Study On System Design And Control Technology For Small Satellite With Rapid Maneuver Missions

With the development of space technology, requirements for spacecrafts with rapid maneuver ability become more and more intense. A small satellite with rapid maneuver missions is discussed in this thesis. Multidisciplinary Design Optimization (MDO) is adopted for its'system design. Combined with the specific characters of this type satellite described as"autonomy and rapid", control sub-system as one of the key sub-systems is studied.Firstly, three types of MDO procedures are studied, including CSSO (Concurrent Subspace Optimization), BLISS 2000 (Bi-Level Integrated System Synthesis 2000) and CO (Collaborative Optimization). Aimed at solving some problems in carrying out CO procedure, an improved CO using dynamic penalty factor and orthogonal experimental design named DPCO is proposed, and its efficiency is tested by a typical optimization problem. The characters of these three MDO procedures are analyzed by two design optimization problems—Speed Reducer and Plane concept design. And the applicability of each procedure is concluded.Secondly, according to the characters of rapid maneuver small satellite, disciplinary models are analyzed; and a parameter optimization model is set up to minimize the cost of satellite. The MDO problem is integrated and solved by DPCO, and advantages of DPCO are verified.Thirdly, a Lyapunov-based orbital controller is studied on the basis of orbital dynamics of spacecraft expressed by two-body motion with guide satellite. The numerical simulations for maneuver missions are presented on the basis of foregoing satellite system design scheme. And the maneuver process is also demonstrated by the software STK (Satellite Tool Kit).The results show that the mission requirements are satisfied and the controller design is feasible. Finally, the attitude control system is introduced in details and a Lyapunov-based control law is discussed for flywheel system. MCOA (Multimethod Collaborative Optimization Algorithm) is adopted to optimize the control parameters of this controller with the object of minimizing control time. Then numerical simulations are presented on the basis of foregoing satellite system design scheme for attitude stabilization control and maneuver control. The results show that the scheme is feasible.To sum up, three types of MDO procedures are discussed. Based on it, DPCO is proposed to solve the system design problem of small satellite with rapid maneuver mission. All of these are beneficial tries for application of MDO in satellite system design. The control system is also discussed; MCOA is adopted to optimize the control parameters, and the rapid maneuver mission on orbit is fulfilled. This thesis is a good foundation for further research on space maneuver system.