Study On Coupling Control Of Attitude And Orbit For Mars Orbit Insertion At Periareon

With the success of India’s Mars Orbit Mission, our plan of Mars exploration has also been taken to the agenda. In this paper, we bases on the project ‘Engineering Technique Research of Mars Orbit Insertion’. There are two points of innovation in this paper. Firstly, we apply particle swarm optimization to parameter optimization of finite-thrust braking at Mars perigee and solve this parameter optimization problem with constraints of perigee height and apogee height. Secondly, we establish dynamical model of liquid-filled flexible spacecraft with high-thrust and have the simulation.This paper carries out the research focus on strategy of capture and coupled orbit-attitude control during MOI. The content of research is divided into the following four parts.Firstly, coordinate system and orbit dynamic model are established. The Earthdeparture orbit, heliocentric-transfer orbit, Mars-approach orbit and Mars-around orbit are designed based on the mission requirement.Secondly, constant-inertial-attitude control, negative-trajectory-direction control and constant-angular-rate control are designed and are optimized by particle swarm optimization. The optimization results are used in simulation analysis.Then the attitude dynamic model of flexible craft is established and used. The simulation of maneuver control by sliding-mode control and attitude-hold control are carried out.Finally coupled dynamical model of liquid-filled flexible spacecraft with highthrust is established. The coupling control simulation analysis of attitude and orbit based on this model with effect of attitude measuring error and thrust eccentric are carried out.The result of this paper can be used in project work and follow-up study.