8/2/2019 Design of Uav-2

1/16

DESIGN OF UAV-

2

Aarthi Shankaran 1802Abhishek Aggarwal 1804

Abhyudaya Saxena 1805

Neha Sharma 1828

8/2/2019 Design of Uav-2

2/16

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.

8/2/2019 Design of Uav-2

3/16

CLASSIFICATION BASED ON WING

CONFIGURATION

Fixed Wing

Rotary wing

Flapping

8/2/2019 Design of Uav-2

4/16

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

8/2/2019 Design of Uav-2

5/16

CLASSIFICATION BASED ON

PURPOSE

Target and decoy

Reconnaissance

Combat

Research and development

Civil and Commercial UAVs

8/2/2019 Design of Uav-2

6/16

PURPOSE

Surveilliance

Covert Operations

Search and Rescue

8/2/2019 Design of Uav-2

7/16

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

8/2/2019 Design of Uav-2

8/16

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

8/2/2019 Design of Uav-2

9/16

PAYLOAD ANALYSIS:

Engine 15kg

Camera 2kg

Avionics 2kgServo Actuators 2kg

Fuel tanks 4kg

Total weight = 25kg

8/2/2019 Design of Uav-2

10/16

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

8/2/2019 Design of Uav-2

11/16

8/2/2019 Design of Uav-2

12/16

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

8/2/2019 Design of Uav-2

13/16

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

8/2/2019 Design of Uav-2

14/16

8/2/2019 Design of Uav-2

15/16

8/2/2019 Design of Uav-2

16/16

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