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Double-flapping rotor aircraft capable of coaxially rotating in same direction

A technology of co-rotating and flapping rotors, applied in the field of micro-aircraft, can solve the problems of performance loss, low aerodynamic efficiency of aircraft, and drastic changes in single-plane configuration wing load, and achieve the effect of improving aerodynamic efficiency

Active Publication Date: 2021-11-23
BEIHANG UNIV
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to solve the problem that the wing load of the single-plane configuration of the existing flapping rotorcraft changes drastically, the aerodynamic efficiency of the aircraft is low, and the aerodynamic performance of the lower wing of the multi-plane configuration is affected by the wake of the upper wing. dual flapping rotorcraft

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  • Double-flapping rotor aircraft capable of coaxially rotating in same direction
  • Double-flapping rotor aircraft capable of coaxially rotating in same direction
  • Double-flapping rotor aircraft capable of coaxially rotating in same direction

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Embodiment Construction

[0036]In order to understand the above-mentioned purpose, features and advantages of the present invention more clearly, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that, in the case of no conflict, the embodiments of the present application and the features in the embodiments can be combined with each other.

[0037] In the following description, many specific details are set forth in order to fully understand the present invention. However, the present invention can also be implemented in other ways different from those described here. Therefore, the protection scope of the present invention is not limited by the specific details disclosed below. EXAMPLE LIMITATIONS. The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0038] figure 1 It is an overall schematic diagram of a coaxial and co-rotating...

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Abstract

In order to solve problems that an existing flapping rotor aircraft is violent in wing load change of a single-plane structure, the aerodynamic efficiency of the aircraft is low, and the aerodynamic performance of a lower wing of a multi-plane structure is influenced by a wake and is lost, the invention provides a double-flapping rotor aircraft capable of coaxially rotating in same direction. The upper and lower pairs of wings of the aircraft are coaxially arranged, reversely and vertically flapped at the same frequency and rotate in the same direction and at the same speed, the thrust moment in the horizontal direction is increased in the opening and closing process of the two wings, the higher passive rotating speed is obtained in the wing rotating moment balance state, and the lifting force is increased and the aerodynamic efficiency is improved.

Description

technical field [0001] The invention relates to the field of micro-aircraft, specifically but not exclusively, to a coaxial and co-rotating double-flapping rotorcraft. Background technique [0002] Since the 1990s, with the continuous maturity of traditional aircraft design technology and the great progress of microelectronics technology, the concept of micro air vehicle has been proposed and its rapid development has been promoted. Micro air vehicles are small in size, light in weight and strong in maneuverability. They have broad application prospects in national security and national economic construction, and can be used for investigation, exploration, and rescue assistance in complex environments. The focus of current micro-aircraft research is mostly concentrated in the field of bionic micro-aircraft. [0003] At present, people's understanding of the principle of biological flight is gradually deepening, and many bionic micro-aircraft have been built to imitate biolo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C33/02
CPCB64C33/02
Inventor 周超李港褚松涛吴江浩
Owner BEIHANG UNIV
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