Momentum wheel layout configuration method for spacecraft with large inertia product

A layout configuration and spacecraft technology, applied in the direction of attitude control, etc., can solve the problems affecting the control of high precision and high stability of spacecraft, the difficulty of control system design, etc.

Active Publication Date: 2015-08-19
SHANGHAI XINYUE METER FACTORY
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  • Abstract
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  • Claims
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Problems solved by technology

The coupling problem brings difficulty and complexity to the design of the control s

Method used

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  • Momentum wheel layout configuration method for spacecraft with large inertia product
  • Momentum wheel layout configuration method for spacecraft with large inertia product
  • Momentum wheel layout configuration method for spacecraft with large inertia product

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Embodiment Construction

[0052] The present invention will be further elaborated below by describing a preferred specific embodiment in detail in conjunction with the accompanying drawings.

[0053] Such as figure 1 As shown, a momentum wheel layout configuration method for a spacecraft with a large inertia product, the momentum wheel layout configuration method includes the following steps:

[0054] S1, spectral decomposition of the inertia matrix of a spacecraft with a large inertia product. The step S1 includes:

[0055] The spectral decomposition of the inertia matrix A of a spacecraft with a large inertia product is performed to obtain:

[0056] P -1 AP = Λ formula (1);

[0057] Among them, Λ=diag[λ 1 lambda 2 lambda 3 ] is the feature matrix, λ 1 ,λ 2 ,λ 3 is the eigenvalue of matrix A;

[0058] P is the transformation matrix of the inertia matrix A; P - 1 = ...

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Abstract

The invention discloses a momentum wheel layout configuration method for a spacecraft with a large inertia product. Through spectral decomposition on an inertia matrix with the spacecraft with the large inertia product, a decoupling attitude dynamics model of the spacecraft is established, the installation angle position of a momentum wheel set and arranged on the spacecraft is calculated, and decoupling control of the attitude angle of the spacecraft is finally realized. The method provided by the invention can prevent coupling existing in attitude motion in two or three directions on a body coordinate axis of the spacecraft, caused by the large inertia product, realizes decoupling control of large-inertia-product triaxial stable zero momentum and realizes independent control of each attitude of the spacecraft.

Description

technical field [0001] The invention relates to a spacecraft attitude control technology, in particular to a momentum wheel layout configuration method for a spacecraft with a large inertia product. Background technique [0002] According to the requirements of the space mission or the installation layout of the spacecraft payload, the spacecraft may have a large inertia product in the mass distribution in a certain body coordinate system. The inertia product makes the attitude motions in various directions in the spacecraft body coordinates coupled. When attitude control is performed on a certain attitude direction of the spacecraft involved in the inertia product, it will affect the attitude motion in other directions involved in the inertia product. [0003] The spacecraft will try to optimize the structural layout design to avoid the generation of the inertia product. The inertia product should usually be 1 to 2 orders of magnitude smaller than the spacecraft’s main ine...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 谭天乐张艳召徐亚娟王新萌辛岩朱东方
Owner SHANGHAI XINYUE METER FACTORY
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