Mission Planning And Orbit Optimization Of Multi-satellite Interception

With the development of aerospace science and technology,people have accelerated the exploration of space.The combat area has also extended from the original land,sea and air to outer space.Competition for space resources has made the research on satellite interception more and more important.In this paper,according to the development trend of the space situation,the interception of multiple evaders by multiple pursuers with multiple defenders is studied,mainly including the task planning and orbit optimization in the interception process.The main research contents are as follows:Aiming at the design of long-range impulsive interception orbit,firstly,the dynamic equations without perturbation terms are established.The Lambert problem is solved by the universal variable method,which avoids the singularity problem when calculating the velocity vector of the transfer orbit.Then,for the design of precise impulsive interception orbit,on the basis of the two-body model,the J2 perturbation and other disturbance terms are added to the dynamic equation,and the differential correction method is adopted.According to the terminal interception constraints,the state-relation matrix is used to iteratively obtain the amount of correction needed for the speed pulse increment at the initial moment.This method can achieve high interception accuracy with reduced computational load.Aiming at the design of long-range continuous thrust interception orbit,considering the maneuvering capability of the evader,the orbital motion equations of the two spacecrafts with J2 perturbation described by state variables are established.Based on the differential game theory,according to the boundary constraints and the performance index function including time and fuel consumption,the conditions for the bilateral optimum corresponding saddle point solution are deduced,and the interception problem when both satellites are maneuvering is converted into two point boundary value problem.The genetic algorithm and sequential quadratic programming algorithm are used to obtain the optimal control strategies of the two satellites during the flight process.This method can solve the problem of interception of maneuvering evaders.Aiming at the interception of multiple evaders by multiple pursuers,and taking into account the mission planning during the avoidance of defenders,a mathematical model for the mission planning of space-based counter-defense systems is established,and the single/multi-impulse attack paths are optimized according to the most fuel-efficien principle.The fuzzy comprehensive evaluation is performed on the factors such as the maneuver velocity,standby threat,preparation time,attack threat,etc.The best attack scheme is obtained based on Borda number ranking.The comprehensive efficiency function is established in combination with the attack benefit,attack cost,fuel consumption,target coverage and damage degree.Based on the Nash equilibrium theory,the evaders and the interception paths are allocated.This method can solve the problem of evaders allocation and interception in complex situations under the condition of ensuring the optimal overall efficiency,and it is able to cope with emergent situations such as damage and other emergencies,and it has strong robustness.Aiming at the optimization of medium-range interception orbit,the relative kinematics equations and differential game models of pursuer and evader,pursuer and defender are established,and the complex multilateral optimization problem is transformed into the search of the Nash equilibrium point.Based on the co-evolutionary algorithm,the fitness function,elite retention mechanism,pursuit strategy,selection,crossover,mutation,and cooperation operator in the process of space pursuit-evasion are designed and the optimal strategies are obtained.This method can solve the problem of two-parties/three-parties confrontation interception.