Nessun titolo diapositiva...VSAERO software, obtaining very high efficiency. • Showed feasibility of very light CFRP structural elements. • Good correspondence between experimental

Prof. Ing. Giulio ROMEO, E. Cestino, F. Danzi, M. Cassaro, G. Frulla, F. Borello, G. Correa, G. Corsino, M. Pacino,

Politecnico di Torino

Dept. of Mechanical and Aerospace Eng.

HELIPLAT®:

Detail Design & Manufacturing of a Scaled Prototype for High

Altitude Very-Long Endurance Solar-Powered RPAS

DIMEAS

[email protected]

All information on Heliplat and VESPAS project contained in this document is property of Prof. G.

Romeo, Dept. of Mechanical & Aerospace Eng. - Politecnico Torino. All rights reserved.

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A.S.I. (1995-2000) EC: 5FP (2000-03)- 6FP (2002-05)

•High Altitude (15-20km) Very-long Endurance Solar Powered Autonomous Stratospheric RPAS (VESPAS) flying for long period of time (4-6 months) by solar-power & fuel cells system. Easily recovered for maintenance.

•Pseudo satellites, with advantage of being much cheaper, closeness to the ground (more detailed land vision), more flexible, with continuous spatial resolution than a real satellite.

• 8-9 HeliPlat would continuously monitor Med Sea from Turkey to Spain. An area with 300km diameter can be monitored.

• Many other applications can be foreseen by such platforms.

NETwork of HELIplat RPAS HELIPLAT

G. Romeo G. Romeo

DIMEAS

3

Borders Patrol, actually, is made by piloted airplanes or helicopters (several personal) or from military ships, increasing the cost tremendously.

Costs sustained by Italian Coast Guard for their ATR-42 airplane equipped for border surveillance (7 crew minimum), is around 7.500-8.000 €/hour of fly.

By UAV flying at 15-18 km altitude and with proper sensors, is possible to detect boat or people and with Total Life Cycle Cost of around 2.000€/hour fly

Homeland Security – Airborne or Ground Sensors

HELIPLAT

IAI Predator B

Typically, satellite sensors may bring a good accuracy - but such high accuracy data remain quite expansive today.

Several satellites system used for earth observation are useless for a continuously real-time border surveillance due to their limited spatial resolution.

Satellite Earth Observation

DIMEAS

POLITO, DIMEAS, [email protected]

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Homeland Security – DARPA Boeing $100 million contract

HELIPLAT DIMEAS

Facebook & Google: Solara Titan Aerospace

AIRBUS D&S – Qinetiq Zephir 7

14days @ 70,740ft

TOGW 100kg, Pl: 5kg

Solar Impulse 2

A

A

A

A

A

A

A

A

CRITICAL ASPECT: ENDURANCE & STATION KEEPING

HELIPLAT

• Main requirement: Avoid interference with civil transport traffic

• Main advantage of the VESPAS-RPA: less climb and descend events; important for interference with the aviation traffic.

• Any other high-altitude RPA configuration for border surveillance has a very limited endurance (24-36 hours) that would drastically increase any potential collision risk with civil aviation traffic.

• At least a double number of RPAs would be requested to continuously guarantee the surveillance service, highly increasing the System Total Life Cycle Cost.

• At least 4 MALE RPAs are requested to cover continuously the same area covered by HALE, since the covered area is decreasing with the square value of the flying altitude. Total Life Cycle Cost of MALE system shall tremendously increase.

• Main Advantage with respect to Aerostatic RPA: high station keeping also with strong jet stream

Copyright by G. Romeo

DIMEAS


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HELIPLAT

Very Long Endurance Solar-Powered Autonomous Aircraft

DIMEAS


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SOLAR CELLS • Maximum available Solar cell efficiency: 85%. To-date obtained eff.: 36%.

• High efficiency (25%) thin (150 microns) mono-crystalline silicon cells are to-day available at low-medium price (about 2000 €/m2) .

• Higher efficiencies (up to 30-35%) very thin (50 microns) single-crystal silicon or GaAs cells are also available, at higher price (about 30-100 k€/m2) .

HELIPLAT

GaAs CELL: 30% Cost: 30 k€/m2

G. Romeo

DIMEAS


Cost: 100 k€/m2

efficiency > 25%

Triple-junction

CELL: 32%

Si mono-crystalline

25% Efficiency

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HELIPLAT® (HELIos PLATform) WT=850kg; Wpl=130kg; Preq=6.5kW; Ppl=1.5kW;

Vc=71km/h (TAS); Solar cell effic. 21%; Fuel cell effic. 60%

Sw=176.5m2; b=73m; ARw=30.2; S ht=28m2; b=17.5m;

® Trademark:POLITECNICO DI TORINO, DIASP, Giulio Romeo

EC – 5FP

Jet-stream up to 150 km/h G. Romeo

DIMEAS

Multi-disciplinary optimisation program: 1) Solar radiation change over year; 2) Altitude; 3) Wind speed; 4) Structural mass. 5-6) Mass and efficiency of solar cells and of fuel cells; 7) Aerodynamic performances;

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Cl-Alpha HPF118 profile - Re=500000

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6

1.8

-7 -6 -5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18

Alfa

CL

Xfoil

Stuttgart

HELIPLAT® Aerodynamic Design

New high performances airfoils developed to reduce the power required for the flight.

HELIPLAT

VSAERO CFD

G. Romeo

DIMEAS


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Scaled Prototype Design & Manufacturing

HELIPLAT

POLITO

G. Romeo

DIMEAS


EASA CS-VLA n= 3.8

HM CFRP material: very light - high stiffened structure.

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Scaled Prototype Manufacturing and Testing

HELIPLAT

HELIPLAT

Wing span: 24m G. Romeo

DIMEAS


Shear/Bending Static Failure Test N=7.5g

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3 HALE UAVs WP Leader: Prof. G. Romeo

SHAMPO

(Solar Hale Aircraft Multi Payload & Operation)

IAI - POLITO

POLITO

MTOW ---> 950 kg; Payload weight ---> 150 kg Ceiling ---> 17-20 km; Payload Power ---> 1.5 kW Endurance ---> months; Wing Span ---> 73 m

MTOW ----> 7700 kg; Payload weight ---> 500 kg Propulsion ----> 559 kg; Wing Span ---> 32 m Ceiling ----> 20 km; Endurance ---> 24 hrs Fuel weight ----> 3400 Kg; Max Airspeed ---> 340 Kt

G. Romeo


HELIPLAT

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HELIPLAT

SESA FLIGHT MODEL

G. Romeo

G. Romeo

DIMEAS


EASA VLA n=3.8g

WOURLD AIR GAMES – Turin 2009

Planned Flight Mission Traiettoria in AP

4,52E+01

4,52E+01

4,52E+01

4,52E+01

4,52E+01

4,52E+01

4,52E+01

4,52E+01

4,52E+01

4,52E+01

7,680 7,682 7,684 7,686 7,688 7,690 7,692 7,694 7,696 7,698 7,700 7,702

Longitudine

Lati

tud

ine

Experimental Recorded Mission

Autopilot/Manual Hardware

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HELIPLAT TANGO Demo Mission Architecture Flight Test Site: Tarquinia Lido

G. Romeo

DIMEAS


-25

0

25

50

75

100

125

150

175

200

225

250

213500 213700 213900 214100 214300 214500 214700 214900 215100

AutoPilot Data

IRIDIUM data

G. Romeo

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DIASP

ENvironmentally Friendly Inter City Aircraft powered by Fuel Cell

© 2010 by Prof. G. Romeo.


Electric-motor airplane powered by fuel cells validated by flight-test.

Rapid 200-Fuel cell

V top =160 km/h V max av 1run =142 km/h V max av 2run =135 km/h V max av 4run =133 km/h Endurance: 49 min

FAI World Speed Record FAI World Endurance Rec

FAI Class C Aeroplane

G. Romeo

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HELIPLAT


DIMEAS

Preliminary Design

Research Contract n.606/2014, Sept. 2014 with:

SHENYANG AEROSPACE UNIVERSITY, CHINA

“Detail Design of a Scaled Prototype for 1 month Flight

Endurance High Altitude Long Endurance Solar-Powered UAV”

The SAU technical requirements include：

1) Payload weight: 10-15kg; 2) endurance: 1 month; 3) Flight altitude and latitude;

The POLITO technical files shall include:

(1)Technical drawings of 3D model including whole structure;

(2)Analysis files of FEM model and results including whole structure;

(3)Aerodynamic performance data;

(4)Technical files for processing and manufacturing.

(5)Technical files and drawings for solar power system include solar power panel system, battery

system, electric motors and controllers.

(6)Flight Dynamic law and Design of flight control system.

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HELIPLAT


DIMEAS

SHENYANG AEROSPACE UNIVERSITY, CHINA

Faku airfield

UAV FC

Liaoning General Aviation Academy (LGAA)

http://www.uasvision.com/2012/08/21/first-flight-of-fuel-cell-powered-uas-in-china/china2-2/

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HELIPLAT

Very Long Endurance Solar-Powered Autonomous RPA

DIMEAS


VESPA must have amount of rechargeable batteries to fulfill the energy requirement during night-time. Batteries' weight greatly affects the operational envelope of such aircraft.

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HELIPLAT


DIMEAS

Preliminary Sizing Multidisciplinary Design Optimization

Aerodynamics

Weight estimation Power balance

Flight Mechanics Structural requirements

Main Outcomes • High aspect-ratio wing to achieve high

efficiency and power index • Very low gross weight • more than 30% battery

Constraints • 1 month of continuous flight @

42°N latitude – 17 km altitude • 15 kg payload • solar cells efficiency 25% • battery energy density 260 W/kg

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HELIPLAT


DIMEAS

Preliminary Design

Best Configuration Design

G. Romeo

G. Romeo

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HELIPLAT


DIMEAS

Gross weight breakdown

Weight breakdown

Overall weight 2056 N

Structural weight breakdown

Structural Analysis • 2 counter posed C-spars made by

carbon-epoxy composite • upper and lower panels made by

carbon epoxy composite • Equal-spaced multi ribs

G. Romeo

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HELIPLAT


DIMEAS

Structural Analysis - Wing Box

G. Romeo

23

HELIPLAT DIMEAS

Wing deflection at n=1, n=3, n=4.5

0,95 m

2,85 m

4,28 m


Structural Analysis - Wing Box

G. Romeo

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HELIPLAT


DIMEAS

Structural Analysis

Horizontal Tail

Vertical Tail

Booms

G. Romeo

25

Flight Simulator HELIPLAT


DIMEAS

Automatic Flight Control System

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HELIPLAT


Optimum Propeller design process Propeller On-design study: parametric analysis for HELIPLAT

INPUT DATA • Flight Speed: V= 20 m/s; • Blade radius: R= 0.5÷2 m; • Thrust: T= 26 N; • Altitude: z= 17000 m;

OUTPUT DATA • Propeller Efficiency, η; • Propeller adimensional coefficients • Power absorbed at shaft, Pa [W]; • Torque absorbed at shaft, Ca [Nm]

DIMEAS

E. Cestino

27

CONCLUSION

• Possible realisation of HAVE-UAV at least for low latitude sites in Europe and for 4-6 months. •Airfoils with high Lift coeff. and small Drag coeff. and at low Reynolds numbers were obtained. • The aerodynamic performances of HELIPLAT were implemented by VSAERO software, obtaining very high efficiency. • Showed feasibility of very light CFRP structural elements. • Good correspondence between experimental analytical and FEM analysis was verified. • The experimental flight tests validated several critical technologies for high altitude very long endurance flight: high efficiency solar cells, electric brushless motor, controllers, video and thermo camera image transmission, telemetry system • Flight Tests of Fuel cell Powered Aircraft showed the feasibility of long endurance UAV • The 30 days endurance flight, planned for next year, should be a great step in direction of a new solar powered RPAS

DIASP HELIPLAT


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DIMEAS

Grazie per la vostra gentile attenzione G. Romeo, Polito, DIMEAS: partner di progetti EC – ESA

HELIPLAT

S STRAT www.polito.it/grupporomeo

www.enfica-fc.polito.it POLITO, DIMEAS, [email protected]

Documents

Nessun titolo diapositiva...VSAERO software, obtaining very high efficiency. • Showed feasibility of very light CFRP structural elements. • Good correspondence between experimental