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Method for estimating angular velocity of spacecraft based on rolling time domain estimation

A rolling time-domain estimation and spacecraft technology, applied in attitude control and other directions, can solve problems such as unsuitable spacecraft

Active Publication Date: 2019-02-15
BEIHANG UNIV
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Problems solved by technology

The system models used in the above patents are not spacecraft models, so the above methods are not applicable to spacecraft

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  • Method for estimating angular velocity of spacecraft based on rolling time domain estimation
  • Method for estimating angular velocity of spacecraft based on rolling time domain estimation
  • Method for estimating angular velocity of spacecraft based on rolling time domain estimation

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Embodiment Construction

[0123] like figure 1 As shown, the spacecraft angular velocity estimation method of the present invention is a rolling time-domain estimation method that considers the spacecraft angular velocity physical constraints and control torque constraints. At each sampling moment, the optimal angular velocity estimate obtained by this estimation method can be fed back to the controller, and the controller uses the optimal estimated value to generate control torque to act on the spacecraft disturbed by the external torque to complete attitude stabilization or attitude maneuvering ; Redundant fiber optic gyroscopes are combined with sensitive spacecraft angular velocity, and the four-way 12-dimensional measurement signals with measurement noise are weighted based on new weighted data fusion processing based on fault failure factor distribution, and then input to the rolling time domain together with the control torque signal The estimator completes the real-time, reliable, accurate and ...

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Abstract

The invention relates to a method for estimating an angular velocity of a spacecraft based on rolling time domain estimation. The method comprises the following steps: constructing a state equation and an observation equation of the angular velocity of the spacecraft based on a spacecraft dynamics model; carrying out simplified processing on four-way twelve-dimensional angular velocity measurementinformation of a redundant optical fiber gyroscope combination to obtain a triaxle angular velocity measurement data of the spacecraft; and based on the constructed state equation and the observationequation, and the obtained spacecraft triaxle angular velocity measurement data, and meanwhile considering an angular velocity constraint and a control moment constraint of the spacecraft, performingonline estimation by utilizing a rolling time domain estimation strategy and a multi-target method to obtain an estimated value of the optimal angular velocity of the spacecraft at the current moment. The method has the advantages of high calculation efficiency, high reliability, good running effect, high precision, and the like, fully considers physical constraints and control moment constraintsof the spacecraft, is an effective optimal online state estimation method, and is suitable for constrained spacecraft angular velocity estimation problems.

Description

technical field [0001] The invention relates to an estimation method of spacecraft angular velocity based on rolling time domain estimation, which is mainly applied to the problem of online estimation of spacecraft angular velocity considering angular velocity constraints and control moment constraints, and belongs to the field of spacecraft attitude determination. Background technique [0002] The development of aerospace technology is based on the control and navigation technology of spacecraft. How to improve the control and navigation accuracy of spacecraft on the basis of existing system hardware equipment is of great significance. In recent years, as spacecraft missions have become more diverse and complex, for spacecraft performing missions in orbit, the accuracy of spacecraft attitude parameters determination determines the accuracy of attitude control, which in turn affects the entire flight. The function realization of the task. [0003] The emergence of new and c...

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Application Information

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IPC IPC(8): G05D1/08
Inventor 胡庆雷张鑫鑫董宏洋郭雷
Owner BEIHANG UNIV
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