Method for de-orbiting GEO (geostationary orbit) satellite by using residual propellant and helium gas

Abstract

A method for de-orbiting a GEO satellite by using residual propellant and helium gas comprises the steps: (1) determining an orbit on the ground; (2) performing thrust calibration: thrust calibrationis performed according to an ignition test of a thruster under different conditions, or combined calibration is performed to obtain a first calibrated thrust; 3) judging whether the eccentricity ratioof the orbit meets the de-orbiting requirement or not, and then judging whether the thruster meets the use condition or not; (4) lifting the perigee, lifting the orbit, measuring the orbit again andperforming combined calibration to obtain a second calibration thrust; and (5) judging whether the semi-major axis of the orbit meets the de-orbiting requirement or not, and then judging whether the thruster meets the use condition or not. In a de-orbiting process, the method can fully utilize the residual propellant and helium gas, lift the semi-long axis of the orbit as much as possible, and reduce the threat to other GEO satellites.

Description

technical field [0001] The invention relates to a method for deorbiting a geostationary orbit (GEO) satellite, in particular to the method for deorbiting a GEO satellite under the condition of insufficient propellant. Background technique [0002] According to the recommendations of the international organization IADC, at the end of the life of geostationary orbit (GEO) satellites, in order to reduce geostationary orbit space debris and purify the geostationary orbit space environment, it is recommended to send dying satellites to grave orbits. The increased height of the semi-major axis of the grave track compared to the GEO track should satisfy the following formula, while ensuring that the eccentricity is not greater than 0.003. [0003] ΔH≥235+1000C r A / M [0004] Where ΔH is the increased height of the semi-major axis of the orbit; C r is the reflection coefficient of the satellite surface, and C is used for specular reflection r =2, take C when it is bold r =1; A ...

AI Technical Summary

Problems solved by technology

[0011] (1) The calculation error of GEO satellite propellant is very large

[0012] (2) In the GEO satellite de-orbiting plan, when it is judged by factors such as thruster temperature and attitude telemetry that there is only one kind of bicomponent propellant remaining, it is considered that the propellant has been consumed, and it will start to execute regardless of whether the required orbital altitude is reached. Passivation operation, residual single-component propellant and high-pressure helium in the tank still have the ability to continue to generate thrust but have not yet utilized

[0013] (3) During the de-orbiting process of the GEO satellite, the thrust of the propulsion subsystem may be unstable. Therefore, the control subsystem generally needs to adjust the attitude control threshold and use the thruster to control the orbit and attitude at the same time. The bias momentum of the satellite The wheel system does not play the role of inertial space stability

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