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GEO satellite small thruster propellant consumption coupling analysis method

A small thruster, coupled analysis technology, used in instruments, special data processing applications, electrical digital data processing, etc.

Inactive Publication Date: 2014-09-17
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0005] The purpose of the present invention is to propose a coupling analysis of GEO satellite small thruster propellant consumption in order to solve the coupling relationship between the propellant consumption and the tank size of the GEO satellite small thruster in the transfer orbit stage and the geostationary orbit stage method

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  • GEO satellite small thruster propellant consumption coupling analysis method
  • GEO satellite small thruster propellant consumption coupling analysis method
  • GEO satellite small thruster propellant consumption coupling analysis method

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Embodiment Construction

[0082] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0083] In this embodiment, the satellite platform has a total of 8 small thrusters, which can realize fixed-point position maintenance and three-axis attitude control of 4 azimuths through their respective combinations. The 8 small thrusters (1A, 2A, 3A, 4A, 1B, 2B, 3B , 4B) installed on the 8 corners of the cuboid-shaped satellite platform, the installation position is as follows figure 1 shown. The installation angles of the eight small thrusters are shown in Table 1, and the combinations of the small thrusters are shown in Table 2.

[0084] In this embodiment, the number of orbit changes of the satellite is 5 times, and the speed increment required each time is [461.2, 404, 584, 170, 102] (m / s). During orbit change, the X, Y, and Z three-axis disturbance torque due to thrust eccentricity is [6, 6, 0.02] (N·m).

[0085] Table 1 Installat...

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Abstract

The invention relates to a GEO satellite small thruster propellant consumption coupling analysis method, and belongs to the technical field of satellite platform overall design. According to the method, the coupling relation between the consumption of propellant at different stages and the radius of a storage box is considered, the position of the mass center of the propellant is updated according to the current stage of a satellite, and the north-south station keeping and east-west station keeping thrust provided by a small thruster and the accuracy of control torque are obviously improved. In the propellant consumption calculating process, the propellant needed by adopting an unloading disturbance torque portion of the small thruster is estimated, a propellant consumption estimating model is made to conform to an actual engineering task, and the model accuracy and actual engineering capacity are improved. Meanwhile, the positions of the propellant in the storage box are different in the static rail stage station keeping process and the transfer orbit stage, different mass center calculating methods are provided, the precision of a position protection thrust and control torque calculating model is improved, and the calculating precision of the consumption of the propellant of a satellite in a full service life period can be improved.

Description

technical field [0001] The invention relates to a GEO satellite small thruster propellant consumption coupling analysis method, which belongs to the technical field of satellite platform overall design. Background technique [0002] The gravitational effect of the sun and the moon will cause the north-south inclination perturbation of the geosynchronous orbit (Geostationary Orbit, GEO) satellite, and the non-standard spherical shape of the earth will cause the east-west perturbation of the GEO satellite. Therefore, during the lifetime of the satellite, GEO satellites usually use North-South Station Keeping (NSSK) and East-West Station Keeping (EWSK) to counteract orbital perturbations. Many experts and scholars at home and abroad have proposed different strategies for the NSSK and EWSK combination strategies of GEO satellites. Now the aerospace industry is increasingly using electric / ion thrusters for orbital position maintenance, mainly due to its high propellant efficienc...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 刘莉彭磊龙腾郭晓松史人赫
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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