Attitude and orbit control method based on fore and after arrangement of engine

Abstract

The invention provides an attitude and orbit control method based on fore and after arrangement of an engine. In the method, the front end and the rear end of a spacecraft are respectively provided with a translation engine; starting-up of the engines is combined to control the position and attitude of the spacecraft at the transverse moving direction, pitching direction and yawing direction of the spacecraft respectively. According to the barycentre position of the spacecraft, startup factor ki1 of positions of the front and rear engines is calculated by the translating control force according to a principle that magnitudes and directions of thrust generated by the front and rear engines at the same direction of the spacecraft are the same as the requirement of control force, and the magnitudes of torques generated by the front engine and the rear engine are the same; startup factor ki2 of attitudes of the front engine and the rear engine is calculated by the attitude control torque requirement according to the principle that the magnitudes and directions of torques generated by the front and rear engines at opposite directions of the space craft are the same as the control torque requirement, and the magnitudes of the thrust generated by the front and rear engines at the opposite directions are the same; and finally, the total startup factor ki equaling to ki1 plus ki2 of the translation engines are calculated, and the engine is started to complete attitude and orbit control after normalization processing.

Description

technical field [0001] The invention relates to an engine configuration method and a spacecraft attitude control method based on the configuration. Background technique [0002] In the manned spaceflight project, the mission of the cargo spacecraft is to deliver experiments and maintenance supplies to the space station, replenish living and consumable materials, and take away living and working waste on the space station. Before the launch of each cargo spacecraft, due to different mission requirements, the configuration ratio of the delivered supplies is different, and the amount of waste taken away from the space station is uncertain, resulting in a large change in the position of the cargo spacecraft's center of mass. For a spacecraft with a standardized design, the configuration and installation of its attitude-orbit control engine must meet the above-mentioned task requirements for large changes in the position of the center of mass, which puts forward higher requiremen...

AI Technical Summary

Problems solved by technology

In the existing spacecraft engine configuration scheme, the center of mass is located on one side of the translation engine, and the translation engine and the attitude control engine complete the position and attitude control respectively. , will inevitably bring attitude interference; attitude control cannot form force couple control, then when performing attitude control, it will inevitably bring position interference

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