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Orbit control method by utilizing interference accumulation angular momentum self balance

A technology of orbit control and angular momentum, applied in three-dimensional position/channel control and other directions, can solve the problem that the interference torque cannot be eliminated in time, and achieve the effect of adjusting the semi-major axis of the large orbit

Active Publication Date: 2013-05-01
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0006] Aiming at the problem that the z-axis (or x-axis) attitude disturbance moment generated during the orbit semi-major axis adjustment process of the ground-oriented satellite cannot be eliminated in time, the momentum wheel is used as the disturbance angular momentum storage mechanism, and by reasonably selecting the orbit control position, The interference angular momentum stored by the momentum wheel is eliminated by the orbit control interference torque in the next orbit control, so as to realize the self-balancing of the z-axis (or x-axis) interference angular momentum, and the z-axis (or x-axis) attitude is not required to achieve the orbit control process. The purpose of controlling the engine work

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  • Orbit control method by utilizing interference accumulation angular momentum self balance
  • Orbit control method by utilizing interference accumulation angular momentum self balance
  • Orbit control method by utilizing interference accumulation angular momentum self balance

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Embodiment Construction

[0021] The present invention will be further introduced below in conjunction with the accompanying drawings.

[0022] For a ground-oriented satellite that uses an orbital thruster for orbit control, assuming that the orbital thruster works continuously on a circle of orbit, the accumulated disturbance moment will be generated, as figure 2 As shown, the coordinate system O-XYZ in the figure is an inertial coordinate system established with XOZ as the orbital plane, the origin O is the center of the earth, the Y-axis is perpendicular to the orbital plane and points to the normal direction of the orbital surface, and the Z-axis points from the center of the earth to the initial Time satellite center, X axis is orthogonal to Y, Z. coordinate system o b -XbYbZb is the satellite body coordinate system, the origin o b is the center of mass of the satellite, Xb points to the forward direction of the satellite, Zb points to the center of the earth, and Yb is orthogonal to Xb and Zb....

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Abstract

The invention discloses an orbit control method by utilizing the interference accumulation angular momentum self balance. The method comprises the following steps that the starting offset angular momentum is built at the starting moment of the satellite orbit control; the orbit control time Tp of the satellite by utilizing an orbit control thruster in each orbit control process is determined; and in one orbit period of the satellite, M orbit control points are uniformly selected for carrying out orbit control. After the orbit control method is adopted, the goal that the interference accumulation angular momentum generated by utilizing the orbit control thruster in the orbit semi-major axis regulating process is used for controlling the satellite orbit is realized.

Description

technical field [0001] The invention relates to the technical field of satellite orbit control, and relates to an orbit control method utilizing disturbance to accumulate angular momentum self-balancing. Background technique [0002] Due to the need for the normal work of the payload, the Haiyang-2 satellite must raise its orbit by 55km to the target orbit. Generally, due to the large disturbance moment during satellite orbit control, jet control is used to maintain the attitude during the orbit control process. However, the Haiyang-2 satellite-Z-axis attitude control engine is not available, and the attitude control of the star during orbit control can only be performed through the momentum wheel. At the same time, due to the impact of the engine plume on the Haiyang-2 satellite, the operation of the orbital control engine produces a large interference moment on the Z-axis direction of the satellite. [0003] In the past, the orbit control of satellites was mostly based o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10
Inventor 王淑一雷拥军王新民宗红袁军张笃周周剑敏赵性颂
Owner BEIJING INST OF CONTROL ENG
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