Initial Relative Orbit Determination And Trajectory Optimization For Non-Cooperative Spacecraft Under Incomplete Measurement

At present,the environment of near-Earth orbit space is increasingly complex,and the problems caused by potential insecurities are increasing.Therefore,in-orbit service tasks such as maintenance and clearance for space non-cooperative targets including failed satellites and space debris are inevitable development directions in the field of national space security technology.The prerequisite for completing the on-orbit service rendezvous is to achieve accurate initial orbit determination and guidance planning.Therefore,this paper is oriented to the space non-cooperative target on-orbit service task under the limited load of service spacecraft,and studies the initial relative orbit determination and rendezvous guidance technology under the condition of incomplete measurement information.Firstly,an initial relative orbit determination method based on camera bias is studied.An angle measurement model based on the centroid installation of the spacecraft is established.The initial orbit determination algorithm based on camera bias is derived.Then,an improved accuracy of orbit determination by state quantity is proposed.The orbital algorithm performs Monte Carlo simulation on the two orbit determination algorithms respectively,and verifies the effectiveness of the algorithm and analyzes the influence of different factors on the orbit determination results.Then,a ranging-only initial relative orbit determination algorithm based on the TOA(Time of Arrival)offset of radio communication is derived.The only ranging measurement model of the distance measuring sensor deviating from the centroid of the spacecraft is established.The problem of orbital ambiguity in the case of ranging measurement is mathematically explained,and the non-periodic is studied by the introduction of the receiver's deviation from the centroid rod arm effect.The relative orbital analysis method and the attitude rotation analysis method for periodic relative orbit determination are carried out.The simulation and performance analysis of the proposed orbit determination algorithm are carried out by numerical simulation experiments.Finally,the trajectory optimization method in the process of non-cooperative target rendezvous is constructed.Based on the reconciliation guidance model of the double-pulse maneuver strategy,the genetic algorithm is used to optimize the optimal trajectory planning problem with the best fuel consumption,and the optimal intersection trajectory and guidance are obtained.The maneuvering pulse sequence was simulated and verified by numerical simulation test.