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Title:
ピラミッド型軌道離脱セイルの形状構築及び姿勢制御方法
Document Type and Number:
Japanese Patent JP7420412
Kind Code:
B2
Abstract:
Provided is a configuration construction and attitude control method for a pyramid deorbit sail. By taking into consideration environmental perturbation like atmospheric resistance perturbation and non-spherical earth perturbation, a dynamics model featuring three-dimensional orbit-and-attitude coupling based on position vectors and quaternion descriptions, the deorbit sail is taken as a rigid body, a spacecraft body is taken as a mass point, airflow obstruction is considered in the windward area, thereby improving the precision of the dynamics model; based on this model, the law of influence of the configuration parameters in the deorbit sail, such as a cone angle and a strut length, on the attitude stability and deorbiting efficiency of the spacecraft in different cases is analyzed, the configuration parameters of the pyramid deorbit sail system are analyzed and optimized according to the derived law, so as to obtain a pyramid deorbit sail achieving high attitude stability and high deorbiting efficiency.

Inventors:
Zhang Jingrui
Zhang Rakunan
Yang Ke-ying
Lin Cheng Lee
Application Number:
JP2022159266A
Publication Date:
January 23, 2024
Filing Date:
October 03, 2022
Export Citation:
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Assignee:
Beijing Institute of Technology
International Classes:
B64G1/24; B64G1/22; B64G1/28; B64G1/40
Domestic Patent References:
JP2018504326A
JP2007157106A
JP58112899A
Foreign References:
CN111470071A
US20200130872
Other References:
Thomas Sinn,RESULTS OF THE DEPLOYABLE MEMBRANE & ADEO PASSIVE DE-ORBIT SUBSYSTEM ACTIVITIES LEADING TO A DRAGSAIL DEMONSTRATOR,7th European Conference of Space Debris
Lars Ttiedemann,ADEO - Architectural Design and Testing of De-orbiting Subsystem,CleanSat Workshop 17-18 .03.2015
Attorney, Agent or Firm:
Riki Yoshimoto



 
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