The Analysis And Suppression Method Of The Influence On Attitude Control Caused By Orbit Control Of Satellite

As the mission of a spacecraft is becoming more and more diversified andcomplex, new requirements have been put forward on the orbit and attitudecontroller. The center of mass of an on-orbit spacecraft may change due to theconsumption of fuel and the departure of payloads. Besides, the long-time orbitoperation of a spacecraft running under certain conditions will also bringdisturbance torque to the attitude control. This thesis comes up with a new method,i.e., thrust vector fusion method, to suppress the disturbance on the attitude controlcaused by longtime orbit operation.The dynamics and kinematics of a satellite is analyzed based on the satellite’sdifferent kind of parameters. After the introduction of flexible attitude module,space disturbance torque module and disturbance torque module caused by rotatingcomponents, the kinetic and dynamic model of the satellite is set up usingquaternion and Euler angle parameters.Then based on the thrust vector fusion method, the combined attitude-orbitthrust usage strategy, the real time estimation of the center of mass, the pulse widthdistribution between attitude and orbit control according to the length of force armand the fusion algorithm of attitude-orbit control pulse width are deducted in detail.The method has been proved feasible according to massive ground test.Based on the comparison of simulation results, we can confidently concludethat the new thrust fusion algorithm is both effective and practical. The algorithmcan effectively suppress the disturbance on the attitude control caused by jet enginesrunning for orbit control operation, while at the same time reduce the consumptionof fuel, thus alleviating the energy shortage problem of the on-orbit satellite.