Orbit Rendezvous Guidance Method Based On Relative Motion Equation

In the deep space exploration mission targeting Mars,the significance of spacecraft orbit rendezvous is very broad.It can be used not only for the rendezvous and docking mission of Mars riser and orbiter,but also for the orbit transfer mission of spacecraft,that is,suppose there is a virtual target spacecraft in the target orbit.Considering the particularity of the current guidance method of orbit rendezvous and deep space exploration,the focus is on the intersection guidance method with the intersection time and fuel consumption as the objective function.The deep space exploration mission has a long period and many orbit-changing missions.Compared with the near-earth exploration mission,it greatly increases the demand for fuel.Considering the most energy-saving orbit rendezvous method,the Hohmann transfer orbit rendezvous method with Mars as the center object is studied.The velocity pulses of circular and elliptical orbits are given,and the terminal intersection deviation caused by the initial navigation error(initial angle,orbit radius of the target spacecraft)of the Hohmann transfer is studied,and the actual deviation is given in the simulation example.Since the Hohmann transfer orbit intersection method cannot control the intersection time,the intersection guidance method based on the relative motion equation is studied.The velocity pulse size of the double-pulse guidance based on the Hill equation is given.The deviation of the circular orbit Hill equation is analyzed using covariance,calculating the mean and covariance matrix of the deviation and the effect of the navigation deviation on the Hill guidance is studied.Calculating the speed pulse size at different intersection times through simulation examples,comparing the speed pulse size required by the Homan transfer and the orbit intersection based on the Hill equation,so as to compare how much fuel is consumed,and simulate the navigation position and speed deviation to the terminal intersection The effect of deviation.In order to obtain the analytical solution of the relative motion equation,a series of simplified operations are used in the derivation process to study the influence of the nonlinear second-order term on the relative motion equation,and the equation form with the second-order term is given;the study considers the perturbed orbit Rendezvous guidance,deducing the influence on the rendezvous process through the influence of perturbation force on the number of orbits.This thesis focuses on 2J perturbation and gives the relative state transition matrix with 2J perturbation.Considering the accuracy of the relative motion equation and the navigation deviation,an iterative multi-pulse rendezvous scheme design is proposed to complete the rendezvous task.