Research On Spacecraft Anti-Rendezvous Evasion Maneuver Method

Space anti-rendevous evasion maneuver is a key technology of space safty, and it will make our satellite escape from enemy’s approaching so that the safty of our spacecraft can be guaranteed. Taking the applications of the spacecraft anti-rendevzous problem as background, this paper will do the rearch on the anti-rendezvous maneuver problem in short distance and final approach respectively. An anti-rendevzous evasion maneuver optimal index and model in short distance based on degree of observability is established, and a final approach anti-rendevzous evasion game analysis method of two-dimensional phase plane and of three-dimensional space are proposed. The main results achieved in this dissertation are summarized as follows.The angles-only relative navigation method and the degree of observability(DOO) expression is dedrived. Taking DOO as evaluation index, single-objective and multi-objective optimization method are used for the short distance anti-rendevzous evasion maneuver optimal direction analysis. 1) The angles-only relative navigation observability model is established, its state equation and observation equation is deduced. By analyzing relative navigation state estimation error, relative motion degree of observability axiom is proposed and the definition of DOO is given. 2) Taking DOO as maneuver optimization index, an anti-rendevzous evasion maneuver single-objective optimization method based on gradient direction is developed. 3) Taking DOO and minimal relative distance as index, and taking evasion maneuver direction and impulse time as optimization variable, the anti-rendevzous evasion maneuver multi-objective optimization model is established. The effectiveness of the optimization results are testified by simulations.A phase plane analysis model of the final approach anti-rendevzous problem without considering gravitation is established, the phase plane relative motion eqution is dedrived, the definition of capture region and escape region is given and the optimal evasion maneuver direction is acquired. A new theory analysis method of the final approach anti-rendevzous evasion game problem is purposed. 1) Based on the existing IRPL relative motion model, theoretical mechanics methods is used to derive the differential equations under MPC coordinate system. 2) The definition of zero effort miss(ZEM) is given, and the optimal evasion maneuver direction of the target spacecraft is derived based on ZEM’s derivative. 3) The acceleration of the LOS vertical direction maθand the acceleration along the LOS direction mra ’s expression of approach spacecraft using TPN guidance law are dedrived, and the capture region and escape region are displayed in the two-dimensional phase plane directly.The phase plane analysis mathod of the final approach anti-rendevzous evasion maneuver is developed. A three-dimensional space analysis mathod of the final approach anti-rendevzous evasion maneuver problem considering gravitation is established. The relative motion equation under MPC coordinate system that considering gravitation is dedrived, and the three-dimensional space analysis model of the final approach anti-rendevzous problem is established. 1) The LOS relative motion equation under LOS coordinate system considering gravitation is dedrived, then the relative motion equation under MPC coordinate system considering gravitation is acquired, and the definition of capture region and escape region is given. 2) Based on maθandmra ’s expression of approach spacecraft using TPN guidance law, the three-dimensional space analysis equation are dedrived. The analysis space is partitioned according to the definition of capture and escape region, and the calculating method of space flow line vector direction is given. 3) The definition of three-dimensional space relative motion equation under limited impulse is given. The simulation results show that the three-dimensional space relative motion equation analysis method is effective. Rearch expands the field of application of space relative motion differential equation.In this paper, we do the research on a new conception--anti-rendevzous problem. The calculating model and mathod in short distance and final approach are established. Research can be a reference to our spacecraft orbit safty.