Novel solar airplane

A solar-powered aircraft and aircraft technology, applied in the field of solar-powered aircraft, can solve the problems of lift and drag loss, reduce the lift-to-drag ratio of the whole aircraft, and cannot give full play to the high lift-to-drag ratio characteristics of positive camber airfoils.

Inactive Publication Date: 2012-10-17
BEIHANG UNIV
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Problems solved by technology

At present, most solar-powered aircraft adopt traditional or flying-wing aerodynamic layout, and achieve wing zero-lift moment trimming by means of flat tail, canard or S-wing, which brings lift and drag loss, and reduces the lift-to-drag ratio of the whole aircraft. Unable to give full play to the high lift-to-drag ratio characteristics of the positive camber airfoil

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Embodiment Construction

[0011] The invention relates to a solar-powered aircraft with high lift-to-drag ratio and low energy consumption. In order to improve the lift-to-drag ratio, the aircraft adopts a positively cambered wing (9) with a large lift coefficient, and the center of gravity (12) is arranged directly below the wing focus (13), thereby generating a large lift-to-drag ratio and nose-up moment, while making the The whole machine has static stability. It can not only improve the lift-to-drag ratio of the aircraft, but also make the whole aircraft have static stability. The area of ​​the wing (9) is large enough to be suitable for installing more solar panels to ensure sufficient energy storage for night and cloudy flight use. At the same time, in order to improve the structural strength of the aircraft and reduce the structural weight, a double-wing surface (9, 11) and a double-supporting wing (5, 14) structure are adopted.

[0012] In order to have a high lift-to-drag ratio capability an...

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Abstract

The invention relates to a solar airplane which has a high lift-drag ratio and low energy consumption. In order to improve the lift-drag ratio, positive camber wings (9) with a large lift coefficient are adopted, a gravity center (12) of the positive camber wing is arranged right below a wing focus (13) so as to generate a large lift-drag ratio and a large rising moment, and meanwhile, the whole airplane has static stability; the lift-drag ratio of the airplane can be improved, and the whole airplane has static stability; the areas of the wings (9) are large enough, so more solar cell panels are suitable to be mounted, and enough energy is guaranteed to be stored for flights at night and on cloudy days; and meanwhile, in order to improve the structural strength of the airplane and lighten the structural weight, a structure of double wing surfaces (9) and (11) and double supporting wings (5) and (14) is adopted.

Description

Technical field: [0001] The invention relates to a solar-powered aircraft with a high lift-to-drag ratio, belonging to the technical field of fixed-wing aircraft in aviation aircraft technical background [0002] As a renewable clean energy, solar energy has broad application prospects. Using solar energy as an aircraft power source is an important research goal with direction and cutting-edge for human beings. [0003] In the design of solar-powered aircraft, one of the main technical difficulties encountered is how to greatly improve the lift-to-drag ratio characteristics of the aircraft with a small increase in structural weight. At present, most solar-powered aircraft adopt traditional or flying-wing aerodynamic layout, and achieve wing zero-lift moment trimming by means of flat tail, canard or S-wing, which brings lift and drag loss, and reduces the lift-to-drag ratio of the whole aircraft. The high lift-to-drag ratio characteristics of the positive camber airfoil can...

Claims

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Application Information

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IPC IPC(8): B64C3/10B64C3/58B64D27/02
Inventor 王维军黄健
Owner BEIHANG UNIV
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