Gradually varied inertia liquid filling execution mechanism and method for controlling high-accuracy attitude of spacecraft

Abstract

The invention relates to a gradually varied inertia liquid filling execution mechanism and a method for controlling a high-accuracy attitude of a spacecraft. The gradually varied inertia liquid filling execution mechanism comprises a vacuum container (1) for fixing and installing a whole flywheel structure, a flywheel bearing (2), a flywheel motor (3) and a flywheel. The control method comprises the steps that a laminar flow boundary layer equation is established, velocity distribution in a boundary layer is calculated, and an attitude kinetic equation of the spacecraft in the inertia changing process of the execution mechanism is established to obtain control toque Tc required by attitude change and provided by the execution mechanism. By the adoption of the gradually varied inertia liquid filling execution mechanism and the method for controlling the high-accuracy attitude of the spacecraft, the executing capacity of the attitude control execution mechanism is improved in the attitude control process, the output torque coverage range is widened, and meanwhile the problems of dynamic unbalance, too large resistance and the like brought by structure and process design problems during high-frequency rotation of a rotation part are decreased.

Description

technical field [0001] The invention relates to a method for controlling a high-precision attitude of a spacecraft, and aims at a gradually changing inertia liquid-filled actuator and a method for controlling a high-precision attitude of a spacecraft. Background technique [0002] Angular momentum exchange actuators, especially reaction wheels, momentum wheels and control moment gyroscopes, have been fully applied in engineering practice as actuators for active attitude control of spacecraft. Among them, the technologies of reaction wheels and momentum wheels are very mature, and are widely used in high-precision and high-stability attitude control of various types of satellites at home and abroad. Due to its simple structure, high reliability, and fast system response, the constant speed control moment gyro has become the preferred attitude control actuator for long-life spacecraft in engineering practice. [0003] During the in-orbit operation of the spacecraft, the react...

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Problems solved by technology

On the other hand, the research on the fuel storage and stability analysis in the tank of the jet system has been started since the 1960s, but there has always been a large amount of mass redundancy and space waste in the spacecraft fuel storage, and the remaining space after the mission is completed The situation of tens of kilograms of fuel is very common, which affects the payload mass and space ratio of the spacecraft to a certain extent, and greatly increases the possibility of mutual influence and interference

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