Near-earth satellite redundant flywheel angular momentum autonomous management method

A near-Earth satellite, autonomous management technology, applied in the field of angular momentum management of satellite flywheel systems, can solve the problems of multiple redundant information, large amount of calculation, etc., achieve simple calculation process, less matrix redundant information, and avoid zero-crossing of flywheel rotation speed. or saturated effect

Active Publication Date: 2017-10-10
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

The domestic patent "A Method for Autonomous Management of Angular Momentum of Redundant Flywheel Sets" provides a zero-motion-based angular momentum management method for geosynchronous orbit satellites, but

Method used

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  • Near-earth satellite redundant flywheel angular momentum autonomous management method
  • Near-earth satellite redundant flywheel angular momentum autonomous management method
  • Near-earth satellite redundant flywheel angular momentum autonomous management method

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Embodiment Construction

[0046] The present invention will be further elaborated below by describing a preferred specific embodiment in detail in conjunction with the accompanying drawings.

[0047] In this embodiment, all capitalized vectors in bold are the angular momentum or torque formed by the flywheels, and lowercase bolded vectors are vectors composed of the angular momentum or output / driving torque of each flywheel in the flywheel set.

[0048] Such as figure 1 As shown, the present invention proposes a method for autonomous management of angular momentum of redundant flywheels of near-Earth satellites, which comprises the following steps:

[0049] S1. Divide the given angular momentum increment ΔH of the flywheel group into the angular momentum increment Δh of each flywheel output attitude control moment in the flywheel group T and the angular momentum increment Δh of zero motion z Two parts, Δh T Obtained by the traditional pseudo-inverse method;

[0050] S2. This step is to obtain the cen...

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Abstract

The invention discloses a near-earth satellite redundant flywheel angular momentum autonomous management method, including the steps of S1. dividing given angular momentum increments of a flywheel group into an angular momentum increment of attitude control output by each flywheel in the flywheel group and an angular momentum increment of zero motion; S2. obtaining the central angular momentum of the flywheels; S3. converting a problem of solving flywheel group zero movement into a constrained quadratic form optimization problem, adopting QR decomposition to convert the constrained quadratic form optimization problem into an unconstrained optimization problem, and obtaining a zero movement angular momentum increment of each flywheel, so that the angular momentum of each flywheel approaches the central angular momentum; and S4. according to a relation between flywheel group null space after part of flywheels fail and flywheel group null space when no flywheel fails, completing angular momentum reconstruction of the flywheel group. The advantages of the method are that while the flywheel group generates given moment of force, the rotating speed of each flywheel can approach preset desired rotating speed, thereby preventing frequent zero passage or saturation of the rotating speed of flywheels and realizing on-line reconstruction of a whole system when part of the flywheels fail.

Description

technical field [0001] The invention relates to the technical field of angular momentum management of a satellite flywheel system, in particular to a method for autonomously managing the angular momentum of a near-earth satellite redundant flywheel. Background technique [0002] For the three-axis attitude stabilization satellites of modern long-life satellites, in order to improve the reliability of the system, more than three redundant flywheels are usually installed as the actuators of the attitude control system. If the satellite operates in low-Earth orbit, the angular momentum accumulated by the space disturbance torque on the flywheel system can be unloaded through a magnetic torque device, etc., but it cannot prevent the flywheel speed from being too low or zero-crossing phenomenon, and at the same time, it can only be passively avoided. Saturation occurs. Since the motor works at low speed for a long time and frequently crosses zero, it will have a very adverse eff...

Claims

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Application Information

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IPC IPC(8): G05B13/02
Inventor 刘刚尹海宁叶立军袁彦红孙锦花冉玉萍李芳华徐樱李圣文
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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