Current Compensation Control Method for Satellite Non-contact Maglev Mechanism
A technology of current compensation and control method, which is applied in attitude control, motor vehicles, space navigation equipment, etc., can solve the problem that the load accuracy and stability are difficult to greatly improve the non-contact maglev mechanism of satellites, and achieve ultra-precise and ultra-stable working conditions , Solving technical bottlenecks and reducing bandwidth requirements
Active Publication Date: 2020-07-14
SHANGHAI SATELLITE ENG INST
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Problems solved by technology
[0004] In view of the defects in the prior art, the purpose of the present invention is to provide a current compensation control method for satellite non-contact maglev mechanism that can effectively solve the problem that the load pointing accuracy and stability are difficult to be greatly improved
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[0015] 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 changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.
[0016] The current compensation control method of the satellite non-contact maglev mechanism of the present invention, the specific implementation steps are as follows:
[0017] The space between the permanent magnets of the non-contact maglev mechanism is subdivided to select sampling points, and the spatial coordinates of the sampling points are defined. 100 sampling points are selected as the best, which are defined as Oxyz, where x, y, and z are positive integers respectively, and the coordinates of...
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The invention provides a satellite non-contact magnetic levitation mechanism current compensation control method, including the following steps: 1. space between permanent magnets of a non-contact magnetic levitation mechanism is subdivided to select sampling points, and space coordinate definition is performed on the sampling points; 2. magnetic field intensities at the sampling points are measured and recorded; 3. magnetic field intensity information of each sampling point is processed, thereby obtaining compensation coefficients of currents of different coordinate point positions; 4. when output force control is performed, the position of a coil central pint is measured in real time; and 5. when output force control is performed, the current output quantity is compensated according to the position of the coil central point and compensation coefficient. Compared with the prior art, the satellite non-contact magnetic levitation mechanism current compensation control method provided by the invention has the following innovative design: ultrahigh precision with satellite attitude pointing accuracy of better than 5*10<4> degrees and attitude stability of better than 5*10<6> deg / s is realized, the ''double-ultrahigh'' technical bottleneck is completely eliminated, and complete measurability and controllability of load attitude are realized.
Description
technical field [0001] The invention relates to an aerospace vehicle structure, in particular to a current compensation control method for a satellite non-contact maglev mechanism. Background technique [0002] The coupling torque of flexible accessories such as large-scale solar panels of traditional satellites to the satellite body is an important factor affecting the accuracy and stability of satellite load attitude pointing, while the low-frequency micro-vibrations induced by moving parts such as flywheels, gyroscopes, and drive mechanisms on satellites , is another factor that reduces the attitude pointing accuracy and stability. In the future, high-performance spacecraft will have higher and higher requirements for satellite attitude pointing accuracy and attitude stability. The interference and flutter problems caused by large flexible structures and vibrations of moving parts have become the main factors restricting the accuracy of satellite attitude control. [000...
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IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 朱敏赵洪波廖鹤赵艳彬张祎朱莎莎刘亦男张高雄
Owner SHANGHAI SATELLITE ENG INST