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

2. WHAT ARE MAVS(AV’S)?
Multi functional, militarily capable, small flight vehicles.
size should be less than15cms.
Reynolds's no < 10^5.
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.
Direct connectivity
Can be individually controlled
Can be used for a wide range of new missions _ (even unthought-of before)

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

9. OVER THE HILL RECONNAISSANCE

10. MOTHER BIRD APPROACH

11. Tracking of chemicals

12. MAIN SUB SYSTEMS FLIGHT CONTROL PROPULSION SYSTEM COMMUNICATION SYSTEM
GUIDANCE&NAVIGATION

13. MAV flight regime compared with existing flight vehicles

14. FLIGHT CONTROL&AERODYNAMICS
Reynolds's no:= inertia force/viscous force
Low Reynolds's no: flights may have lift to drag ratio of 5 to 10.
The best aspect ratios usually lie between 1&2
Angle of attack should be 5-12° for good endurance.
If angle of attack <5, low aerodynamic efficiency
Endurance=/power requirement
For optimal endurance the mav should fly at7°

15. ACTIVE OR PASSIVE CONTROL
Use strategies using MEMS
Create &install tiny sensors
miniature actuators
Flow character controlled by sensor arrays
Flexible membranes or micro flaps to affect the flow as required
Micro motors piezoelectric devices magneto elastic ribbons

16. WING DESIGN AND FABRICATION
Types of wings
wing shapes
Composite materials,
Carbon fibres
carbon fibre-balsawood sand witches are commonly used

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

19. 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

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

21. Controlling of wing
by using piezoelectric material

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

23. I-2000 & X-24A
Both have inflatable wing
I-2000 is UAV
X-24A is manned

24. Disadvantages They are not self powered Cannot launch from ground
There are chances of air bag buckling

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

27. COMMUNICATION SYSTEM A video/still camera, various sensors,
micro processors,
Transducers
& an omni directional antennae

28. GUIDANCE AND NAVIGATION
A combination of GPS+inertial sensing is ideal
Geographical information system to provide a map terrain for infrastructure would be great
Pressure sensors

29. MAV SYSTEM INTEGRATION

30. 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
2. Davis, W.R., "Micro UAV," Presentation to 23rd Annual AUVSI Symposium, July, 1996.
Research paper by James M. McMichael Program Manager Defense Advanced Research Projects Agency
and
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
117 Hessert Center, University of Notre Dame
Notre Dame, IN 46556
DESIGN AND DEVELOPMENT OF A MICRO AIR VEHICLE
CONCEPT: PROJECT BIDULE
Mr T. Spoerry1, Dr K.C. Wong
School of Aerospace, Mechanical and Mechatronic Engineering
University of Sydney
NSW 2006

31. 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 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

32. BACK REFERENCES
Mueller, T. J., "Low Reynolds Number Vehicles", AGARDograph No. 288, 1985
Lissaman, P. B. S., "Low-Reynolds-Number Airfoils", Annual Review of Fluid Mechanics, Vol. 15, 1983, pp
Burgart, M., Miller, J., and Murphy, L., "Design of a Micro Air Vehicle for the 2000 MAV Competition", internal progress report, University of Notre Dame, 2000
ernet, 14 December 2000, available from
pagefa1006.htm.
Air Force 2—A New Thrust in DERA Micro Air Vehicle Development,“ 24 July 2000, n.p.: On-line.
Int 025, August 1996, n.p.; On-line. Internet, 18 December 2000, available from
Air Force Doctrine Document (AFDD) 1, Air Force Basic Doctrine, September 1997.
Air Force Scientific Advisory Board, New World Vistas Air and Space Power for the 21st
Century Summary Volume, 1995, n.p.; On-line. Internet, 4 December 2000, available
from
Ashley, Steven, —Palm-size Spy Plane,“ Mechanical Engineering, February 1998, n.p.;
On-line. Internet, 16 November 2000, available at
backissues/february98/features/palmsize/palmsize.html.
Ashley, Steven, —Turbines on a Dime,“ Mechanical Engineering, October 1997, n.p.; On-
line. Internet, 16 November 2000, available at
backissues/october97/features/turbdime/ turbdime.html.
Barrows, Geoffrey L., —Optic Flow Sensors for MAV Navigation,“ Proceedings of the
Conference on Fixed, Flapping and Rotary Vehicles at Very Low Reynolds Numbers,
5-7 June 2000, University of Notre Dame, ed. Thomas J. Mueller, 13 pages.
Brendley, Keith W. and Randall Steeb, Military Applications of Microelectromechanical
Systems, RAND Report MR-175-OSD/AF/A. Santa Monica, CA: RAND, 1993.
Carroll, Bruce, —MEMS for Micro Air Vehicles,“ Project Summaries, n.p.; On-line.
Internet, 24 August 2000, available from
Projects/individual_66.html.
Carroll, S., —US Navy, DARPA Develop IMINT/EW Payloads for Mini-UAVs,“ Journal
of Electronic Defense 21, no. 9 (September 1998):
Chandler, Jerome Greer, —Micro Planes,“ Popular Science 252, no. 1 (January 1998): 54-
59.