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Apogee ignition high-precision analytical orbit autonomous prediction method

An apogee, high-precision technology, used in adaptive control, instrumentation, control/regulation systems, etc., to solve problems such as the inability to provide orbital calculation information autonomously

Active Publication Date: 2016-02-17
BEIJING INST OF CONTROL ENG
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Problems solved by technology

This phenomenon is mainly due to the fact that the satellite cannot independently provide accurate and fast orbit calculation information during the transfer orbit segment, especially during the apogee ignition, so it can only rely on the ground personnel to calculate the attitude by injecting attitude fitting coefficients in each ignition arc. information

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  • Apogee ignition high-precision analytical orbit autonomous prediction method
  • Apogee ignition high-precision analytical orbit autonomous prediction method
  • Apogee ignition high-precision analytical orbit autonomous prediction method

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Embodiment Construction

[0064] The invention provides a high-precision orbit autonomous prediction method, which can realize autonomous calculation of orbit information on the satellite during apogee ignition without ground interference, reduces the risk of operational errors by measurement and control personnel, and improves system reliability. If the method of the present invention is selected, if the ignition time lasts for 1.5 hours, the orbit prediction position error on the satellite is less than 3km. Since the analytical method is selected for solution (the perturbation term of the maneuvering force calculated by S, T, W in step 6 belongs to the second type without singularity root, and belongs to the known technology in the field), it does not involve numerical integration, which is fast and effective, and saves Calculate the cost. At the same time, the analytical form of the orbital equation has a clear physical meaning, and the changes of each orbital element can be clearly seen (the analyti...

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Abstract

The invention relates to an apogee ignition high-precision analytical orbit autonomous prediction method. Orbit information of each phase of a transfer orbit including apogee ignition can be accurately calculated. The second type of nonsingular orbital elements are selected for recurrence so as to be suitable for the situations of small orbit inclination angles and low eccentricity. Therefore, the apogee ignition high-precision analytical orbit autonomous prediction method is also suitable for orbit calculation of each phase of a synchronous orbit and has great significance.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude and orbit control, and relates to a method for autonomous calculation of on-planet orbits during apogee ignition of GEO spacecraft transfer orbits. Background technique [0002] Before and after the apogee ignition of the traditional GEO spacecraft transfer orbit, the satellite cannot provide orbit information independently, and the control accuracy largely depends on the accuracy of the attitude fitting coefficient calculated by the ground measurement and control personnel. Specifically, before ignition, the ground measurement and control personnel need to use the ground orbit information to calculate the yaw and attitude determination fitting coefficient, and inject it on the star, and realize the yaw axis maneuver through the yaw too sensitive; then obtain the attitude measurement through gyro integration At the same time, inject the attitude offset value, let the star rotate 90 degrees aroun...

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Application Information

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IPC IPC(8): G05B13/02
CPCG05B13/0225
Inventor 乔国栋黎康汤亮史晓霞彭洲
Owner BEIJING INST OF CONTROL ENG
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