Satellitic self-determination orbital transfer method

Abstract

The invention relates to an independent orbital transfer of a satellite, comprising (1) star capture step, in which before the satellite establishes orbit-controlled ignition attitude, inertia attitude of the satellite is pre-estimated and satellite attitude is controlled; zero offset of gyro drift and an accelerometer is marked; (2) inertia attitude regulation step, used for establishing the orbit-controlled ignition attitude of the satellite, realizing maneuver of the satellite attitude, pre-estimating the inertia attitude of the satellite and a jet control is used for controlling the satellite attitude; (3) star orientation step, in which after the satellite establishes the orbit-controlled ignition attitude, a stable state control is carried out and a star sensor is used for filtering and correcting the satellite attitude; and (4) orbit-controlled orientation step, in which starting and shutdown control is carried out for a rail-controlled engine; the ignition attitude of the satellite is determined and attitude stable control is carried out in the period of the ignition. The invention solves the problem that spacecraft such as a deep space exploitation satellite transfers orbit, and ensures that the orbital transfer can be completed accurately and reliably.

Description

technical field [0001] The invention relates to a method for autonomous orbit changing of a spacecraft, which is suitable for accurate and autonomous orbit changing of spacecraft such as deep space exploration satellites. Background technique [0002] There are many methods for satellites to independently implement orbit changes. Among them, the orbit change of the medium and low orbit ground-oriented satellites is generally carried out under the normal ground-to-ground attitude. The orbit change method is relatively simple. The on-off time of the orbit-change engine is injected from the ground, and the on-board engine is turned on and off according to the time. Satellite orbit control can be realized. It does not involve too many stages or stage transitions such as attitude maneuvering and attitude adjustment, but in deep space exploration satellites, the orbit change method of low- and medium-orbit satellites is no longer applicable, and it is necessary to solve complex a...

AI Technical Summary

Problems solved by technology

It does not involve too many stages or stage transitions such as attitude maneuvering and attitude adjustment, but in deep space exploration satellites, the orbit change method of low- and medium-orbit satellites is no longer applicable, and it is necessary to solve complex attitude determination and control before and after orbit change. program for reliable track change

[0003] The fixed-point orbit change control of the geostationary orbit satellite mostly adopts the ground control method, and the ground controls the satellite from the cruising attitude (the +X-axis orientation attitude of the satellite) to the ignition attitude, and the infrared earth sensor and the sun sensor are used in the control Attitude determination is performed on the data of the satellite, and the satellite attitude determination accuracy in the orbit control process is not high, which affects the orbit control accuracy

This method requires a large number of control calculations on the ground, and the ground operation is more complicated, and the on-off operation of the orbit control engine is also completed by the ground, and the transmission link delay of the ground command will also affect the orbit control accuracy.

Thus affecting the uniqueness of the orbit control window (timely and accurate implementation of orbit control)

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