Attitude-orbit integrated thrust distribution method for satellite

A thrust distribution and satellite technology, which is applied in the field of satellite control, can solve problems such as thruster layout optimization, influence on thruster control accuracy, and large thrust distribution error, so as to save fuel, reduce thrust distribution error, and improve control accuracy.

Inactive Publication Date: 2015-09-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

These modified pseudo-inverse methods have improved the limited problems of the traditional pseudo-inverse method, but none of the existing distribution methods have optimized the layout of the thruster and various characteristic indicators, resulting in a large error in thrust distribution. Affect the control accuracy of the thruster

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  • Attitude-orbit integrated thrust distribution method for satellite
  • Attitude-orbit integrated thrust distribution method for satellite
  • Attitude-orbit integrated thrust distribution method for satellite

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Embodiment Construction

[0035] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0036] In the selection process of the thruster, the least thrust and the least control error caused by the thrust configuration should generally be considered. In order to reflect the proportional coefficient between the control error influenced by the relative geometric relationship of the thruster and the expected control quantity, the fuel consumption factor CDOP is defined as follows:

[0037] CDOP=tr[DD T ]

[0038] The smaller the fuel consumption factor CDOP, the smaller the control error caused by the thrust configuration. When the thruster layout is constant, as the number of engines participating in the allocation increases, the configuration fuel consumption factor CDOP also increases correspondingly, and the allocation error increases. Therefore, from the perspective of reducing the allocation error, the number of engines participating in the ...

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Abstract

The invention discloses an attitude-orbit integrated thrust distribution method for a satellite, and belongs to the technical field of satellite control. After the installation layout of a thruster is determined, a mathematical model of thrust distribution is built, and the initial solution of thrust distribution, namely the initial thrust distribution scheme, is obtained based on the conventional pseudo-inverse method; then, grouping is performed based on the initial solution, and the thrust distribution scheme based on a chain type distribution revised pseudo-inverse method is obtained; and finally, a thrust distribution optimization index is designed, overall algorithm optimization is realized with the combination of various indexes of the thruster, and thrust distribution is optimized. According to the method, the integrated control task of the satellite can be effectively accomplished within the load range configured by the thruster, fuels are effectively saved, the thrust distribution error brought by thrust configuration is reduced, and the control precision of the thrust is improved.

Description

technical field [0001] The invention relates to a method for distributing thrust of a satellite, in particular to a method for distributing thrust of a satellite with integrated attitude and orbit, and belongs to the technical field of satellite control. Background technique [0002] Attitude-orbit integrated control is a control technology that simultaneously considers the orbit and attitude maneuver tasks of the satellite during the satellite’s in-orbit operation, and realizes the simultaneous control of orbit and attitude by sharing a set of actuator configurations. The implementation of integrated control of attitude and orbit can maximize the use of the maneuverability of the actuator, save some hardware resources, improve the functional density of the system, and at the same time improve the efficiency of fuel utilization, so as to save fuel and prolong the service life of satellites in orbit . [0003] Thruster is a commonly used satellite actuator, when the force it...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04G05D1/08G05D1/10
Inventor 华冰邵珠君关欣康国华吴云华
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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