route configuration did you think as to whether or not you could actually count that towards the useful payload that's being delivered by the vehicle we first thought we can count that for the 10 metric tons but then we instead realized that what if the water is not like you cannot use the water after it's been uses shield so we probably just ended up using it as its own separate mess a hundred and twenty billion dollars a lot of money it it's I'm just wondering if it struck you as curious that you came out with that number since that number is for instance about a hundred times as much as the cost of development to the Falcon Heavy that do wouldn't you suspect that maybe you made a math mistake well we did do the calculation numerous times and this is the answer we got however we would also like like to like to point out that this has been adjusted for inflation to the year 2026 and also the Apollo program when adjusted for inflation was also a hundred and twenty billion dollars so it is actually roughly extremely similar to the Apollo program in terms of cost and also like I have said when you divide this over eight years it's roughly fifteen billion dollars per year which which means that the NASA but overall budget every year has to rise only 0.6% which is last which is less than the NASA budget during the Apollo program which was 3% so this cost is actually very reasonable and accurate there any further questions all right thank you very much [Applause] this is the Polish team right hello everyone I am Justin and I have a pleasure to introduce your project Eagle team today me and my friends kacper critial Asha Miho and Anja with a little help Oh Ignacio and Carter will tell you a little bit more about our project we are a group of 16 students representing different fields of science mechanics electronics biologists material engineers and more we are part of student scientific association of road which focuses on space products polish space program is developing and we want to contribute to that for this reason we are decided to challenge ourselves in different kind of tasks like creating Mars Lander and to gain the experience in space projects for a reticle contest we recruited the whole new team which was managed by more experienced members of our association like me and Anna and it was quite a challenge compared to our previous projects because it requires more specialists acknowledged in fields of science who had no previous experience in we we started our work by dividing into two groups each of them had two months to prepare and design one concept of Mars Lander modular and one body we wanted to have different points of view to compare them and to choose the best one we had our meetings at least two times a week to keep the information flow to discuss the progress the problems to share the experience we gained and of course to avoid having to work after all we designed and checked more than 10 different Mars Landers concepts including the most craziest one like creating electromagnetic color shield so the last one we have pleasure to present to you today one of the most crucial part of our work was free good plan of work and my spoons we had to achieve in a specific time we had to use dedicated professional tools like for the modeling programs program stone Eliza's and break management programs to design and analyze our project as exact as we can we reached out specialists from professional institutions like ISA because with their help we could make make out best solutions and now Casper will tell you a little bit more about our Mars Lander so our final concept is the only body Mars Lander which uses two forms of deceleration the first one is our braking acceleration module which is basically hired and the second one our rocket engines to obtain the best volume size ratio we've decided to design our Lander as a cylinder with people to come on top and it's dimensions are eight point two meters in diameter and 15 meters in total height with an it weights the dry mass of our Lander is about 24 tonnes adding four tons of propellant and 10 tons of payload we are ending the total mass of 38 tons one of the crucial parts of designing a space vessel is to obtain the lowest possible overall mass without loss of necessary durability and to achieve this goal we decided to use stretched skin supporting structure construction as you can see on the screen and in this construction the mind string is carried on trust and the outer layer provides stability and isolate the insights of a rounder and of we want to be sure that this construction will meet its requirements so we've made several the finite elements analyzes so we could optimize the shape of the truss and the sizes of of the ribs and the main parts of the supporting structures are the square cross section of 50 by 50 millimeters ribs and plates going up through the whole cylinder as you can see and we also have a shallow going around the whole outer layer of our lander and the first part of our shell from the outside are the other side ties because we're using two forms of the scenario deceleration that it makes a lot of heat so we wanted to be sure that we have some thermal protection and those styles are applied on the same aluminum layer which covers a layer of an isolation foam and this isolation foam we have chosen BM 265 since they its properties are examined for now and and we've decided that it's the best option and that's all it that the foam is connected to the a carbon epoxy composite which which is connected to the outer layer of supporting structure which is made of aluminum alloy and I forget to mention that the whole supporting structure is made of titanium alloy and that's basically our engineering part in a nutshell thank you okay so now something about landing in order to reduce mass we decided to rely mainly on iron braking and our atmospheric deceleration module abbreviated IDM is based on the hypersonic inflatable aerodynamic decelerator currently in development by NASA the ADM consists of obviously two parts the inflatable structure 22 meters in diameter and the rigid nose housing called the necessary electronics and nitrogen tanks used for inflation we consider the use of the symmetrical higher but concluded that if the simple solution works there is no need for additional R&D costs costs the whole module is attached directly to the lenders legs with explosive bolts which eliminates need for an adapter which further reduces mass and after the aerobraking phase the module is detached and the part design phase begins okay so the problem with vengeance is that there is no engine continues or in development that would suit our needs you could use an engine like RD 58 that is kerosene and oxygen but this is not a good long-term solution if you want to meet missing that could could be produced on Mars so we decided to base our design on the 3d printed demonstrator engine currently in development by NASA the engines they said would use missing and oxygen mixture and operating a gas generator cycle the pretty printing technology allows for it allows reduced around the production costs the reaction control system is composed of a simple pressure fed trusters mainly for reliability reasons and to use the same propellants as the main engines our fuel tanks made from the woven carbon composite and are the central element of our unified fuel system that simplifies the construction reduces the overall lenders mass and probably allows for a more flexible mission profile our landing gear is responsible for three things obviously the safe touchdown acting as an adapter for the ADM and maintain enough room for the under the lander for the cargo bay to the lower the they are constructed in such a way that they could adapt to the Martian terrain the main energy dispersion dispersing elements is the honeycomb structure at the base of the legs in our lander we decided to implement convertible cargo unit and thanks to this we can use in both type of mission it's meant and unmanned mission so first of all our cargo bay is cuboid and its dimensions are 4 by 4 by 8 meters and after landing the cargo is being extracted on an elevator platform as you can see on the screen and the size of cargo which can be unload at once is 64 cubic meters in our design we create the opportunity to put the astronauts on board the lander however it's optional because in our opinion it will not be safe before before 2010 to 26 because available technology will not be advanced enough however we can however we can take the Irit last cargo bay and put it meant module inside and our lender can store a supplies for 10 months of mission for 4 astronauts on you you're right you can see how our life-support system looks like and it consists of for mine subsystem and its atmosphere revitalization subsystem water management subsystem heat transfer subsystem oxygen supply and product pressure control subsystem so first of all our water recovery subsystem it's partially closed loop which means that we can recover water from urine from cleaning and from air conditioning but not from deficit and the water is pumped back to the temperature control subsystem and utilized for cleaning purposes on board we have also for emergency tanks which can be used as a potable water for the astronauts to provide oxygen we we use dedicated generator and similar to other we have three tanks in case of emergency we have also filtration system to remove a contaminations bacteria from game and water from the air and to preliminary remove carbon dioxide and metabolic acid such methane benzene benzene ammonia etc we decided to use algae you would we we choose this dissolution because I'll just grow it's it's accessible source of micro and micro elements for the astronauts and the green color is proved to be relaxing for humans and according to this the walls in a site our lender have also bright colors so in our concept precooked food provide more than half daily energy requirements and we decided to add today it edible bags as a source of proteins and calories and as mentioned before algae as a source of vitamins micro and micro elements we choose two types of bugs and it's to be a cockroaches and hermit a Larry and her Mattia can be filled with plastic food packet can be filled with plastic food packaging and we can use them as a source of food for Dubai cockroaches and for the astronaut on this light you can see how our mint module looks like and the entire area of this module is 80 cubic meters and this module consists of two decks on the first deck we have insects breeding facilities sleeping compartment with two beds bathroom with a shower toilet workout equipment and food storage and on the upper deck we have computer subsystem seats and to storages the first one for a foot and the second one for equipment and now me how will tell you something more about electronics on board our Lander okay so we found that if we want to show a Phoenix design in our Lander we have to divide this power into the small problems as you can see we were managed to specify the following sections like the steering system guidance power management and supply and the communication while designing avionics in our Lander we took into consideration the previous Mars missions and the other both successful successful and those with ended with the fellow from which we learned the most power supply and storage so why solar panels seem to be a good choice for a spaceship we assumed that for our land there have to be a useful not just in space but on the Mars planet as well and therefore we decided to use advanced during radioisotope generators which can strengthen the whole construction of the lander and provide power supply for devices a srg is NASA technology that not only would supply lower the cost of the future Mars missions but also it can provide enough power for more emissions in one time for the navigation in space response the deep-space positioning system which allows us to determine exact position of the spaceship in the solar system and the deep space atomic clock is responsible for the accurate time measurements which are automatically synchronized which automatically synchronize received sent radio time signal and the separate part of the DPS are the micro star trackers and high sensitivity cameras which these devices can recognize stars and planets around the spacecraft and in the entry descent landing stage we decided to use a mus lidar radars and landing cameras of course each device with the proper redundancy ok and now our feature which is the printed electronics so the production of course are really low and the printed electronics could be thin and simultaneously flexible and present most of the censorious in the space industry it could be printed in this technology and it is said that to 2020 of necessary parts will be available and the advantage of this technology is that the astronauts can design and manufacture safely manufacture the new electronic boards in space or on the Mars planet and replace the damaged parts of the lander or create the new one or for the another devices okay so as for the organization of the mission the biggest challenge for us was probably the planning of the mission and creating the wholesome budget that's why we contacted specialists working for a European Space Agency and with his help we organized our workshops focus on managing a professional managing of such a big space endeavor and then we started with creating a risk analysis we felt about and written down every malfunction or accident that could occur at every stage of our mission and we also compared that to the solution we used previous in our design and make sure to include the new ideas into the final form to conclude the whole risk analysis we also scored malfunctions by its probability separately and probability to detect them and that's how we find out that the most crusher question of the risk that we listed would be for sure the electronic system failure and also the SLS not being ready on time and we could thought about the backup plans to reduce the risks then when after we included risk analyst outcome into our final design we moved on to the planning first we said it's a Power Lunch to December 2026 because as they're closest to the optimal window given the rules of the competition and then for the rest of the planning we used NASA's system engineering handbook because we had no experience in that kind of big space mission planning move it's how we managed to divide our mission into seven phases and the longest part would be the alignments manufacturing and also the final integration of the system taking place in the phase C and faced day together with the land in Phase II it would take about four years so that's that because amount of time we also stimulated the time for the flight and for the data that the collection of the analysis about a year each and then as for the budget we set the budget at around a billion dollars we base it on the assumption we base our assumptions on the other well-known missions that's because we didn't we couldn't acquire most of the cause of special technologies and also materials because they were simple classified especially for the foreigners then we also take into consideration the fact that for example the redundancy that we use for our life training systems would double some of the expenses but on the other hand it was also increased the safety of our mission on the other hand we decided to use as soon as possible of the new technologies because its implementation will cause us big time and it still could end in the failure with the failure and and we set our priority on the safety of the mission and use it of well known tested tested technologies so on the slides you can see there are presented the chart comparing amounts of funds used on every part of our mission the electronics and also the mission organization thank you we are glad we took on the task of designing to designing Mars Lander and that is that is capable to land on the surface of Mars with ten tons of payload we had amazing opportunity to learn new things in feats of science you had no previous experience in to gain the experience in space project and of course to talk to specialists from professional institution like ISA we are sure that we will use new skills in our future space projects and we hope that there will be more contests like this one because we are really proud of progress that we made in a short period of the time we like to thank thanks to all people engage in our project including specialists from sonoma's society post Condesa and of course we'd like to thank to all our sponsors because without their help we couldn't be here to present our work so high-five perché work and that's all thank you for your attention I hope you enjoy it right we have a good amount of time for questions so I'll just start off so first of all I just like you to review for me the mission sequence you know how you get from interplanetary trajectory to the surface of Mars and the other question I had was at one point I believe you said that the aeroshell the inflatable aeroshell was 22 meters in diameter and that the lander itself was 15 meters tall yet in the artwork that you showed it seemed like they were almost the same size but maybe I'm wrong about that but anyway if you could clarify the mission sequence and also did you do any analysis showing that the hot wake from the aeroshell would miss the lander but considering the competition rules we had to think about humans first and so our physicist calculated that we should first of all use either I or capture or enter the circular orbit by the by using the orbital engines which are part of the RCS system and from that we would start the proper aerobraking count so tell the story what did you how does it go explain it in the meantime um given that you have a nearly full propellant tank on top of a structure that's almost as tall as it is wide with a Hyatt at the front how confident are you that this structure is aerodynamically stable comes to part of the sound I think it should be fine the plan is to acquire the or circular orbit around Mars mainly by by using the orbital engines and after that we will try to enter the atmosphere so okay so just walk me through it you're coming to Mars interplanetary trajectory and you're capturing into orbit using rocket proposal is that correct or are you using the arrow break are you arrow capturing or rocket capturing well actually both know the plans to use air breaking for so your arrow breaking into your arrow capturing into Mars orbit yes and then you are then after that you're coming and use the aeroshell to slow down and then rocket still a it yes all right that back just clarifies my question and then the question about the weather the hot wake from you know that's coming around the side of the aeroshell does it hit the the lander or not well protection on the side of the lander because the wake will will hit it okay got it can you tell me again I'm sorry can you tell me again the total cost I was trying to add up the numbers real quick but what was the total thank you good if you can pull up something where you can see the landing legs okay and in part maybe one with the each Hilden then you also have the one landed when there they catch the heat shield like that did you talk a little bit about how you would deploy the heat shield aerodynamic decelerator relative to the vehicle and then right so that's the leg deployment how do you get rid of the aerodynamic decelerator inflatable in the meantime the and the part descent begins okay and then in terms of landing gear did you look at tangential loads so the vehicle is moving sideways the legs okay I think there was also a comment in the Power Systems about with the ASR G something about it strengthening the structure well in part I wanted to know if I understood what you said for the advanced Stirling radioisotope generator I thought you made some comment about the structure I was just wondering what that was this is the energy the strongest because we hide them in the lander so when we cut the solar furnace we do something with them in this place before the landing and that was from okay okay see I've got two questions how bad was the power requirement to keep the methane and oxygen liquid on your way to Mars is that a major impact to your power budget okay so we do all the calculations but so the is about 26% of the efficiency and energy is the heat and we wanted just passive going to do the passive going of it and okay I also have a question about there's something about a length of mission of 10 months was at only 10 months on the surface that you were gonna support the crew the calculation and because of the area of our Lander is limited so the area for food and any other equipment it's also limited and according to this so we get the tents mission is the best option because we can search for food for for more than 10 mission also water and oxygen if we want to have some readiness like this tanks with water and with oxygen and also because we're thinking about mission longer than 10 months it's good to have to produce food on board not like us using cockroaches or something like that but some plants and the again area of our lender is too small to do this and we don't didn't don't have equipment to do this on Mars surface so the tents 10 months of mission looks like the best option for us and because of also because of psychological reasons because we have something about six months of trip from Earth to Mars and I get it from Mars to to art another under six months and on the service surface 10 was it and it's actually almost two years of mission and it's actually we didn't have any information about how our body can change during so that long missions it's the so I when we see my sauce you might all these things we decided to with the say that ten months is death the maximal option for this mission and I is it I'm understanding your reasoning but mine also my understanding is it takes six months to get to Mars and the best and then you have to wait a year and a half or 18 months before you can come back so the requirement this that's if very well thanks one more question I apologize if I missed it in the presentation but did you give a total mass for your vehicle yes the total mass was and 38 tons thank you wet and loose payload 24 times what are the triangles at the bottom of the landing legs for these triangles the thing is that our first idea to attach the IDN to the legs was to use the clamps at the end of legs and our friend that was responsible for the legs they forget forgot to remove them from the final yes okay you have the the the rather large aeroshell what speed does that aeroshell get you down to before you drop it and then your propulsive after that Mach two and then you power off of it and enter land from there and you know what altitude that occurs in alright thank you any other questions from the judges alright then thank you very much okay