Method for regulating propeller direction to point to combined-body spacecraft centroid

Abstract

The invention discloses a method for regulating a propeller direction to point to a combined-body spacecraft centroid, relating to a propeller control method of a combined-body spacecraft in on-orbit service, and the method further comprises a quality and characteristic identification method of the combined-body spacecraft, belonging to the field of posture control of a spacecraft. The method comprises the following specific implementing steps of 1, online identifying a centroid position of the combined-body spacecraft, and obtaining a centroid deviation of a tracking spacecraft and the combined-body spacecraft; 2, obtaining a regulation angle of the propeller according to the centroid deviation; and 3, adjusting the propeller direction according to the regulation angle of the propeller obtained in the step 2, and enabling a spray nozzle of the propeller to repeatedly point to the centroid of the combined-body spacecraft. According to the method, the combined-body centroid can be identified, and the propeller direction can be regulated and is enabled to point to the combined-body centroid, and the regulated propeller can be used for integrated control of a combined-body spacecraft attitude and orbit.

Description

technical field [0001] The invention relates to a method for adjusting the thruster direction to point to the center of mass of an assembled spacecraft, in particular to a thruster control method for an assembled spacecraft in on-orbit service, which also includes a method for identifying mass characteristics of an assembled spacecraft, belonging to The field of attitude control for spacecraft. technical background [0002] In the process of on-orbit service of space spacecraft, attitude-orbit integrated control is the process of spacecraft in-orbit operation, while considering the orbit and attitude maneuver tasks of the spacecraft, and realizing simultaneous control of the orbit box attitude by sharing a set of actuator configurations The integrated control of attitude and orbit can make the best use of the excitation ability of the actuator, save some hardware resources, and improve the efficiency of fuel utilization. [0003] In the rendezvous and docking mission of the...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the jet direction of the thruster no longer points to the center of mass due to the change of the center of mass of the combined spacecraft after rendezvous and docking in the on-orbit service mission. The method of the center of mass of the combined spacecraft can not only identify the center of mass of the combined body but also adjust the direction of the thruster to point to the center of mass of the combined body. The adjusted thruster can be used for the integrated control of the attitude and orbit of the combined spacecraft

Images