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Autonomous formation flight control method for satellites

A formation flight and control method technology, applied in attitude control and other directions, can solve problems affecting the accuracy of orbit control speed increment execution

Active Publication Date: 2014-11-12
BEIJING INST OF CONTROL ENG
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Problems solved by technology

If the thruster is used for attitude control, the speed increment generated by the attitude control will seriously affect the execution accuracy of the orbit control speed increment

Method used

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  • Autonomous formation flight control method for satellites
  • Autonomous formation flight control method for satellites
  • Autonomous formation flight control method for satellites

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Embodiment Construction

[0086] The formation flight of multiple satellites can complete the functions that a single satellite cannot complete. Formation flight requires a certain distance between satellites. In practice, when the initial orbits of the two satellites deviate and the perturbation effects on the satellites are slightly different, the configuration of the formation will change. At this time, it is necessary to design a maintenance control strategy for the formation configuration so that the relative positions between satellites meet the requirements of the mission.

[0087] The satellite's instantaneous orbital element describes the satellite's orbital state at a certain instant. The theory of orbital root number decomposes the change of satellite orbital root number according to different characteristics such as long-term change, short-period change, and long-period change. The long-term variation part and the long-period variation part express the variation characteristics of the orb...

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Abstract

The invention discloses an autonomous formation flight control method for satellites. Formation flight control is carried out through relative orbit mean elements, and due to the fact that a long-term trend of relative movement between the satellites is accurately reflected through the relative orbit mean elements, long-term changes of the relative movement can be well controlled with the method. The autonomous formation flight control method is characterized in that a mean semi-major axis difference control strategy in an orbital plane is designed, the mode that control targets are set in a partitioned mode is adopted, and it is guaranteed that the drift speeds within control zones are low; when outside the control zones, the control targets can return to the control zones at high speeds. According to the autonomous formation flight control method, due to the mode that small-pulse air injecting is used for orbit control multiple times, and a momentum wheel is used for posture control, influences of posture air injection control on orbits are reduced, and the orbit control execution accuracy is improved.

Description

technical field [0001] The invention relates to a satellite autonomous formation flight control method, which is suitable for the control of satellite long-term formation flight. Background technique [0002] When describing the relative motion between two satellites flying in formation, the C-W equation after linearization is generally used to describe. When controlling the formation, the C-W equation is also used to calculate the control quantity. However, some recent research results show that the C-W equation is not accurate in describing the long-term motion trend of the formation when describing the relative motion. The orbital element difference (also known as the relative orbital element) description method developed in the past 10 years can better describe the long-term relative motion trend and can be used for orbit control of formation flight. However, there are few studies on how to calculate orbital element differences from measurement data in the existing lit...

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Application Information

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IPC IPC(8): G05D1/08
Inventor 韩冬王颖谌颖郭明姝杨彬刘洁刘涛车汝才汤文澜张怡毕鹏波褚楠董筠
Owner BEIJING INST OF CONTROL ENG
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