METHOD FOR CONTROLLING ORBIT OF SPACE FLYING BODY, AND METHOD FOR ESTIMATING RELATIVE POSITION SPEED

摘要

PROBLEM TO BE SOLVED: To set an orbit correcting maneuver many times during the time from main maneuver to stop maneuver execution and perform a precisely orbit control without the danger of the collision with a rendezvous target by estimating the relative position speed with the rendezvous target by use of a navigation filter having a short converging time. SOLUTION: When a navigation filter 16 is not converged because of an abnormality of a navigation sensor 15 or a communication system until the thruster injection quantity of a rendezvous maneuver 8 is calculated by the induction processing of a loaded computer 17, execution of the maneuver 8 is stopped, and a rendezvous maneuver 9 is executed after the navigation filter 16 is converged. The converging time of the navigation filter is shortened in this way, whereby many rendezvous maneuvers are preliminarily planned, the converting state of the navigation filter is judged, in actual operation, from the elapsed time from the orbit control executed in the latest time or a status flag showing the observation residual of an Karman's filter, and a precise orbit control can be performed without the danger of the collision with a rendezvous target 2.