Identifying method for modal parameter of flexible satellite capable of restraining gyro noise influence

A modal parameter and flexible satellite technology, which is applied in the field of flexible satellite modal parameter identification, can solve problems such as increasing the complexity of the structure, and achieve the effects of facilitating engineering realization, reducing cost and design difficulty, and improving identification accuracy

Active Publication Date: 2015-12-16
SHANGHAI XINYUE METER FACTORY
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Problems solved by technology

However, the measurement elements required by these methods undoubtedly increase the complexity of the structure. Therefore, it is necessary to co

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  • Identifying method for modal parameter of flexible satellite capable of restraining gyro noise influence
  • Identifying method for modal parameter of flexible satellite capable of restraining gyro noise influence
  • Identifying method for modal parameter of flexible satellite capable of restraining gyro noise influence

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Embodiment Construction

[0018] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0019] Such as figure 1 As shown in the on-board mode conversion diagram of the present invention, when the satellite is separated from the rocket, it first enters into the initial deflection control mode, and damps the angular velocity of the satellite body, so that the angular momentum of the satellite body (including all rotating parts) can be captured. The need before the earth control; then use the infrared horizon and gyroscope as the measuring element to control the jet control of the groun...

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Abstract

The invention provides an identifying method for a modal parameter of a flexible satellite capable of restraining gyro noise influence. The method comprises the following steps: utilizing measuring data of a satellite body angular velocity while the satellite flies in an orbit to identify a modal frequency and a modal damping ratio parameter of the whole satellite; approximately regarding the measuring noise of the gyro in a short-term period as two parts, namely, constant drifting and random drifting; and performing differential treatment on the gyro data and utilizing the property of Gaussian noise three-order accumulated quantity constantly being zero to restrain the influences of the two parts of noises on an identifying result. Compared with the prior art, the identifying method for the modal parameter of the flexible satellite capable of restraining gyro noise influence can utilize the measuring data of the gyro on the satellite to perform modal parameter identification and restrain the measuring noise, so that the identification precision of the algorithm is increased.

Description

technical field [0001] The invention relates to a flexible satellite modal parameter identification technology. According to the change of the angular velocity of the star during the operation of the satellite, the whole satellite modal frequency and modal damping ratio are used to suppress the two errors of the constant value drift and the Gaussian noise generated by the gyro measurement. identification method. Background technique [0002] During the control process of satellites with flexible structures such as large antennas and sailboards, in order to avoid the vibration of accessories and achieve high-precision and high-stability control of satellite attitude, it is necessary to improve the accuracy of the control model, and ground modeling is no longer enough To meet the requirements of control accuracy, it is necessary to use the satellite in-orbit operation data to identify the on-orbit state parameters. [0003] At present, there is no domestic case of using satel...

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 刘川
Owner SHANGHAI XINYUE METER FACTORY
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