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Tilting dual-rotor aircraft and attitude control method thereof

A tilt-rotor, flight control technology, applied in attitude control and other directions, can solve the problems of troublesome vector structure, not fast enough, easy to fail, etc., to avoid the risk of crash, reduce demand, and balance reliability problems.

Pending Publication Date: 2022-07-15
佛山市鹰火微峰科技有限公司
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  • Abstract
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  • Application Information

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Problems solved by technology

Therefore, the more rotors there are, the more tolerance the aircraft will have for the failure of the power system. On the contrary, the control of the vector structure by the aircraft is more troublesome, the reliability is not high, and it is prone to failure or even crash
At the same time, the more rotors, the weaker the efficiency and endurance of the aircraft, the flight is not flexible enough, and the speed is not fast enough

Method used

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  • Tilting dual-rotor aircraft and attitude control method thereof

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Embodiment Construction

[0021] In order to make the technical solution, technical purpose and technical effect of the present invention clearer, so that those skilled in the art can understand and implement the present invention, the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.

[0022] like figure 1 shown, figure 1 A schematic diagram of the structure of the tilting dual-rotor aircraft according to the preferred embodiment of the present invention is shown. The tilt-rotor aircraft includes a hovering bag 10 , a flight control module 30 , a remote control module 40 and two sets of tilt-rotor combination structures 20 ;

[0023] The tilt-rotor combined structure 20 includes a motor 21, a steering gear 22 that is tiltably mounted on the hovering bag 10 and connected to the motor 21 and used for tilting the motor 21; the motor 21 is provided with a propeller;

[0024] The flight control module 30 is installed on the h...

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Abstract

The invention provides a tilting dual-rotor aircraft and an attitude control method thereof. The tilting dual-rotor aircraft comprises a hovering capsule body (10), a flight control module (30), a remote control module (40) and two sets of tilting rotor combined structures (20), the tilting rotor combined structure comprises a motor (21) and a steering engine (22) which is mounted on the hovering capsule body in a tilting manner and is connected with the motor; propellers are mounted on the motors; the flight control module is mounted on the hovering capsule body and is electrically connected with the tilt rotor combined structure; the remote control module is in communication connection with the flight control module. According to the tilting dual-rotor aircraft and the attitude control method thereof, a variable-inclination-angle dual-rotor technology is creatively adopted, multi-degree-of-freedom movement steering is achieved through the minimum number of rotors, the hovering capsule is adopted, the reliability problem caused by the adoption of a two-tilting-rotor combined structure is solved, and the risk of air crash is avoided.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a tilting dual-rotor aircraft and an attitude control method thereof. Background technique [0002] For an aircraft with certain motion characteristics, the more the quantity that can participate in the control, the easier it is to obtain a good control effect. Therefore, the more rotors there are, the more the aircraft can tolerate the failure of the power system. On the contrary, the control of the vector structure by the aircraft is more troublesome, the reliability is not high, and it is prone to failure or even crash. At the same time, the more rotors, the weaker the efficiency and endurance of the aircraft, the less flexible the flight, and the less fast speed. SUMMARY OF THE INVENTION [0003] In view of the above technical problems, the present invention provides a tilting dual-rotor aircraft and an attitude control method thereof. [0004] The technical scheme...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCG05D1/0833
Inventor 姚刚章池生肖鑫胡会明陈海涛刘坤
Owner 佛山市鹰火微峰科技有限公司
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