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An Autonomous Orbit Control Method Based on Autonomous Calibration for Satellite Semi-major Axis Keeping

A semi-major axis and orbit control technology, which is applied in space navigation equipment, space navigation aircraft, space navigation equipment and other directions to achieve the effect of improving accuracy and improving autonomous survivability.

Active Publication Date: 2022-04-22
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, under certain requirements, when the delay of the ground telemetry and remote control method does not meet the real-time requirements, the satellite must have the ability of autonomous orbit determination and autonomous orbit control, and no similar autonomous orbit control method has been found in the prior art

Method used

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  • An Autonomous Orbit Control Method Based on Autonomous Calibration for Satellite Semi-major Axis Keeping
  • An Autonomous Orbit Control Method Based on Autonomous Calibration for Satellite Semi-major Axis Keeping
  • An Autonomous Orbit Control Method Based on Autonomous Calibration for Satellite Semi-major Axis Keeping

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Embodiment 1

[0035] The present invention is a satellite semi-major axis-based autonomous orbit control method based on autonomous calibration. The method first performs real-time satellite orbit calculation based on GNSS measurement or orbit extrapolation calculation; secondly, according to the nominal orbit semi-major axis bound on the star and real-time calculation Compared with the satellite average orbit semi-major axis, when the error is greater than the autonomous orbit control threshold for N consecutive times, the autonomous thrust calibration and the calculation of the autonomous orbit control amount are carried out. According to the real-time measurement of the pressure sensor and the temperature of the storage tank, the real-time autonomous calibration of the satellite mass and the orbit control thrust is carried out, and then the orbit control duration is calculated according to the error between the semi-major axis of the target orbit and the semi-major axis of the real flat or...

Embodiment 2

[0061] A method for maintaining autonomous orbit control based on the semi-major axis of satellites based on autonomous calibration. The satellite is in a sun-synchronous orbit at 10:30 when the satellite is operating at a height of 500 kilometers and the descending node for a long time. The method of application example 1 is implemented as follows:

[0062] 1) Real-time satellite orbit calculation based on GNSS measurement or orbit extrapolation calculation.

[0063] Mean orbital semi-major axis for the current period

[0064] 2) Allows for autonomous orbit control calculations, the nominal orbital semi-major axis a bound on the star normal It is 6888.1400000000003 (km). because The error is greater than Δa for 30 consecutive times lim =5 (km), carry out the following steps 3) to 5) for real-time autonomous thrust calibration and autonomous orbit control calculation.

[0065] 3) According to the real-time measurement of the pressure sensor and tank temperature, the sat...

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Abstract

A satellite semi-major axis-maintaining autonomous orbit control method based on autonomous calibration, which belongs to the field of spacecraft orbit control. Firstly, real-time satellite orbit calculation is performed based on GNSS measurement or orbit extrapolation calculation; secondly, according to the nominal orbit semi-major axis bound on the star Compared with the satellite average orbit semi-major axis calculated in real time, when the error is greater than the autonomous orbit control threshold for N consecutive times, the autonomous thrust calibration and the autonomous orbit control amount calculation are performed. According to the real-time measurement of the pressure sensor and the temperature of the storage tank, the real-time autonomous calibration of the satellite mass and the orbit control thrust is carried out, and then the orbit control duration is calculated according to the error between the semi-major axis of the target orbit and the semi-major axis of the real flat orbit, and the apogee time is selected As the central moment of track control start-up, the Q Pre The apogee position after the lap is set as the central moment of the orbit control start-up, and then the start-up and shutdown time of the de-orbit control thruster are determined. The method of the invention greatly improves the autonomous orbit control capability of the spacecraft.

Description

technical field [0001] The invention relates to an autonomous orbit control method for satellite semi-major axis maintenance based on autonomous calibration, and belongs to the field of spacecraft orbit control. Background technique [0002] At present, the existing orbit determination and orbit control of satellites adopt the method of ground telemetry and remote control. The ground station is used to track the satellite within the visible arc and perform data processing to obtain information such as the orbit attitude of the satellite. At the same time, according to the mission requirements, the The remote control command is uploaded to the satellite to realize the corresponding control operation. However, under certain requirements, when the delay of the ground telemetry and remote control method does not meet the real-time requirements, the satellite must have the ability of autonomous orbit determination and orbit control, and no similar autonomous orbit control method ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/36
CPCB64G1/242B64G1/36
Inventor 王淑一刘洁雷拥军陆栋宁丁建钊王晋鹏程莉刘彤李晶心何世民
Owner BEIJING INST OF CONTROL ENG
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