Approach For Zero-Propellant Large-Angle Attitude Maneuver Of Space Station

Space station attitude control technology is essential for space station project. Zero-propellant maneuver is an advanced concept of space station attitude maneuver control, which has been applied to International Space Station recently. With the background of preliminary tasks of the Chinese Space Station project, this dissertation studies torque equilibrium attitude of space station, attitude maneuver path planning, analysis and optimization of key parameters, and simulation demonstration based on Simulink. The main achievements obtained in this dissertation are summarized as follows.The calculation method of torque equilibrium attitude is improved. 1) The analytical solution of instantaneous torque equilibrium attitude is deduced, the explicit relation between the instantaneous torque equilibrium attitude and the configuration parameters is established, which provides valuable suggestions for the space station configuration design; 2) The calculation formula of the average and dynamic torque equilibrium attitude are deduced. The average and dynamic torque equilibrium attitude can be used as on-orbit attitude control modes with a long period, whose effectivity has been proved by simulation results.The attitude path planning of zero-propellant maneuver is studied. 1) The model of attitude maneuver path planning is established by the modified rodrigues parameter, which has no constrains and does not incline to be singular. Path planning model contains the dynamic model, constrain conditions and cost functions; 2) The problem of attitude maneuver path planning is solved by the direct shooting method and the Gauss pseudospectral method, and efficiencies of these two methods are compared and analyzed; 3) A solving strategy of two-steps conversion of cost functions is designed. With this strategy, the large-angle optimal attitude path for space station is obtained, which consumes no propellant and uses least energy, with the geometry constrain satisfied.The key parameters analysis and optimization of zero-propellant maneuver are finished. 1) The influence on performance criteria caused by the key parameters is analyzed. The key parameters contain maneuver time, orbit elements, configuration and environment parameters. The performance criteria contain the peak momentum of control torque gyroscopes, the maximal control torque and energy consumption; 2) Defining the key parameters as optimal variables, the single parameter and multi-parameter optimization problems of zero-propellant maneuver are solved; 3) Physical programing method is used to solve the multi-objective optimal parameters and attitude path that satisfies different preference structures.The simulation demonstration of zero-propellant maneuver based on Simulink is executed. 1) The zero-propellant maneuver simulation model is designed and established, and the parameters initialization, attitude dynamics and control, space environment and data display modules are constructed; 2) The simulation demonstration of zero-propellant large-angle attitude maneuver based on Simulink is executed.With the background of the Chinese Space Station project, this dissertation investigates the analysis theory and design method of zero-propellant large-angle attitude maneuver. The dissertation provides some new thoughts and approaches for the large-angle maneuver of space station and large-scale spacecrafts. The research results have practical significance for reducing fuel consumption, prolonging on-orbit time and enhancing the safety of space station.