High-aspect-ratio high-strength double-layer wing solar unmanned aerial vehicle

A technology of solar unmanned aerial vehicles and large aspect ratio, which is applied in the field of aviation aircraft, can solve the problems of difficulty in reducing the structural weight, low aerodynamic efficiency, and the aspect ratio of the wing cannot be too large, so as to improve the resistance to crosswind disturbance High capacity, simple structure, favorable effect of shape drag reduction

Pending Publication Date: 2021-04-06
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It is difficult to reduce the weight of the structure with the conventional layout. Due to the limitation of the strength and stiffness of the wing, the aspect ratio of the wing cannot be too large, so the aerodynamic efficiency is not high

Method used

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  • High-aspect-ratio high-strength double-layer wing solar unmanned aerial vehicle
  • High-aspect-ratio high-strength double-layer wing solar unmanned aerial vehicle
  • High-aspect-ratio high-strength double-layer wing solar unmanned aerial vehicle

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Embodiment Construction

[0033] This part is the embodiment of the present invention, which is used to explain and illustrate the technical solution of the present invention.

[0034] A large aspect ratio high-strength double-layer wing solar unmanned aerial vehicle, such as figure 1 , figure 2 and image 3 Shown, comprise fuselage 3, wing and empennage; Wherein, wing is horizontal consistent system wing, and wing has two, is respectively upper strata wing 2 and lower deck wing 1, and fuselage is arranged on upper deck wing 2 Between the upper wing 2 and the lower wing 1, the upper wing 2 and the lower wing 1 are connected by a wingtip support wall 17; the upper surfaces of the upper wing 2 and the lower wing 1 are provided with solar panels; the empennage is located at the fuselage tail.

[0035] There are two fuselages 3, and the two fuselages are located between the upper wing 2 and the lower wing 1, and the two fuselages 3 are symmetrical to the center line of the aircraft.

[0036] The leadin...

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Abstract

The invention belongs to the technical field of aviation aircrafts, and discloses a high-aspect-ratio high-strength double-layer wing solar unmanned aerial vehicle which comprises a fuselage, wings and an empennage. The wings are transverse through wings, the number of the wings is two, the wings are an upper layer wing and a lower layer wing respectively, the fuselage is arranged between the upper layer wing and the lower layer wing, and the upper layer wing and the lower layer wing are connected through a wingtip supporting wall; solar panels are arranged on the upper surfaces of the upper-layer wing and the lower-layer wing; the empennage is arranged at tail of the fuselage. According to the double-layer united wing layout, on the premise that structural strength limitation is met, the aspect-ratio of the wings is increased to 30 or above, and the double-layer united wing layout has great significance in designing aerodynamic drag reduction of airplanes with large lift coefficients; the wingspan is reduced by 29%, the structural weight is reduced by 22%, and the mission load and the continuous flight time of the aircraft can be remarkably improved; the wings are high in bending resistance and torsion resistance; and satisfactory three-axis stability and control capability can be provided.

Description

technical field [0001] The invention belongs to the technical field of aviation aircraft, relates to a solar unmanned aerial vehicle, in particular to a large aspect ratio high strength double-layer wing solar unmanned aerial vehicle. Background technique [0002] At present, the successful test flight of solar-powered UAVs has small task loads, small aspect ratios, and low aerodynamic efficiency, and very few of them can fly across the day and night. Due to the strength, stiffness and aeroelasticity of the wings, large-scale solar UAVs with large aspect ratios are disturbed by gusts of wind, the wings are broken, and the aircraft crashes, such as the "Helios" solar UAV in the United States. [0003] At present, small and medium-sized solar-powered UAVs cannot install heavy mission systems, and their energy systems cannot provide long-term power supply for mission systems. Due to the large structural weight and relatively small power weight, it is difficult to achieve long-t...

Claims

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Application Information

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IPC IPC(8): B64C39/08B64C27/22B64C3/36B64D27/24B64C9/00B64C25/10
CPCB64C39/08B64C27/22B64C3/36B64D27/24B64C9/00B64C25/10B64C2009/005B64U50/19
Inventor 张声伟张超明亚丽杨天星王延风
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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