Title: Fast accurate error modeling and optimizing method for inertial stellar compass
Application Number: 200610165504 Application Date: 2006.12.21
Publication Number: 1975330 Publication Date: 2007.06.06
Approval Pub. Date: Granted Pub. Date:
International Classifi-cation: G01C17/00;G01C17/34;G01C17/38;G01C21/00;G01C21/16
Applicant(s) Name: Beijing Aerospace Univ. Address:
Inventor(s) Name: Fang Jiancheng;Quan Wei;Xu Fan;Wang Ke;Zhong Huimi
Attorney & Agent: guanling lixin hua
Abstract:
    This invention disclosed an error modeling and optimizing method for inertia star box and needle. It could integrate the four main error sources including the optical system, the sensitive parts, MEMS inertia parts and the processing system. So the error modeling and optimazing was very rapid. It works like this: analyze the characters of the error sources and obtain a brief model; input the brief model as GP arithmetic and calculate an error model as a whole with optimal adaptability; optimize the whole error model by improved GA. The modeling efficiency and precision was improved by this invention. It can be applied to combined navigation system and assembled settings.
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