Method for regulating and controlling posture of spacecraft by flow velocity and actuating mechanism thereof

Abstract

The invention relates to a method for regulating and controlling a posture of a spacecraft by the flow velocity and an actuating mechanism thereof and belongs to the field of control to the posture of the spacecraft. The method comprises the following steps that: according to a difference value of a current posture and a desired posture, a three-axis control moment vector required by the spacecraft is obtained, and according to a principle of the momentum moment, a relation between the three-axis control moment vector and the variation of a liquid fuel flowing angular velocity is obtained; according to the working principle of ring-shaped pipe liquid angular momentum exchange equipment, a relation between the liquid fuel flowing angular velocity and the change rate of a velocity vector in the tangential direction of a pipe when liquid fuel flows is obtained; according to corresponding generated required conditions, the power of the pressure pump is controlled to apply work to the liquid, so that the flow velocity of the liquid is changed, and thus, the angular momentum H of a mass center of the spacecraft is changed and the posture of the spacecraft 10 is changed; and the changed posture is measured by a sensor and is compared with the desired posture and the steps are circularly repeated from the beginning of the step 1. The actuating mechanism for regulating and controlling the posture of the spacecraft by the flow velocity, which is used for implementing the method disclosed by the invention, comprises a liquid filled ring-shaped pipe, the pressure pump, an oil storage tank, a valve, a liquid outlet connecting pipe, a liquid return connecting pipe and a control mechanism.

Description

technical field [0001] The invention relates to an actuator for controlling the attitude of a spacecraft, in particular to a method for controlling the attitude of a spacecraft by adjusting the flow rate and the actuator thereof, belonging to the field of attitude control of the spacecraft. Background technique [0002] With the development of the aerospace industry, the requirements for the accuracy, life and reliability of the actuators of the attitude control system are getting higher and higher. On-board attitude control mainly refers to the control of the attitude angle of the spacecraft on orbit, which refers to the pitch, yaw, and roll motions. Generally, the attitude of the spacecraft is projected in a certain coordinate system, and the coordinate system is expressed by Euler angles or quaternions posture changes. There are various corresponding control methods, such as the widely used and mature PID control method in the industry. PID control method can refer to: ...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the unstable and unbalanced problems in the process of angular momentum exchange in the control moment gyroscope in the prior art, and to propose a method for controlling the attitude of a spacecraft by adjusting the flow rate and its executive mechanism

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