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Solar pilotless plane

A technology of unmanned aircraft and solar energy, which is applied in the field of solar unmanned aircraft, can solve the problems of difficult flight control and poor stability of solar unmanned aircraft, so as to alleviate the poor stability and maneuverability, increase the blanking time, and improve the horizontal Effects on directional and longitudinal stability and maneuverability

Inactive Publication Date: 2008-09-03
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the problems of difficult flight control and poor stability of flying wing layout solar unmanned aircraft, the present invention proposes a solar unmanned aircraft

Method used

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  • Solar pilotless plane

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Embodiment 1

[0015] The present embodiment is an unmanned aircraft powered by solar energy, which adopts a single wing with a large aspect ratio and a V-shaped tail layout. The straight section of the wing is a rectangular wing with a span length of 300cm and a chord length of 30cm; the outer winglet is a right-angled trapezoidal wing with an upturn of 30°, a chord length of 30cm, a sweep of 15°, and a tip ratio of 0.67; the fuselage length is 186cm.

[0016] This embodiment includes wing 4 , outer winglet 5 , V-shaped tail 8 , thin-film solar cell 6 , fuselage 7 and equipment cabin 2 . Forty pieces of flexible thin-film solar cells with a length of 25 cm and a width of 7 cm are pasted on the upper surface of the skin of the straight section of the wing. The main structure of the wing 4 and the V-shaped tail 8 is balsa wood and aviation laminates, and the skin is a heat-shrinkable film. Fuselage 7 is made of carbon fiber composite material pipe. Equipment compartment 2 is made of balsa w...

Embodiment 2

[0029] The present embodiment is an unmanned aircraft powered by solar energy, which adopts a single wing with a large aspect ratio and a V-shaped tail layout. The straight section of the wing is a rectangular wing with a span length of 300cm and a chord length of 30cm; the outer winglet is a right-angled trapezoidal wing with a 10° upturn, a chord length of 30cm, a sweep back of 20°, and a tip ratio of 0.5; the fuselage length is 186cm.

[0030] This embodiment includes wing 4 , outer winglet 5 , V-shaped tail 8 , thin-film solar cell 6 , fuselage 7 and equipment cabin 2 . Forty pieces of flexible thin-film solar cells with a length of 25 cm and a width of 7 cm are pasted on the upper surface of the skin of the straight section of the wing. The main structure of the wing 4 and the V-shaped tail 8 is balsa wood and aviation laminates, and the skin is a heat-shrinkable film. Fuselage 7 is made of carbon fiber composite material pipe. Equipment compartment 2 is made of balsa w...

Embodiment 3

[0043] The present embodiment is an unmanned aircraft powered by solar energy, which adopts a single wing with a large aspect ratio and a V-shaped tail layout. The straight section of the wing is a rectangular wing with a span length of 300cm and a chord length of 30cm; the outer winglet is a right-angled trapezoidal wing with a 20° upturn, a chord length of 30cm, a swept back of 10°, and a tip ratio of 0.5; the fuselage length is 186cm.

[0044] This embodiment includes wing 4 , outer winglet 5 , V-shaped tail 8 , thin-film solar cell 6 , fuselage 7 and equipment cabin 2 . Forty pieces of flexible thin-film solar cells with a length of 25 cm and a width of 7 cm are pasted on the upper surface of the skin of the straight section of the wing. The main structure of the wing 4 and the V-shaped tail 8 is balsa wood and aviation laminates, and the skin is a heat-shrinkable film. Fuselage 7 is made of carbon fiber composite material pipe. Equipment compartment 2 is made of balsa w...

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Abstract

The invention relates to a solar unmanned aircraft. In order to overcome the problems of difficult flight control and bad stability of the flying wing solar unmanned aircrafts, the invention adopts the configuration of tip winglets(5) arranged at the outer segments of a large aspect-ratio high wing, a V shaped empennage and a wing(4); the wing(4) is connected with and a fuselage(7) through a bridge wing(3) and a controlling rudder(9) is arranged on the V shaped empennage(8) to realize the pitching and yawing control of the aircraft. Combining the characteristic of the high energy conversion efficiency of a flexible thin film solar battery, the invention lays the flexible thin film solar battery(6) on the wing(4). An engine and propeller propulsion system (1) adopts a haul-in-type, and an equipment cabin (2) is arranged at the front part of the fuselage(7). The solar unmanned aircraft improves the lift-drag ratio of the aerial vehicle, prolongs the operation time and effectively improves the horizontal and the vertical stabilities and maneuverability of the aircraft, thus relieving the problems of bad stability and bad maneuverability of the flying wing configuration.

Description

(1) Technical field [0001] The invention relates to a solar unmanned aircraft. (2) Background technology [0002] Unmanned aerial vehicles have very broad application prospects in military and civilian applications. In terms of military affairs, the main military uses of unmanned aircraft include aerial reconnaissance, intelligence surveillance, missile attack, decoy, target tracking, electronic warfare and battlefield damage assessment. In terms of civil use, unmanned aircraft can be used for communication relay, disaster monitoring, traffic monitoring, border patrol, aerial photography, power transmission line inspection, environmental monitoring, meteorological monitoring, forest fire monitoring, etc. It is precisely because of the extremely broad application prospects and use value of unmanned aircraft in military and civilian aspects that it has attracted great attention from many researchers in the world and has become an international research hotspot. [0003] Trad...

Claims

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Application Information

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IPC IPC(8): B60L8/00A63H27/18A63H27/24
CPCY02T10/7083Y02T10/7072
Inventor 李占科高广林王利光宋笔锋
Owner NORTHWESTERN POLYTECHNICAL UNIV
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