Research On Orbit Maneuver Problem For Multi-target Visit With A Single Impulse

With the development of technology and the increasing number of spacecraft,space multi-target visit technology has more and more important application value in space attack and defense,on orbit services and other space missions.At present,in the research on space multi-target visit,the relevant theoretical methods used are usually based on one or multiple impulses visiting a single target.However,visiting multiple space targets with a single impulse can improve mission efficiency and reduce the consumption of ground telemetry and telecontrol resources.This thesis studies the orbital maneuver method of spacecraft visiting multiple space targets with a single impulse maneuver,mainly including the following contents:For the reachable domain of spacecraft under the condition of visiting a given target,the coplanar orbit and the nonplanar orbit of spacecraft and target are studied.For the coplanar orbit case,the necessary conditions that the reachable domain boundary needs to meet are derived.Firstly,based on the geometric characteristics of the orbit,a method to quickly determine the feasible ranges of impulse time and visit time is presented.Then,by solving the extreme values and boundary values of multivariate function in the feasible ranges,the maximum values of visit trajectory in all phase directions are determined,and the boundary of reachable domain is solved.A comparative simulation example is given to verify the effectiveness and superiority of the method;For the case of nonplanar orbit,a detailed analysis and description of the expression form of the reachable domain is made firstly,and then the variable angle of the orbit plane is determined through the impulse magnitude constraint.Then for any orbital plane within the variable angle range,by using spatial geometry analysis and combined with Kepler equation,a method to quickly solve the feasible orbits is given.Finally all the feasible orbits can be gotten by traversing the impulse time and the variable angle.The effectiveness of the method is verified by simulation.For the problem of visiting multiple space targets under absolute motion with a single impulse maneuver,a dimensionality reduction solution strategy based on Lambert problem and Gibbs’three-vectors orbit determination theory is proposed.Firstly,the constraint conditions and free variables of the problem are analyzed and discussed in detail,and the problem is divided into coplanar and nonplanar orbits.For the two-target visit case in coplanar orbit,the dimension of the constraint equations of the problem is reduced from 4 to 2;For the three-target visit case in coplanar orbit and two-target visit case in nonplanar orbit,the dimension of the constraint equations of the problem is reduced from 6 dimensions to 2 dimensions.It effectively reduces the difficulty of problem solving.Further,the initial values of iterative process are provided by the grid method,and the Newton iterative method is used to solve the problem.And for different cases,based on the solution of the two-body model,homotopy method and differential correction strategy are applied to get the solutions under₂perturbation model.For the problem of visiting multiple space targets under relative motion,based on linear Clohessy-Wiltshire（CW）and Tschauner-Hempel（TH）equations,an orbit design method for visiting multiple relatively fixed position targets is proposed.By the proposed method,the Gibbs three-vector orbit determination theory in absolute motion is extended to relative motion space.Firstly,considering that the main satellite orbit is circular or elliptic,and the target orbit is coplanar or different from the main satellite orbit,the problem is divided into four cases,and the number of constraint equations and free variables are discussed.Through the linear relative motion equations and periodic revisit constraints,the dimension of the problem in different cases is reduced from 4 to 6 dimensions to1 or 2 dimensions,and numerical solutions process is carried out by segmented golden section+secant method and grid method+Newton iteration method,which effectively reduces the complexity of the solution.Then,based on the method proposed for the relatively fixed position targets,the orbital maneuver method for visiting the relatively moving targets is studied and used to solve the problem.For each case,based on the average orbital elements,the corresponding results under₂perturbation are obtained by differential correction strategy.Finally,the correctness and effectiveness of the method are verified by simulation.