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Method for detecting fault of electric propulsion satellite in geostationary orbit and position maintaining method thereof

A technology for geostationary orbit and satellite faults, which is applied in electrical digital data processing, special data processing applications, instruments, etc., and can solve the problems of lack of failure mode position retention scheme, failure to consider thruster fault detection, etc.

Active Publication Date: 2018-12-21
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The current position keeping strategy does not consider the thruster failure detection link, and lacks a set of failure mode position keeping schemes with two functions of failure detection and drift elimination

Method used

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  • Method for detecting fault of electric propulsion satellite in geostationary orbit and position maintaining method thereof
  • Method for detecting fault of electric propulsion satellite in geostationary orbit and position maintaining method thereof
  • Method for detecting fault of electric propulsion satellite in geostationary orbit and position maintaining method thereof

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Embodiment 1

[0187] Such as figure 1 As shown, this embodiment discloses a fault detection method for geostationary electric propulsion satellites. In order to verify the method, firstly, a satellite operating in geostationary orbit is selected as the main research object. The start time of the simulation is 0:00:00 (Universal Time) on January 1, 2020. The basic parameters of the satellite are shown in the table below.

[0188] Table 1 Satellite parameters

[0189]

[0190]

[0191] Step 1: Establish the instantaneous orbital motion model of the geostationary satellite under environmental perturbation through the Lagrange planetary motion equation, and the environmental perturbation includes the earth's non-spherical perturbation R ENP , sun and moon gravitational perturbation R LSP , solar light pressure perturbation R SRP . ;

[0192] When classical orbital elements describe the orbital motion of GEO satellites with small inclination and small eccentricity, singularity problem...

Embodiment 2

[0224] Such as figure 2 As shown, on the basis of the fault detection method of a geostationary orbit electric propulsion satellite, this embodiment also discloses a position keeping method of a geostationary orbit electric propulsion satellite failure mode, including the geostationary orbit electric propulsion satellite The steps one to five of the satellite failure detection method also include steps six to nine. For verifying the method, the parameters selected in the first five steps are consistent with embodiment 1, and steps six to nine are as follows:

[0225] Step 6: Calculate the orbit drift caused by thruster failure by filtering method;

[0226] As a preference, the filtering method described in step 6 is preferably an unscented Kalman filtering method, and the specific implementation methods of the steps are shown in formulas (39)-(43).

[0227] In this example, the initial value of the state covariance matrix is ​​set as shown in formula (59):

[0228] P=diag(1...

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Abstract

The invention belongs to the field of spacecraft orbit dynamics and control. The invention discloses a fault detection method of a geostationary orbit electric propulsion satellite, which is realizedby establishing an instantaneous orbit motion model of the geostationary orbit satellite under environmental perturbation. the average orbital motion model is established; the orbital motion model under the action of the controlled force is established. The orbital motion model under all forces is deduced. The fault detector is designed and the convergence of the designed fault detector is verified. The invention also discloses a position maintaining method of a failure mode of a geostationary orbit electric propulsion satellite. On the basis of the satellite failure detecting method, the orbit drift caused by the failure of a thruster is calculated. A control law is designed to correct the orbital drift caused by thruster failure. The discrete control law is used to obtain the switching sequence of the electric thruster. By using the switching sequence, the position maintenance of the GEO electric propulsion satellite in the failure mode is realized. The invention is universally applicable to high-orbit and geostationary orbit electric propulsion satellites.

Description

technical field [0001] The invention relates to a fault detection method and position maintenance method of a geostationary orbit electric propulsion satellite, in particular to important technologies such as thrust fault detection and position maintenance of a geostationary orbit electric propulsion satellite, and belongs to the field of spacecraft orbit dynamics and control. Background technique [0002] Geostationary Orbit (GEO) refers to a special geosynchronous orbit with an orbital height of 35786km and an inclination of zero. The spacecraft operating in the geostationary orbit are usually large and complex spacecraft with high cost, high power, long life, and high precision. They have the characteristics of large coverage area and are stationary relative to the ground. Military and civilian fields such as meteorology and data relay play an important role, and their economic value is very high. [0003] The orbital motion of GEO satellites is mainly affected by three ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 张景瑞李林澄李延艳赵书阁
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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