The Micro Satellite Formation And Attitude Control Based On The Atmospheric Drag

With the advantages of low cost, short cycle of development and the lack of risk, small satellite quickly gained wide attention and research. The concept of distributed satellite formation system involves the distribution of the function of a single satellite among several smaller, cooperative satellites. Distributed satellite formation system in design and development, cost, performance, risk assessment are better than the complex structure of the traditional single satellite, it has become a hot research field in recent years. The small satellite attitude stabilization and track motion control is the premise and foundation of the normal operation of the distributed satellite formation. Satellite autonomous control technology is one of the key technologies of distributed satellite system.Autonomous multiple satellite formation flying space missions offer many promising possibilities for space exploration. Aiming at the lack of small satellite to carry large amounts of propellant capacity is insufficient, the use of near earth orbit satellite by atmospheric drag effects, design a nonlinear adaptive sliding mode variable structure control algorithm to control the attitude of small satellites and stable formation relative orbital motion. The traditional satellite attitude and orbit control by active force control system. To load a certain satellite propulsion device, cost a certain amount of fuel for satellite maneuver to provide rotational torque or power. Control technology of active force to the small satellite overall design, research and development costs and launch risk difficulty. However, the small satellite belongs to power in low earth orbit environment by atmospheric drag. By changing the satellite surface to mass ratio, using atmospheric drag control satellite motion without propulsion device and propellant, which accords with the characteristics of small satellite's small size and light weight and simple structure, etc.First of all, this paper studied the control of small satellite formation flying relative orbital motion based on atmospheric drag.Combined with the adaptive sliding mode variable structure control theory and the principle of the design of a nonlinear control algorithm.By rotating the installed on the satellite a pair of pneumatic plate to change the satellite surface to mass ratio, as a control input. Due to natural conditions, only discuss the formation relative motion in orbit plane. The simulation results show that the proposed control strategy has good control performance in the presence of the initial error conditions.Then, this thesis investigates the attitude control of a satellite based atmospheric drag.Combined with the adaptive sliding mode variable structure control theory and the principle of the design of a nonlinear control algorithm.In the case of the aerodynamic drag stabilized satellite, the drag plates are considered to be attached to the satellite. Two on the contrary pneumatic plate installed on the satellite to pneumatic plate angle as input control. The simulation results show that the proposed control algorithm has good control performance and can keep the satellite attitude stabilization.