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Attitude control system for coaxial double-propeller spacecrafts

An attitude control and aircraft technology, applied in the field of coaxial double propeller aircraft, can solve the problems of large and expensive steering gear, and achieve the effect of compact structure, large lift and simple structure

Pending Publication Date: 2019-10-01
桐乡市乌镇鹰航科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The existing vector coaxial scull aircraft, the vector coaxial scull aircraft still realizes the attitude control of the aircraft through the mechanical mechanism, and the steering gear used for the control requires a huge torque and a very fast response speed, resulting in big and expensive

Method used

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  • Attitude control system for coaxial double-propeller spacecrafts
  • Attitude control system for coaxial double-propeller spacecrafts

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Embodiment Construction

[0033] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0034] refer to figure 1 with figure 2 ,Such as figure 1 with figure 2 As shown, an attitude control system of a coaxial scull aircraft includes a fuselage 1, a lift assembly 2, and an attitude control assembly 3;

[0035] The fuselage 1 is composed of a control center 11 and a load 12;

[0036] The lift assembly 2 is composed of a forward propeller 21, a first motor 22, a reverse propeller 23, and a second motor 24;

[0037] The attitude control assembly 3 is composed of a third motor 31, a first attitude paddle 32, a fourth motor 33, and a second attitude paddle 34;

[0038] The first mot...

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Abstract

The invention discloses an attitude control system for coaxial double-propeller spacecrafts. The attitude control system for the coaxial double-propeller spacecrafts comprises a fuselage, a lifting force assembly and an attitude control assembly, wherein the fuselage consists of a control center and a load; the lifting force assembly consists of a positive propeller, a first motor, a negative propeller and a second motor; and the attitude control assembly consists of a third motor, a first attitude propeller, a fourth motor and a second attitude propeller. According to the attitude control system for the coaxial double-propeller spacecrafts, the lifting and heading are controlled through the two motors at the upper part, and the forward, backward, leftward and rightward movements are realized through the two motors at the lower part; and the attitude control system for the coaxial double-propeller spacecrafts comprises the respective advantages of the traditional coaxial double-propeller spacecrafts and multi-rotor spacecrafts, and abandons the disadvantages thereof.

Description

technical field [0001] The invention relates to a coaxial scull aircraft, in particular to an attitude control system of the coaxial scull aircraft. Background technique [0002] At present, the development direction of international unmanned helicopters tends to agree with coaxial helicopters. Under the same level of engine, its payload is larger than that of single-blade helicopters, it is safer, its volume is relatively small, and it is also convenient for taking off and landing on smaller sites. , suitable for smaller ground vehicles to carry. Convenient maintenance without tail rotor structure. Since the upper and lower rotors rotate in opposite directions, the moment balance in the horizontal direction of the helicopter is formed, so the twin-blade coaxial helicopter does not need a tail rotor to balance the moment in the helicopter's horizontal direction. The aerodynamic characteristics are symmetrical and the maneuverability is good. In the case of using the same ...

Claims

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Application Information

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IPC IPC(8): B64C27/10B64C27/82
CPCB64C27/10B64C2027/8236
Inventor 姚刚章池生黃景旺胡会明肖鑫乔安娜伊莎贝拉西伯特
Owner 桐乡市乌镇鹰航科技有限公司
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