The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
Oct. 15, 2019
Filed:
Feb. 17, 2017
China Three Gorges University, Yichang, Hubei Provience, CN;
Liqing Pan, Yichang, CN;
Xianwei Yang, Yichang, CN;
Zhihui Luo, Yichang, CN;
Hua Zhao, Yichang, CN;
Mingxue Shao, Yichang, CN;
Qiongying Ren, Yichang, CN;
Chao Tan, Yichang, CN;
Min Liu, Yichang, CN;
Chao Wang, Yichang, CN;
Chao Zhang, Yichang, CN;
Sheng Zheng, Yichang, CN;
Hongguang Piao, Yichang, CN;
Guangduo Lu, Yichang, CN;
Yunli Xu, Yichang, CN;
Xiufeng Huang, Yichang, CN;
CHINA THREE GORGES UNIVERSITY, Yichang, Hubei Province, CN;
Abstract
A high-precision magnetic suspension accelerometer for measuring the linear acceleration of a spacecraft is provided, comprising a magnetically shielded vacuum chamber system, a magnetic displacement sensing system, a magnetic suspension control system and a small magnetic proof mass. A optical coherence displacement detection technique is utilized for precisely measuring the position and the posture of the small magnetic proof mass in real time, and a magnetic suspension control technique is utilized for precisely controlling the position and the posture of the small magnetic proof mass to be brought back to the origin, so as to keep the small magnetic proof mass in the center of the systemic inner chamber. When the spacecraft is subject to a non-conservative force, the magnitude and direction of the acceleration can be precisely measured via the measurement of currents in the position control coils due to the acceleration of the spacecraft proportional to the currents of the position control coils. The accelerometer of the invention can avoid the technical bottleneck of high-precision machining, is easy to be produced and can achieve more high-precision measurement of the acceleration vector.