Attitude control of spacecraft during propulsion of swing thruster

XIA Xi-wang, JING Wu-xing, GAO Chang-sheng, WEI Wen-shu

Dept. of Aerospace Engineering,Harbin Institute of Technology,Harbin 150001,China,



Abstract:

As for orbit transfer vehicle (OTV) with multiple satellites/payloads carried,the release of each payload will bring serious change to the mass center of OTV and the thrust produced by the swing thruster will form a rather large disturbance to the attitude of OTV. Steering the nozzle to track the estimated center of mass (ECM) of OTV can reduce but not remove the disturbance due to the difference between the ECM and the practical mass center (PCM) of OTV. The practical propelling direction will change with the internal motion during the propulsion process and attitude control system should be enabled to guarantee that the propelling direction is collinear with the command. Since the structural parameters have changed,which is due to internal motion and fuel consumption,the dynamic model have to be formulated to determine these time-varying parameters and the required attitude of OTV should be determined as well. Modulating attitude quaternion results in quasi Euler angles. Based on the resulting quasi Euler angles,a novel attitude switching control law is introduced to control the variable-mass OTV. Simulation results show that,even in the case of structural asymmetry,control torque matrix asymmetry,attitude disturbance and strong coupling between the channels,the attitude of OTV can be controlled perfectly,and the proposed attitude control law is effective for the variable-mass OTV with swing thruster.

Key words:  variable-mass spacecraft  relative motion dynamic modeling  quasi Euler angle  attitude switching control law

DOI：10.11916/j.issn.1005-9113.2012.01.019

Clc Number:V448.22

Fund: