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High Altitude Long Endurance

Unmanned Aerial VehicleSattwik Suman Das

Shashank S

Tanveer Ali

AE 412: Aerospace Vehicle Design

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Requirements

Border patrol for 6400 sq.km.

Operational Ceiling-19.8 km (65000 ft)

Maximum speed-147 km/hr

Endurance-40 hours (Loiter)

Conventional Runway takeoff (Maximum 600m)

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Payload (maximum weight 113kg)

1. Synthetic Aperture Radar (SAR): Sandia Labs MiniSAR -14 kg

2. Electro-Optic-Infrared Sensor: 23 kg (APM UAV Payloads)

3. Data link: (l-3 communications) :1kg

Source:http://www.sandia.gov/RADAR/index.html

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Initial sizing

Weight fractions for the various operationalphases were computed*

Iteration using MATLAB

*Reference: Airplane Design by Jan Roskam

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Existing UAV data

UAV WTO (kg) WE (kg)RQ-1A Predator 2250 1150

RQ-2B Pioneer 452 304

Prowler 200 117

Gnat 750 1126 560

Heron 2425 1323Kentron RPV-2 529 323

Shadow 200 316 200

Shadow 600 584 327

Raptor-low 1880 810

Vixen 200 140Exdrone 91 71

Freewing 383 253

RQ-5A Hunter 1600 1190

E-Hunter 2100 1430

Hermes 450 992 441

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Weight is found to be 1800 kg

ln(WE)

ln(W

TO)

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Airfoil selection

Criterion:

1. Maximum Lift Coefficient

2. Aerodynamic efficiency

3. Off design aerodynamic characteristics

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Databases Used

David LednicersThe Incomplete guide to AirfoilUsage

UIUC Airfoil Co-ordinates Database

Program Used

Martin Hepperles JAVAFOIL

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Airfoils considered

NACA 5 digit 63 series and 23 series

NASA General Aviation airfoil series

Selected airfoil: NACA 23015

Source: Airfoil Investigation Database

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Wing Design Low/mid wing

No sweep back Fowler flaps

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Constraint analysis

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Constraint analysis, Contd

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Roadblock

We get Power required as over 200 hp

IC engines cannot be used

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Solution?

Turboprop

Pratt and Whitney Canada PT 6A

Source: http://www.pwc.ca/en/engines/pt6a

http://www.pwc.ca/en/engines/pt6ahttp://www.pwc.ca/en/engines/pt6ahttp://www.pwc.ca/en/engines/pt6ahttp://www.pwc.ca/en/engines/pt6ahttp://www.pwc.ca/en/engines/pt6a

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Initial sizing II

Using DARCORPs Advanced Aircraft Analysisv2.5

Weight of the UAV is obtained as weight of theUAV as 1579.15 kg

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Tail Sizing

Tails Considered:i. H Tail

ii. V Tail

Why V Tail?

Image Courtesy: https://www.tu-

braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefa

Typical H Tail

Typical V Tail

https://www.tu-braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefahttps://www.tu-braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefahttps://www.tu-braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefahttps://www.tu-braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefahttps://www.tu-braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefahttps://www.tu-braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefahttps://www.tu-braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefahttps://www.tu-braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefahttps://www.tu-braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefahttps://www.tu-braunschweig.de/ism/forschung/ag-flzg/projekte-alt/nefa

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Landing Gear: Tire sizing

We have used Raymers statistical method Assumption: Front tires carry 10 % of the aircrafts weight

and back tires carry the remaining 90%

25+7 % margin

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Configuration and layout

Pusher configuration:

i. Frees up the nose of the aircraft, which allows thepayloads to be placed in the front part of the fuselage.

ii. Reduces the skin friction drag because the pusher

location allows the aircraft to fly in undisturbed air.iii. Allows a reduction in the aircraft wetted area by

shortening the fuselage.

Propeller diameter 2.3m

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Disadvantages of Pusher configuration

The propeller has a reduced efficiency because it isforced to work with the disturbed airflow from fuselage,wing and tails.

It requires a longer landing gear because the aft location

causes the propeller to dip closer to the runway as thenose is lifted for take-off.

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Layout

Fuel tanks are inside the wings

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Refined sizing

We use Raymers formula for a turbopropaircraft

From refined sizing, we have the take-off weightas 1547.889 kg.

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Material selection

Fuselage: Composites inspired by Predator Wing skin: Al 2024 alloy clad with Zinc alloy forcorrosion resistance

Why?

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Weight estimation

With Reserve fuel fraction of 5%

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CG estimation

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3d views using Google Sketchup 8

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Future Prospects

Limited Variable Configuration

Longer Range

Additional Payloads

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Thank You