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기술보고서

기술보고서 게시판 내용
타이틀	Modeling Attitude Dynamics in Simulink: A Study of the Rotational and Translational Motion of a Spacecraft Given Torques and Impulses Generated by RMS Hand Controllers
저자	Mauldin, Rebecca H.
Keyword	ATTITUDE (INCLINATION); CONTROLLERS;; EQUATIONS OF MOTION;; IMPULSES;; MOMENTS OF INERTIA;; REMOTE MANIPULATOR SYSTEM;; RIGID STRUCTURES;; SPACECRAFT CONTROL;; SPACECRAFT MOTION;; TORQUE;; TRANSLATIONAL MOTION
URL	http://hdl.handle.net/2060/20110007233
보고서번호	M11-0146
발행년도	2010
출처	NTRS (NASA Technical Report Server)
ABSTRACT	In order to study and control the attitude of a spacecraft, it is necessary to understand the natural motion of a body in orbit. Assuming a spacecraft to be a rigid body, dynamics describes the complete motion of the vehicle by the translational and rotational motion of the body. The Simulink Attitude Analysis Model applies the equations of rigid body motion to the study of a spacecraft''s attitude in orbit. Using a TCP/IP connection, Matlab reads the values of the Remote Manipulator System (RMS) hand controllers and passes them to Simulink as specified torque and impulse profiles. Simulink then uses the governing kinematic and dynamic equations of a rigid body in low earth orbit (LE0) to plot the attitude response of a spacecraft for five seconds given known applied torques and impulses, and constant principal moments of inertia.