[Music] [Music] good morning friends welcome to this course on design of fixed Wing UAV I'm suban sadara instructor for this course and uh here we have two of two of our T Mr deep parik and Mr salahudin Kazi they'll be helping us in solving the assignments and and whatever doubts you have you can mail them they'll be helping you yeah okay thank you thank you being the part of this course so right now we heard that registration has clicked uh clicked about 2500 uh now we can no more assume the students who have registered in this course have the have performed the prerequisite so we have to redesign the course course content in such a way that even a fresher uh a student who is out of this uh aerospace engineering should be able to understand whatever we are going to discuss in this lectures so let's look at what are we going to discuss in this course so we'll start with some basic introduction right first few lectures we'll cover the introduction about uavs and their classification and then some brief anotomy of aircraft followed by this we discuss about some basic aerodynamics and then aerodynamic characteristics [Applause] of wing sections and also aerodynamic characteristics of finite things and we'll also talk about what is aerodynamic Center which is very important for us one of the important variable and center of [Applause] pressure and their relationship [Applause] relationship between aerodynamic Center and center of pressure so we'll also discuss about what is lift drag which is in fact the drag polar and some concepts related to flight path angle right followed by this we look at how to measure the velocity during flight subsequently the standard atmosphere [Applause] [Applause] [Music] right these are the some of the introductory Concepts that we'll cover and then we look at some of the basic uh prerequisites of this course that relates to Performance uh performance characteristics this includes study about study or analysis about level flight level flight such as uh we'll talk about thrust requirement [Applause] and power requirement and [Applause] range endurance and then LBD wing loing and thrust load right so we use these Concepts to figure out what should be the weight of the fuel or the battery that you would like to carry to perform a particular Mission how do we get to know by understanding what is the thrust requirement of the system to to perform or to execute that particular mission uh from which we can also identify since most likely we'll be uh talking about propeller driven aircraft or a UAV is here right so we have to talk in terms of the power requirement right so whether which kind of propulsion system should I select the answer for me I mean the answer that I get is by performing this performance analysis right so l byd w by S yeah [Applause] and we'll also look at clim performance where we talk about rate of [Applause] climb rate of climb and angle of climb say what limits your rate of climb or what limits your angle of climb no for the design that you're going to do what are the parameter that limits your rate of climb and angle of climb so if we have to know then we have to perform this and we have to study this clim performance right so we'll look at both uh study rate of clim as well as accelerated rate of clim right and the third chapter will be uh will be about more or like you can say analytical estimation where you talk about various stability and control derivatives of the system right so analytical estimation so the main emphasis is how to design a system which is stable by itself without any add-on like control system right how do you make the system stable by itself during its flight right so if you here we start we talk about static stability so start with equilibrium static stability [Applause] conditions to satisfy that uh and then so there are two F two Case Case case studies one is about longitudinal static stability and the second part is about lateral static stability so in longitudinal static stability you'll talk about which what should be the size of the wing for example or what should be the wing and tail size right so how far they should be a part for a stable flight right again when we say Wing tail fusel and all these things in propulsion system each carries a weight right so there exist a CG for this entire system once you assemble it you know uh you'll you'll figure out a CG location right so where does this CG CG location should be what are the limitations of this CG travel so we'll also look for most forward it's like constraints on CG location right right F CG locations locations for stable flight again so this the all these conditions are for meant for a stable flight okay and we'll also look at like how how big should be your elevator or the control surface right if you have if you want to control your aircraft how big should be your elevator does that sizing involve the distance between wing and tail or this CG plays any role in that sizing of this elevator so we'll address this questions while performing this sizing of control [Applause] surface so sizing of control surface like uh how how the sizing can be performed and what is the role of this CG location as well as the distance between wing and tail when I say the distance between wing and tail we broadly talk in terms of distance between the aerodynamic centers of these two components right so once we do this control surface sizing and at the same time the distances are fixed then we need to understand what is the range of angle of attacks yeah range of angle of attacks for which the aircraft can be trimmed for so we'll look at that possible range to trim so when we say possible range to them it talks about control surface deflections possible control surface face deflection okay at the same time for lateral directional case we'll perform vertical tail [Applause] sizing right which are mainly governed by means of some lateral directional uh parameters stability and control parameters right so so we have to design such a way that uh the vehicle should be able to uh come back to its equilibrium Whenever there is a disturbance in lateral directional case and then vertical tail sizing R sizing rder is a control surface that that is located on this vertical tail which is used for directional control yeah and then we'll uh proceed to talk about simulation why do we need simulation right so whatever you have designed you have to translate since you may not be before fabrication right see ultimately design what is the output of this design yeah what should be the output yes you should have some physical dimensions no ultimately you should have a planform geometry as well as the cross-sectional properties right and their respective locations with each other right let us say if you have you have designed the wing with a with a span with a cord right with a particular span and cord and you have a tail and you have located both of them so the output should be a geometry right now whether this geometry will in reality will fly or not or do we need to I mean is there a step that is involved before flying act flying the actual uh design right or the Prototype we can still do do that by means of simulation right so what do we do in simulation is like convert this physical model to mathematical domain right you translate to the mathematical domain and then you various inputs and see how the system behaves right if it have sufficient stability or whatever the disturbance that you give does it vanish with time or increases with time right all these things you can analyze before actually going for fabrication since we'll not be fabricating any design any model that we are going to design in this course let us concentrate on simulation we it is worth spending some time performing pering the simulation as well so what we do here is derive Sixt derive derivation of rigid body body equations of motion right so rigid body equations of motion are common but how can you simulate your design by using that rigid body equations of motion right so the answer is [Applause] modeling external forces and moments whatever the shape or whatever the design that you have performed I mean you you made will reflect in terms of external forces and moments called aerodynamic forces right forces and moments I call it as aerodynamic model here right this aerodynamic model will go as an input right so to this equations of motion and you use a numerical simulation some numerical algorithm numerical [Applause] integration [Applause] algorithm to solve the derived rigid body equations of motion which are which in general are in differential form right first order differential equations so numerical integration and then analysis right and finally now you actually start a design design methodology we'll take one or two case studies and we'll do the entire process like without understanding the performance and stability aspects of this we'll not be able to design a configuration uh if possible we'll also try to include some optimization here right so but this limits the scope of this particular course and yeah our TS will take you to the UAV as UAV laboratory here where there are few UAV models like and if possible we'll also include the flight test of those models during this course right yeah so you might have heard a general term called drone and what does how does it differ differ from an UAV right we should know that you more or less use drone and UAV for uh as a common right so we need to know what is the difference between them grown is also an unmined system like and which which is meant to perform a mission more more a pre-programmed mission right so that means it will not try it will not be able to send whatever data that he has it has acquired during that particular mission to the ground station station unless it come come back to its home right so it's like limited intelligence limited onboard intelligence right it is also an unmanned flight vehicle with [Applause] limited onboard intelligence and mostly designed to perform pre-program motions right whereas as most of you know the word UAV stands for unial [Applause] vehicle it's an unmat aial vehicle [Applause] of course there is no onboard pilot yes right so it is more controlled from the ground station or in an autonomous mode right but it it can communicate to ground station so when there exist a communication link you'll be able to change the mission whenever it is required right during the flight it it's like Dynamic Mission planning you can actually change the mission whenever it is required [Applause] better onward [Applause] intelligence and then it can also when I say it can communicate to the ground station it can update abouts the payload data as well as health health of the system right and the performance of the system so it can update details of update details for the data acquired acquired by onboard payload as well as data related to sensus health uh say health of the system and also the performance of the system right so in this course we'll talk about this uavs right so how can we classify this UAV there are many uavs right starting from 10 cm UAV to a 10 m UAV right in terms of span how to classify this UAV right first of all let us look at the mode of operation and how they are nomenclature right so uavs can be broadly classified into a fixed Wing based UAV fixed Wing based and rotary being based and a flapping Wing based as aess uh combination of f right combination of either of [Applause] this fixed Wing rotary Wing mostly a combination of fixed wing and rot can say hybrid UAV right okay flapping Wing or mostly also termed as onop right so where the aerodynamics is uh I mean the design is carried out by means of the aerodynamics associated with the insects flights and all right and birds so on so in case of rotary Wings again there are a single rotor and multi [Applause] rotor us so there are single rotor as well as multi-rotor based test bits right that you can develop uh under this rot ring uavs like so what we'll be talking about is fixed Wing U so the content that we have presented here is more of or less related to this fixed Wing you have to further narrow it down as we know fixed wing works well in the atmosphere right so we'll be more more Clos closely talking about an atmospheric flight [Applause] vehicle or atmospheric flight vehicle which in our case is an UAV design so we'll be talking about fixed Wing atmospheric UAV design so here this classification is made uh by means of principle of operation now let us look at uh the classification based upon the size and weight at the same time the mode of operation let's look at the classification of this uavs based upon their size and weight as well as their mode of operation right so the micro uavs uh there are four different classification five different classification right uh in in terms of L Dimension as well as weight of this uavs there are micro mini very small small medium and large right very small and mini they are more or less we can't we can't exactly differentiate them but here the micro uavs whose weight class Falls below like uh I mean the size is less than 10 cm uh whereas the very small will comes under anything between 30 to 50 cm and the small uavs will have a span of of5 to 2 m and medium size uavs will be of 5 to 10 m and the large size uavs are 20 to 50 m as high as 50 m right so these are some of these uavs which can be classified based upon this I mean there are few examples for it e e e e e and also there is a classification based upon its mode of operation so there is a tactical and comact UAV which will be used uh more in a dynamic sense uh those are more active they are used to drop the payloads and whatever the payload may be right it can be a warhead or anything so the these tactical and comact uavs are more more active in the sense and in this sense and there is a male UAV which is which is abbreviated for medium altitude long endurance UAV the and the hail high altitude long endurance UAV these two uavs are meant to perform surveillance and reconnaissance measures right so the High Altitude long endurance UAV will can have a range up to 4 40,000 km right and uh a medium altitude long endurance UAV can have a range up to yeah similar range but in at a lower altitude dear friends we are right now near the runway of this flight laboratory of iur so flight laboratory is in front of me uh as you can see this is a fix ring UAV uh 1.5 M Class the total uh overall takeoff weight is 1.6 uh CES and it was designed to have an endurance of 2 hours right now so uh let me introduce uh our chief test pilot right he is a test pilot for most of our configurations Mr navino and you know Mr deep again who's here so let's quickly have a flight test of this conf and uh this has been designed by us right and see how this design behaves right now so it's bit windy as you can see the model is almost waving here right so let us see how this performs in the Wind you can zoom that wind back bit Gusty this [Music] yeah yeah it's on zero throttle yeah it I am critical so you can witness a power of flight so the model is gliding and is able to sustain its weight because of this gust [Music] yeah land yeah yeah nice [Music] [Music]