Flywheel angular momentum autonomous unloading method based on discrete jet

A technology of angular momentum unloading and angular momentum, which is applied in the direction of aerospace aircraft, aircraft, motor vehicles, etc., can solve the problems of difficulty in accurate calculation of interference torque, increased ground management dependence, and difficulty in the design of regular angular momentum unloading. The effect of orbital autonomous operation capability

Active Publication Date: 2019-04-16
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

For large satellites with complex structures, it is difficult to accurately calculate the disturbance moment, and the periodic unloading design of the diagonal momentum brings great difficulties, and at the same time increases the dependence on ground management

Method used

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  • Flywheel angular momentum autonomous unloading method based on discrete jet
  • Flywheel angular momentum autonomous unloading method based on discrete jet
  • Flywheel angular momentum autonomous unloading method based on discrete jet

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Embodiment Construction

[0025] In order to better clearly express the technical solution of the present invention, the present invention will be further described below in conjunction with the accompanying drawings.

[0026] figure 1 A specific embodiment of the present invention is shown, a method for autonomous unloading of flywheel angular momentum based on discrete jets. Specifically, include the following steps:

[0027] First, enter step S101 to calculate the angular momentum of the satellite body: according to the flywheel configuration on the star, calculate the angular momentum of each flywheel by using the current rotation speed of the flywheel, and calculate the angular momentum provided by the flywheel on the satellite body in combination with the installation layout of the flywheel.

[0028] Then, enter step S102, determine the flywheel angular momentum unloading threshold: determine whether to perform angular momentum unloading, the flywheel angular momentum unloading threshold include...

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Abstract

The invention provides a flywheel angular momentum autonomous unloading method based on discrete jet, which comprises the following steps of: calculating the angular momentum of a satellite body; determining a flywheel angular momentum unloading threshold; calculating the duration of each jet of an unloading thruster; calculating the interval time of each unloading jet of the thruster; calculatingthe number of times of unloading jet of the thruster. The angular momentum of the satellite is calculated according to the rotating speed of the flywheel, and according to the installation layout ofthe thruster and the requirements of the satellite attitude control precision and stability, the thruster for unloading is selected, the jet time width, jet interval time and times of jet of the thruster are selected. The method is based on independent angular momentum unloading technology of discrete point spraying of the thruster, can ensure that the angular momentum unloading is automatically achieved on the premise of meeting the attitude control precision, and improves the satellite on-orbit autonomous operation capability.

Description

technical field [0001] The invention belongs to the technical field of attitude control of geostationary orbit satellites, in particular to a method for autonomous unloading of flywheel angular momentum based on discrete jets. Background technique [0002] In order to ensure the long-term stable operation of the payload on the satellite, the flywheel is used as the actuator of the attitude control system during the long-term orbital operation of the satellite. Affected by the external disturbance torque, the angular momentum of the flywheel accumulates continuously over time. When the angular momentum of the flywheel reaches When it is saturated, the control output capability is lost. Therefore, it is necessary to apply an additional unloading torque to unload the angular momentum of the flywheel to prevent "saturation" of the angular momentum of the flywheel. Considering that the earth's magnetic field in the geostationary orbit is weak, it cannot be unloaded through the ge...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24B64G1/28
CPCB64G1/24B64G1/283B64G1/245
Inventor 郭正勇朱虹王静吉丰保民黄京梅戴维宗修艳红
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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