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Geo-synchronous orbit satellite apogee orbit transferring method based on inertial pointing mode

A geosynchronous orbit and apogee technology, applied in the field of satellite control, can solve problems such as limiting the satellite launch window

Active Publication Date: 2019-03-12
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 pointin

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  • Geo-synchronous orbit satellite apogee orbit transferring method based on inertial pointing mode
  • Geo-synchronous orbit satellite apogee orbit transferring method based on inertial pointing mode
  • Geo-synchronous orbit satellite apogee orbit transferring method 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 Deficiencies 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. Such as 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 : T...

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Abstract

The invention relates to a geo-synchronous orbit satellite apogee orbit transferring method based on an inertial pointing mode, which comprises the following steps of: firstly, establishing a J2000 geocentric inertial system, a J2000 quasi-inertial coordinate system, a satellite body coordinate system, a southeast geodetic coordinate system and an orbit coordinate system, measuring and calculatingto obtain conversion matrixes among the coordinate systems, and calculating a three-axis target attitude of the geo-synchronous orbit satellite under the J2000 quasi-inertial system, finally calculating the difference between the current three-axis target attitude and the target three-axis target attitude, and performing attitude control during the remote ignition period of the geo-synchronous orbit satellite. According to the invention, a star sensor is used for establishing the remote ignition posture, the yawing to see the sun is not required, the requirements on the emission window and orbit entry precision are reduced, the flexibility of ignition timing selection is improved, and the device 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 ...

Claims

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Application Information

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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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