The Attack Orbit Optimization Of Space Attack And Defense

The development of space technology is extremely rapid,and the role of space platform in information warfare is becoming more and more obvious.All countries are vigorously developing space technology and space weapons in order to enhance their own status in the information war.In this paper,the space attack and defense in the use of anti-satellite interception as the background,to intercept satellite attack orbit planning and control methods are studied.First of all,aiming at the orbital optimization problem of intercepting satellite attack under the "single-single" situation,this paper uses the impulsive satellite equipped with pulse rocket and continuous thrust satellite equipped with electric propulsion as the object to orbit optimization problem.The dynamic defense model of the target satellite is established.According to the characteristics of the orbital,the impulsive thrust model is transformed into the characteristic velocity of the intercepting satellite.The continuous small thrust model is simplified as the attitude angle of the propulsion system of the intercepting satellite in the reference orbit coordinate system.A variable length real number genetic code is designed.The genetic algorithm genetic algorithm and fitness function are optimized,and the feasibility of genetic algorithm is verified by simulation.Secondly,in order to solve the orbiting problem of intercepting satellite coordinated attacks in the "multi-multi" situation,a multi-star cooperative orbit planning method based on adaptive genetic algorithm is proposed.The time required for the intercepting satellite team to arrive at the target location is assumed to be a co-variable;the security of the attacking orbit is a collaborative constraint;and the path cost function is a synergistic function.Achieve multiple interception of satellites hit the target at the same time,improve the overall combat effectiveness and mission success rate.In addition,the operation parameters and genetic operators of genetic algorithm are optimized,and the adaptive ability of the algorithm is improved.Simulation shows that this method can meet the requirements of interception tasks.Thirdly,aiming at the orbit optimization problem of intercepting satellites with maneuvering escape,a co-evolutionary algorithm is proposed to solve the problem of three-dimensional space pursuit of two spacecraft with fixed confrontation time.According to Nash equilibrium,the complicated bilateral optimal programming problem can be transformed into a search for Nash equilibrium,which simplifies the system model.Taking the relative distance of two spacecraft as the payment function,the fitness function of the algorithm is established and the cooperative operator is improved.The trajectory of two spacecraft escape routes under coplanar orbits and the orbital orbits are simulated and analyzed respectively.At the same time,the changes of the two controlled accelerations over time are obtained.Simulation results show that when the two opposing sides are coplanar orbit,the optimal pursuit strategy is still generated in the coplanar orbit.Finally,when using electromagnetic interference to destroy the target satellite communication system,it is necessary to stop the intercepting satellite near the target satellite.In view of the orbit planning problem of sustained hovering orbiting interference and the control force equation and fuel consumption estimation of hovering orbit configuration,the system is approximated by the power series method under the constant thrust.Under the condition of a certain hovering distance,the optimal position of spacecraft hovering is calculated by the genetic algorithm based on the principle of optimal fuel consumption,so as to calculate the control force needed to maintain the configuration.Based on the open-loop control,the feedback control law is designed by using LQR control to realize the relative position of the two spacecraft during the hovering and accurate control of relative speed.The simulation verifies that the hovering orbit control method proposed in this paper has certain anti-interference ability.