1. MICRO AIR VEHICLES MOHAMED RINJU P M S7M2 ROLL NO:27209

2. WHAT ARE MAVS(  AV’S)? Multi functional, militarily capable, small flight vehicles. Multi functional, militarily capable, small flight vehicles. size should be less than15cms. size should be less than15cms. Reynold’s no < 10^5. Reynold’s no < 10^5. For a Primarily intended and developed for defence applications. For a Primarily intended and developed for defence applications.

7. WHY MAV’S? WHY NOT SOMETHING BIGGER? Keeps security personnel out of harms by providing situational awareness right down to platoon level. Keeps security personnel out of harms by providing situational awareness right down to platoon level. Direct connectivity Direct connectivity Can be individually controlled Can be individually controlled Can be used for a wide range of new missions _ (even unthought before  ) Can be used for a wide range of new missions _ (even unthought before  )

8. APPLICATIONS Reconnaissance Reconnaissance Surveillance Surveillance Defence applications Defence applications Weather forecast Weather forecast Wildlife study &photography Wildlife study &photography Crowd control Crowd control Targetting Targetting Border surveillance Border surveillance Traffic monitoring Traffic monitoring Tracking criminals & illegal activities Tracking criminals & illegal activities Biochemical sensing Biochemical sensing Sesmic detection Sesmic detection inspection of pipes inspection of pipes

9. OVER THE HILL RECONNAISSANCE

10. MOTHER BIRD APPROACH

11. MAIN SUB SYSTEMS 1. FLIGHT CONTROL 2. PROPULSION SYSTEM 3. COMMUNICATION SYSTEM 4. GUIDANCE&NAVIGATION

12. FLIGHT CONTROL&AERODYNAMICS Completely different aerodynamics due to low Reynold’s number Completely different aerodynamics due to low Reynold’s number Reynold’s no:= inertia force/viscous force Reynold’s no:= inertia force/viscous force Here viscous forces dominate while at high Reynold’s no:’s inertia forces dominate Here viscous forces dominate while at high Reynold’s no:’s inertia forces dominate Reynold’s no:=  c/  Reynold’s no:=  c/  Low reynold’s no: flights may have lift to drag ratioof 5 to 10(conventional flights have these ratios 3 to 4 times higher) Low reynold’s no: flights may have lift to drag ratioof 5 to 10(conventional flights have these ratios 3 to 4 times higher)

13. MAV flight regime compared with existing flight vehicles

14. Due to small size it needs to have high surface to volume ratios to generate the required thrust Due to small size it needs to have high surface to volume ratios to generate the required thrust Aspect ratio=WS/chord length,or WS²/total wing area Aspect ratio=WS/chord length,or WS²/total wing area Exact ratio depends upon the total weight Exact ratio depends upon the total weight The best aspect ratios usually lie between 1&2 The best aspect ratios usually lie between 1&2 Stability and control issues related to low weight,small moment of inertia,wind gusts also needs to be addressed Stability and control issues related to low weight,small moment of inertia,wind gusts also needs to be addressed

16. ANGLE OF ATTACK AND WING DESIGN Angle of attack shoud be 5-12° for good endurance. Angle of attack shoud be 5-12° for good endurance. If angle of attack <5, low aerodynamic efficiency If angle of attack <5, low aerodynamic efficiency Endurance=  /powerequirement Endurance=  /powerequirement For optimal endurance the mav shoud fly at7° For optimal endurance the mav shoud fly at7° Hysterisis may occur (lift to drag ratio different from normalwhen angle of attack differs) Hysterisis may occur (lift to drag ratio different from normalwhen angle of attack differs)

17. ACTIVE OR PASSIVE CONTROL Use strategies using MEMS to improve aero dynamic perfomance Use strategies using MEMS to improve aero dynamic perfomance Create &install tiny sensors to dynamically adjust camber(curvature)and shape depending on instantaneous conditions Create &install tiny sensors to dynamically adjust camber(curvature)and shape depending on instantaneous conditions miniature actuators can be used to move the control surfaces like rudders ailerons and flaps miniature actuators can be used to move the control surfaces like rudders ailerons and flaps Flow character over the wings could be controlled by sensor arrays that detect shear stresses or fluid vortices Flow character over the wings could be controlled by sensor arrays that detect shear stresses or fluid vortices Flexible mebranes or micro flaps to affect the flow as required Flexible mebranes or micro flaps to affect the flow as required

18. Flow seperation an be mitigated by air sution or absorption as required,(requires micro valve or pump),wallheat transfer or electro magnetic force as required Flow seperation an be mitigated by air sution or absorption as required,(requires micro valve or pump),wallheat transfer or electro magnetic force as required Exhausted air is directed out of the trailing edge to prevent flow seperation,which also inreases lift Exhausted air is directed out of the trailing edge to prevent flow seperation,which also inreases lift Micro motors piezoelectricdevices magneto elastic ribbons are all alternatives for performing the actuator function in a flight control system Micro motors piezoelectricdevices magneto elastic ribbons are all alternatives for performing the actuator function in a flight control system Processing these control systems may require soft computational techniques like fuzzy logic,neutral networks,genetical algorithms or knowledge based systems Processing these control systems may require soft computational techniques like fuzzy logic,neutral networks,genetical algorithms or knowledge based systems

19. WING DESIGN AND FABRICATION Rotary wings, fixed wings, or alternate flapping& gliding wings could be employed Rotary wings, fixed wings, or alternate flapping& gliding wings could be employed Wing shape could be circular, elliptical, rectangular, Zimmerman or inverse Zimmerman Wing shape could be circular, elliptical, rectangular, Zimmerman or inverse Zimmerman Flapping &gliding and inverse Zimmerman proved to be most efficient Flapping &gliding and inverse Zimmerman proved to be most efficient Wing type depends on requirement Wing type depends on requirement Composite materials,carbon fibre cloth strips, carbon fibre-balsawood sand witches are commonly used Composite materials,carbon fibre cloth strips, carbon fibre-balsawood sand witches are commonly used Single or double layer of carbon fibre cloth wetted with epoxy resin Single or double layer of carbon fibre cloth wetted with epoxy resin Balsa wood for frame and carbon fibre glass cloth for reinforcing critical areas like leading edges and wing tips is a super combination Balsa wood for frame and carbon fibre glass cloth for reinforcing critical areas like leading edges and wing tips is a super combination

21. Inflatable wing  Distend (fill) with air or gas  Application in UAV, military  To stow the wings  Can be launched from gun or aircraft

22. Advantages of aircrafts with inflatable wings  Can be packed to 1/10 of original size  Low mass  Low power requirements  High reusability  It can be steered, accelerated, and decelerated in level flight.  High stability and control  High lift and slow landing speed

23. Experiment on inflatable wing  Experiment conducted using I 2000  It was launched from 800-1000 feet  Inflatable wings comes out in 1\3 sec  Successfully controlled the launch,flight and landing

24. Controlling of wing by using piezoelectric material  by using piezoelectric material

25.   actuator can be quartz and substrate can be aluminum or steel   inflatable wings has smooth surface so low value of skin friction

26. PROPULSION SYSTEM Propulsion system alone consumes 90% of total power Propulsion system alone consumes 90% of total power Lithium alkaline batteries Lithium alkaline batteries IC engines IC engines Pulse jet engines Pulse jet engines Micro jets Micro jets Reciprocating chemical muscle Reciprocating chemical muscle Self consuming system Self consuming system Lithium battery that recharges using solar energy and fuel cells are also future prospects Lithium battery that recharges using solar energy and fuel cells are also future prospects

27. COMMUNICATION SYSTEM A video/still camera, various sensors,a micro processor, transducers& an omni directional antennae are the major components A video/still camera, various sensors,a micro processor, transducers& an omni directional antennae are the major components Challenges are small antennae, restriction of power available Challenges are small antennae, restriction of power available Based on the application either cellular communication or satellite communication could be employed. Based on the application either cellular communication or satellite communication could be employed. CCD cameras and IR sensors, nuclear, biological or chemical agent sensors, acoustic sensors could be used. CCD cameras and IR sensors, nuclear, biological or chemical agent sensors, acoustic sensors could be used.

28. GUIDANCE AND NAVIGATION Completely autonomous navigation system needs to have the ability to use sensory data for on board processing thus avoiding obstacles. (complete dependence on remote is undesirable) Completely autonomous navigation system needs to have the ability to use sensory data for on board processing thus avoiding obstacles. (complete dependence on remote is undesirable) A combination of GPS+inertial sensing is ideal A combination of GPS+inertial sensing is ideal Geographical information system to provide a map terrain for infrastructure would be great Geographical information system to provide a map terrain for infrastructure would be great Pressure sensors acting as altimeters, accelerometers, low drift gyroscopes and also systems capable of locating the mav ’s position with respect to the launch point form a part of the inertial navigation system Pressure sensors acting as altimeters, accelerometers, low drift gyroscopes and also systems capable of locating the mav ’s position with respect to the launch point form a part of the inertial navigation system

29. MAV SYSTEM INTEGRATION

30. CONCLUSION Micro Air Vehicles are a class of UAVs whose time has just about come. A confluence of key events is about to occur that will enable these versatile aircraft to have military effects disproportionate to their diminutive size. The supporting technologies are progressing rapidly to the point that first simple, short-duration missions will be possible, then with time, more varied and enduring applications. At the same time, the need for weapons that help achieve the Joint Chief of Staff vision for dominant maneuvering precision engagement, full dimensional protection, and focused logistics will be more pressing than ever. The military utility of MAVs in this context can only grow as they come closer to realizing their potential. At the start, microairvehicles could find application by providing localized imaging reconnaissance. Then as other key technologies mature, uses may expand to electronic warfare, nuclear, biological, and chemical agent warning, and battle damage assessment. Later still, we could see MAVs autonomously flying through air shafts reconnoitering deeply buried bunkers and reporting back to enable proper configuration of penetrating weapons. MAVs might then proliferate throughout the force structure becoming as much an — arrow in the quiver“ of the foot soldier as another round on the hardpoint of a fighter‘s wing. Micro Air Vehicles are a class of UAVs whose time has just about come. A confluence of key events is about to occur that will enable these versatile aircraft to have military effects disproportionate to their diminutive size. The supporting technologies are progressing rapidly to the point that first simple, short-duration missions will be possible, then with time, more varied and enduring applications. At the same time, the need for weapons that help achieve the Joint Chief of Staff vision for dominant maneuvering precision engagement, full dimensional protection, and focused logistics will be more pressing than ever. The military utility of MAVs in this context can only grow as they come closer to realizing their potential. At the start, microairvehicles could find application by providing localized imaging reconnaissance. Then as other key technologies mature, uses may expand to electronic warfare, nuclear, biological, and chemical agent warning, and battle damage assessment. Later still, we could see MAVs autonomously flying through air shafts reconnoitering deeply buried bunkers and reporting back to enable proper configuration of penetrating weapons. MAVs might then proliferate throughout the force structure becoming as much an — arrow in the quiver“ of the foot soldier as another round on the hardpoint of a fighter‘s wing.

31. REFERENCES Research paper “Death by a thousand cuts”micro air vehicles in the service of air force missions- by ARTHUR F HUBER,II LT COL USAF Research paper “Death by a thousand cuts”micro air vehicles in the service of air force missions- by ARTHUR F HUBER,II LT COL USAF http://mil.ufl.edu/~nechyba http://mil.ufl.edu/~nechybahttp://mil.ufl.edu/~nechyba 2. Davis, W.R., "Micro UAV," Presentation to 23rd Annual AUVSI Symposium, 15-19 July, 1996. 2. Davis, W.R., "Micro UAV," Presentation to 23rd Annual AUVSI Symposium, 15-19 July, 1996. Research paper by James M. McMichael Program Manager Defense Advanced Research Projects Agency Research paper by James M. McMichael Program Manager Defense Advanced Research Projects Agency and and Col. Michael S. Francis, USAF (Ret.) formerly of Defense Airborne Reconnaissance Office Col. Michael S. Francis, USAF (Ret.) formerly of Defense Airborne Reconnaissance Office MICRO AERIAL VEHICLE DEVELOPMENT: DESIGN, COMPONENTS, FABRICATION, AND FLIGHT-TESTING Research paper by Gabriel Torres and Thomas J. Mueller MICRO AERIAL VEHICLE DEVELOPMENT: DESIGN, COMPONENTS, FABRICATION, AND FLIGHT-TESTING Research paper by Gabriel Torres and Thomas J. Mueller 117 Hessert Center, University of Notre Dame 117 Hessert Center, University of Notre Dame Notre Dame, IN 46556 Notre Dame, IN 46556 DESIGN AND DEVELOPMENT OF A MICRO AIR VEHICLE DESIGN AND DEVELOPMENT OF A MICRO AIR VEHICLE CONCEPT: PROJECT BIDULE CONCEPT: PROJECT BIDULE Mr T. Spoerry1, Dr K.C. Wong Mr T. Spoerry1, Dr K.C. Wong School of Aerospace, Mechanical and Mechatronic Engineering School of Aerospace, Mechanical and Mechatronic Engineering University of Sydney University of Sydney NSW 2006 NSW 2006

32.  Aerodynamics for engineers:-John J. Bertin  Mechanics of flight :-A.C Kermode  Inflatable wing on aircraft article :-new scientist june 2001   www. nasa explores. COM\aerodynamics\inflatable wing  Miller, Jay,, The X-Planes, Aero fax, Arlington, Texas, 1988  morphing of inflatable wing for UAV  morphing of inflatable wing for UAV David Cardigan* and Tim Smith†   ILC Dover, Frederica, DE 19946   Innovative Wing Design Could Soar in Martian Skies by benianntova   Inflatable wing for high lift john H gleen research centre Ohio   www.nastech.com/mechtech   www.spaceref.com/newtech   www.nasa.gov/aerodynamics  www.nasa.gov/multimeadia

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