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Apogee Orbit Change Method for Geosynchronous Orbit Satellites Based on Inertial Pointing Mode

A technology of geosynchronous orbit and apogee, which is applied in the field of satellite control, can solve the problems of limiting the satellite launch window, etc., and achieve the effect of streamlining the flight control process, reducing the workload, and improving the calibration accuracy

Active Publication Date: 2021-11-16
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0003] Before the apogee is ignited, the gyroscope is generally calibrated by using the earth sensor and the digital sun sensor in the earth pointing mode, which requires the angle between the earth, the satellite and the sun to meet certain requirements, thus limiting the satellite launch window

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  • Apogee Orbit Change Method for Geosynchronous Orbit Satellites Based on Inertial Pointing Mode
  • Apogee Orbit Change Method for Geosynchronous Orbit Satellites Based on Inertial Pointing Mode
  • Apogee Orbit Change Method for Geosynchronous Orbit Satellites Based on Inertial Pointing Mode

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Embodiment Construction

[0045] The present invention overcomes the deficiencies of the prior art, provides a geosynchronous orbit satellite apogee orbit change method based on the inertial pointing mode, and solves the problem of using the earth sensor and the digital sun sensor to calibrate the gyroscope in the prior art, which requires the angle between the earth, the satellite and the sun Defects that meet certain requirements, through the use of star sensitivity to establish apogee attitude, there is no requirement for the angle between the earth, satellites and the sun, and the constraints of the satellite launch window are reduced. The method of the present invention will be described in detail below in conjunction with the accompanying drawings. like figure 2 Shown is a flow chart of the present invention, and the method of the present invention includes the following steps.

[0046] 1. Definition of coordinate system

[0047] (1) J2000 Geocentric Inertial System OX i Y i Z i : The coord...

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Abstract

The apogee orbit change method of geosynchronous orbit satellites based on the inertial pointing mode, first establishes the J2000 geocentric inertial system, the J2000 quasi-inertial coordinate system, the satellite body coordinate system, the southeast earth coordinate system, and the orbit coordinate system, and then measures and calculates the coordinates of each coordinate system The transformation matrix between them, and calculate the three-axis target attitude of the geosynchronous orbit satellite in the J2000 quasi-inertial system, and finally calculate the difference between the current three-axis target attitude and the target three-axis target attitude, and carry out the geosynchronous orbit satellite during the apogee ignition period Posture control. The invention utilizes the star sensor to establish the apogee ignition attitude, does not require the yaw sun to be visible, reduces the requirements on the launch window and the accuracy of orbiting, improves the flexibility of ignition timing selection, and has good use value.

Description

technical field [0001] The invention relates to the field of satellite control, in particular to an apogee orbit changing method for a geosynchronous orbit satellite based on an inertial pointing mode (IPM, Inertial Pointing Mode). Background technique [0002] At present, for geosynchronous orbit satellites such as the Dongsan and Dongsi platforms, the rockets send the satellites into the transfer orbit, and it is necessary to perform multiple orbit control after the satellite and rocket are separated. The orbit control task is an important part of the satellite flight control work. [0003] Before the apogee is ignited, the gyroscope is generally calibrated by using the earth sensor and the digital sun sensor in the earth pointing mode, which requires the angle between the earth, the satellite and the sun to meet certain requirements, thus limiting the satellite launch window. There is no requirement for the angle between the earth, the satellite and the sun by using the ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 吴小明林波彭坤王佐伟刘江杨帆蔡君亮尹静孙旻昊
Owner BEIJING INST OF CONTROL ENG
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