제어로봇시스템학회:학술대회논문집
- 1989.10a
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- Pages.59-64
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- 1989
Launch trajectory analysis of a scientific satellite M-3H-3 including guidance and control system
유도제어시스템을 포함한 과학위성 M-3H-3의 궤도해석
Abstract
In this paper, the launch trajectory of the Japan scientific satellite M-3H-3 from launch to orbit injection is investigated. For the terminal conditions at a guidance target point, a guidance and control system is used. An open-loop and a closed-loop guidance schemes are used simultaneously. For the closed-loop guidance scheme, the velocity polynomial algorithm represented by the velocity difference between the target point and present velocity is used. A PD control system is used for activating gimbal type engines. The simulation result shows that all the terminal position and velocity conditions are satisfied and the trajectory for the M-3H-3 scientific satellite is reasonable.
Keywords