Attitude rail coupling adjusting method based on high-thrust satellite

Abstract

The invention relates to an attitude rail coupling adjusting method based on a high-thrust satellite. The method includes steps of 1), optimizing the structure layout at inside and outside of a satellite body on the basis of the satellite structure design by taking the symmetrical design in the satellite body and no shielding at surrounding of propellent releasing nozzle at outside of the satellite body as a principle; 2), analyzing the influence of high thrust on the satellite body when the satellite propellent is released, designing an attitude control system to guarantee the normal running of the satellite after releasing the propellent; 3), processing a propellent storage bottle on the satellite so that the propellent release meets the normal release requirement of high thrust; 4), controlling the satellite attitude by the attitude control system, and realizing the attitude rail coupling control of the high-thrust satellite. Through the optimized design of the satellite structure, the calculation analysis of satellite centroid and rotational inertia in the centroid coordinate system after the propellent is release, the satellite attitude is adjusted before the release of propellent every time.

Description

technical field [0001] The invention relates to an attitude-orbit coupling adjustment method based on high-thrust satellite maneuvering to realize high-mobility requirements of satellites by applying high-thrust. Background technique [0002] It is very important to use high thrust to realize rapid orbital maneuvering of satellites in applications such as deep space exploration and earth observation. [0003] At present, high-thrust is mainly used in the orbit change requirements of satellites in various missions. When the propellant is released, the impact of the high-thrust on the satellite itself is likely to cause attitude-orbit coupling problems. It shows that the high thrust is not only to meet the needs of orbit change, but also to produce impact and disturbance moment on the satellite body. At present, the attitude adjustment method for the application of high-thrust satellites mainly uses the momentum wheel for attitude control. The typical method is the PID contro...

AI Technical Summary

Problems solved by technology

However, for high-thrust satellites that release propellant multiple times in a row, it is impossible to control the satellite persistently through momentum wheels and thrusters

[0005] (2) For small satellites that need to use large thrust for orbital maneuvering, due to the small mass of small satellites, the commonly used momentum wheel attitude control method is adopted, and the interference torque generated by high thrust on the attitude of small satellites is too large, so that the satellite still has a large Risk of not continuing to function normally

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