Title: Micro low power consumption inertial stellar compass for micro nano spacecraft
Application Number: 200610165166 Application Date: 2006.12.14
Publication Number: 1987354 Publication Date: 2007.06.27
Approval Pub. Date: Granted Pub. Date:
International Classifi-cation: G01C17/00;G01C17/34;G01C21/00;G01C21/16
Applicant(s) Name: Beijing Univ. of Aeronautics and Astronautics Address:
Inventor(s) Name: Fang Jiancheng;Quan Wei;Wang Ke;Zu Fan;Yang Sheng;
Attorney & Agent: guanling lixin hua
Abstract:
    The compass includes sensing subsystem, signal acquisition and pretreatment subsystem (SAPS), and synthesis subsystem (SS). Collecting astronomical information and inertia information, the sensing subsystem converts the collected information to electrical signal, and sends the electrical signal to SAPS. SAPS carries out smoothing and preprocessing the astronomical information and inertia information, and sends the obtained information of star point and position of center of mass as well as smoothed gyro information to SS. SS carries out synchronous processing astronomical information and inertia information so as to accomplish star map identification and attitude determination. Further, using inertia, star and compass combined method for determining pose implement determination of system pose. Advantages are: small size, low power consumption, and low cost.
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