Spacecraft attitude control method based on variable and inertia flow velocity adjustment controller and actuating mechanism of spacecraft attitude control method

Abstract

The invention discloses a spacecraft attitude control method based on a variable and inertia flow velocity adjustment controller and an actuating mechanism of the spacecraft attitude control method. The actuating mechanism comprises a main ring liquid filling annular pipe, a main ring pressure pump, an oil storage tank, a valve, a main ring liquid outlet connecting pipe, a main ring liquid return connecting pipe, a variable ring liquid filling annular pipe, a variable ring pressure pump, a variable ring liquid outlet connecting pipe, a variable ring liquid return connecting pipe and a control mechanism. A flowing loop is formed by the main ring liquid filling annular pipe, the main ring pressure pump, the oil storage tank, the valve, the main ring liquid outlet connecting pipe and the main ring liquid return connecting pipe. The other flowing loop is formed by the variable ring liquid filling annular pipe, the variable ring pressure pump, the oil storage tank, the valve, the variable ring liquid outlet connecting pipe and the variable ring liquid return connecting pipe. According to the spacecraft attitude control method based on the variable and inertia flow velocity adjustment controller and the actuating mechanism of the spacecraft attitude control method, the problems of rotation speed saturation of angular momentum exchange type actuating mechanisms in the process of wide-angle attitude adjustment in the prior art and much mass and the size requirement burden, caused by generated actuating mechanism redundant configuration of a traditional actuating mechanism in order to solve the problem of rotation speed saturation, of a spacecraft are solved.

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 an spacecraft based on a variable inertia flow rate adjustment controller and its actuator, and belongs to the technical field of attitude control for spacecraft. Background technique [0002] In modern space missions, in order to achieve more diverse space missions, the requirements for attitude control and adjustment capabilities of spacecraft are also increasing. There are many types of attitude control actuators on the planet. At present, the angular momentum exchange actuator is used as the method of attitude control on the planet because of its advantages of no additional working fluid consumption, high control accuracy, and stable and continuous thrust. It is widely used in spaceflight. task of all ages. The method of controlling the attitude of spacecraft by using the flow rate adjustment controller has b...

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Problems solved by technology

[0005] The purpose of the present invention is to solve the technical problem in the prior art that due to the requirements of fluid working conditions and the limitation of the flow rate adjustment ability of the pressure pump, the output torque of the actuator is saturated and cannot meet the requirements of aerospace attitude adjustment. Spacecraft Attitude Control Method and Its Actuating Mechanism Based on Inertia Flow Velocity Adjustment Controller

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