Micro Air Vehicles Seminar1
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MICRO AIR VEHICLES
MOHAMED RINJU P M
S7M2
ROLL NO:27209
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WHAT ARE MAVS(QAV¶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.
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WHY MAV¶S? WHY NOT
SOMETHING BIGGER?
Keeps security personnel out of harms byproviding situational awareness right down toplatoon level.
Direct connectivity
Can be individually controlled
Can be used for a wide range of new
missions _ (even unthought-of before)
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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
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OVER THE HILL
RECONNAISSANCE
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MOTHER BIRD APPROACH
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Tracking of chemicals
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MAIN SUB SYSTEMS
1. FLIGHT CONTROL
2. PROPULSION SYSTEM
3. COMMUNICATION SYSTEM
4. GUIDANCE&NAVIGATION
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MAV flight regime compared with
existing flight vehicles
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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=J/power requirement
For optimal endurance the mav should fly at7°
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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
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WING DESIGN AND
FABRICATION
Types of wings
wing shapes Composite materials,
Carbon fibres
carbon fibre-balsawood sandwitches are commonly used
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Inflatable wing
Distend (fill) with air or gas
Application in UAV, military
To stow the wings
Can be launched from gun or aircraft
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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, anddecelerated in level flight.
High stability and control High lift and slow landing speed
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Experiment on inflatable wing
Experiment conductedusing I 2000
It was launched from
800-1000 feet Inflatable wings comes
out in 1\3 sec
Successfully controlled
the launch,flight andlanding
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Controlling of wing
by using piezoelectricby using piezoelectricmaterialmaterial
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actuator can be quartz and substrate can be
aluminum or steel
inflatable wings has smooth surface so low
value of skin friction
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I-2000 & X-24A
Both have inflatable
wing
I-2000 is UAV
X-24A is manned
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Disadvantages
They are not self powered
Cannot launch from ground
There are chances of air bag buckling
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PROPULSION SYSTEM
Propulsion system alone consumes 90% of totalpower
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
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COMMUNICATION SYSTEM
A video/still camera,
various sensors,
micro processors, Transducers
& an omni directional antennae
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GUIDANCE AND NAVIGATION
A combination of GPS+inertial sensing isideal
Geographical information system toprovide a map terrain for infrastructurewould be great
Pressure sensors
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MAV SYSTEM INTEGRATION
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REFERENCES
Research paper ³Death 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
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 ProjectsAgency
and Col. Michael S. Francis, USAF (Ret.) formerly of Defense Airborne Reconnaissance Office
MICRO AERIAL VEHICLE DEVELOPMENT: DESIGN, COMPONENTS, FABRICATION, ANDFLIGHT-TESTINGResearch 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
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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 TimSmith
ILC Dover, Frederica, DE 19946
Innovative Wing Design Could Soar in Martian Skies by benianntova
I nflatable 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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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. 223-239
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 http://defence-data.com/f2000/
pagefa1006.htm.
Air Force 2 ²A New Thrust in DERA Micro Air Vehicle Development,³ 24 July 2000, n.p.: On-line.
Int 0 25 , August 1996, n.p.; On-line. Internet, 18 December 2000, available from
http://www.au.af.mil/au/2025/index2.htm.
Air Force Doctrine Document (AFDD) 1, Air Force Basic Doctrine, September 1997. Air Force Scientific Advisory Board, N ew World Vistas Air and Space Power for the 21st
Century Summary Volume, 1995, n.p.; On-line. Internet, 4 December 2000, available
from http://www.sab.hq.af.mil/Archives/1995/NWV/vistas.htm.
Ashley, Steven, ²Palm-size Spy Plane,³ Mechanical Engineering , February 1998, n.p.;
On-line. Internet, 16 November 2000, available at http://www.memagazine.org/
backissues/february98/features/palmsize/palmsize.html.
Ashley, Steven, ²Turbines on a Dime,³ Mechanical Engineering , October 1997, n.p.; On-
line. Internet, 16 November 2000, available at http://www.memagazine.org/
backissues/october 97 /features/turbdime/ turbdime.html.
Barrows, Geoffrey L.,²Optic Flow Sensors for MAV Navigation,³ Proceedings of the
Conference on Fixed, Flapping and Rotary Vehicles at Very Low Reynolds N umbers,
5-7 June 2 000 , University of N otre Dame, ed. Thomas J. Mueller, 13 pages. Brendley, Keith W. and Randall Steeb, Military A pplications of Microelectromechanical
Systems, RAND Report MR-175-OSD/AF /A. Santa Monica, CA: RAND, 1993.
Carroll, Bruce,²MEMS for Micro Air Vehicles,³ Project Summaries, n.p.; On-line.
Internet, 24 August 2000, available from http://www.darpa.mil/MTO/MEMS/
Projects/individual_66.html.
Carroll, S.,²US Navy, DARPA Develop IMINT/EW Payloads for Mini-UAVs,³ Journal
of Electronic Defense 21, no. 9 (September 1998): 30-32.
Chandler, Jerome Greer, ²Micro Planes,³ Popular Science 252, no. 1 (January 1998): 54-
59.
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