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Multi-body coupling attitude control method and system based on zero-force control

An attitude control, zero-force control technology, applied in attitude control and other directions, can solve the problem of inability to guarantee the high precision and stability of the platform and load attitude control, to improve the attitude control accuracy and stability, reduce the impact, and simplify the design. effect of difficulty

Pending Publication Date: 2022-07-15
ELLIPSPACE (BEIJING) TECH CO LTD
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Problems solved by technology

[0008] Aiming at the deficiencies of the prior art, the present invention provides a multi-body coupling attitude control method and system based on zero-force control to solve the problem that the existing satellite platform has multiple turntable mechanisms and carries large inertial loads at the same time, and the attitude of the platform and the load cannot be guaranteed. High precision and stability of control

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  • Multi-body coupling attitude control method and system based on zero-force control

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Embodiment Construction

[0043] The technical solutions in the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present invention.

[0044] The technical solutions of the present application will be described in detail below with specific examples. The following specific embodiments may be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments.

[0045]The aircraft is oriented to the ground, and the direction of the load is realized by the rotation mechanism. The aircraft (such as small satellites) is small in size and light in weight,...

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Abstract

The invention discloses a multi-body coupling attitude control method and system based on zero-force control. The method comprises the following steps: acquiring disturbance torque generated between a satellite platform and a rotating mechanism due to movement of the rotating mechanism; and calculating a compensation torque according to the disturbance torque and an expected zero torque, and controlling a corresponding rotating mechanism to act according to the compensation torque so as to counteract the influence of the movement of the rotating mechanism on satellite platform control. The rotating mechanism between the satellite platform and the effective load is used as an intermediate medium, and the satellite platform is compensated by controlling the rotating mechanism to act according to the compensation torque, so that the influence of load rotation on satellite platform control is reduced, the attitude control precision and stability of the satellite platform are improved, and the reliability of the satellite platform is improved. Decoupling of satellite platform control and load rotation is achieved, and the requirement for satellite platform control when different space pointing directions of multiple loads are provided at the same time can be met.

Description

technical field [0001] The invention relates to the technical field of spaceborne payload applications, in particular to a multi-body coupled attitude control method and system based on zero-force control. Background technique [0002] Due to the constraints of flight orbits, space vehicles cannot meet the mission requirements of remote sensing of ground targets at any time. In order to improve the response speed to ground targets and shorten the revisit period, spacecraft often need to have the ability to adjust the attitude of the remote sensing payload to increase the remote sensing range of the payload. [0003] Space loads often have high resolution, so high requirements are placed on the pointing accuracy and stability of the control. The existing main design solutions cannot solve the problem that the aircraft platform carries a variety of loads with different spatial orientation requirements, and the load inertia is basically equal to the platform mass. [0004] Th...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0808
Inventor 张涛田丰
Owner ELLIPSPACE (BEIJING) TECH CO LTD
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