Fuel Optimization Of Orbit Control Around Irregular Asteroid

Asteroid exploration an important part of deep space exploration.The mechanical environment near the celestial body is difficult to characterize,according to the irregular gravitational field of the irregular asteroid.The open-loop control system is sensitive to initial value.And the preset orbits of designing orbits for such gravitational fields are not accurate enough.There is control redundancy in the closed-loop control system.But fuel is the basis of detection task.Reducing fuel consumption can effectively extend the working life of the probe and increase scientific returns.Based on the above reasons,this article introduces the basic gravitational model and dynamic model of the orbital simulation of irregular asteroids.Considering the nonlinear and high-dimensional problems that may be encountered in orbital simulation,heuristic algorithms are used for fuel optimization.In view of the shortcomings of the heuristic algorithm,we proposed a Q-learning based cuttlefish optimization(QL-CFO)algorithm which is combined the multiple strategies of cuttlefish optimization(CFO)algorithm and strategy optimization of reinforce learning.Compared with the CFO algorithm,it is of faster convergence and higher calculation accuracy.The Kalman filter based particle swarm optimization(K-PSO)algorithm is fast in calculation but premature convergence.We proposed a particle filter based on particle swarm optimization(P-PSO)algorithm.Combining the advantages of proposed PPSO algorithm and K-PSO algorithm,we proposed a hybrid Kalman filter and particle filter based particle swarm optimization(HKP-PSO)algorithm.Compared with other related optimization algorithms,the proposed HKPPSO algorithm does not sacrifice time complexity but achieves better calculation accuracy.With the goal of minimum fuel consumption,the QL-CFO algorithm is used to optimize the orbit parameters of the probe.Following the redesigned optimal fuel consumption performance index,the HKP-PSO algorithm is used to optimize the orbital control system.These are verified through simulation experiments.