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8/2/2019 Design of Uav-2
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DESIGN OF UAV-
2
Aarthi Shankaran 1802Abhishek Aggarwal 1804
Abhyudaya Saxena 1805
Neha Sharma 1828
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WHAT IS A UAV?
The UAV is an acronym for Unmanned Aerial Vehicle, which is
an aircraft with no pilot on board. UAVs can be remotecontrolled aircraft (e.g. flown by a pilot at a ground control
station) or can fly autonomously based on pre-programmed
flight plans or more complex dynamic automation systems.
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CLASSIFICATION BASED ON WING
CONFIGURATION
Fixed Wing
Rotary wing
Flapping
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CLASSIFICATION BASED ON
RANGE/ALTITUDE
Handheld 2km
Close 100km range
Tactical 100-300km
range
MALE (medium altitude, long endurance) 500km
HALE (high altitude, long endurance) >3000 km
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CLASSIFICATION BASED ON
PURPOSE
Target and decoy
Reconnaissance
Combat
Research and development
Civil and Commercial UAVs
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PURPOSE
Surveilliance
Covert Operations
Search and Rescue
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SPECIFICATION
Endurance : 8-10 hours
Payloads : Optical Sensors,
Thermal camera ,highresolution camera,
GPS, Autopilot, L-Band
transceiver (SATCOM)
Data transmission range : 300km
Cruise speed : 110km/h
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SPECIFICATION AND CHALLENGES:
Take-off and landing : HTOL or bungee launchmechanism , normal landing(parachute recovery).
Wing span : 3m
Propulsion : Piston prop engine
Airframe : Easy repairable,Detachable parts
Camera system : Camera lens in nosesection
Operation : One to Two men operable
Mission altitude : 7000m from the sea level
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PAYLOAD ANALYSIS:
Engine 15kg
Camera 2kg
Avionics 2kgServo Actuators 2kg
Fuel tanks 4kg
Total weight = 25kg
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WEIGHT ESTIMATION
Wo =Wstructure +Wpayload +Wengine +Wavionics +Wfuel
Fora given vehicle, the structure is a fraction of the total weight,typically somewhere between 0.25 to 0.35 (but can be as high as 0.75).
Thus, combining and rearranging
Wo = Wpayload +Wfuel +Wengine +Wavionics/1-X
Fora given payload and engine (with assumed fuel use and time offlight), TOW can be estimated
GTOW =Wo =Wstructure +Wpayload +Wfuel +Wengine +Wavionics
Wstructure = XWo
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CONTINUED
Taxing W1/W0=0.997
Take Off W2/W1=0.9985
Climb W3/W2=0.98
Cruising W4/W3=0.6622
Descent W5/W4=0.9867
Landing W6/W5=0.9928
Mff=0.5896
Wf/W0=(1-Mff)1.06=0.435
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CONTINUED
W0=Wpl/(1-Wf/W0-We/W0)
We/Wo =0.42 (as per analysis of Similar UAVs)
W0=172 kg
L=0.5 rho v^2 S.Cl
Comes out to be
Cl= (cruising)
Ar=7.5 (assumption from various data of uav) Span(b) limited to 3m
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FUTURE PROSPECT:
Wing design: wing sweep
wing anhydral
wing twist
structural analysis: material selection:
V-n diagram:
take off and landing performance:
communication system:
control system: auto pilot