제어로봇시스템학회:학술대회논문집
- 2003.10a
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- Pages.531-536
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- 2003
Trajectory and Attitude Control for a Lunar lander Using a Reference Model (2nd Report)
- Abe, Akio (Department of Aerospace Engineering College of Science and Technology, Nihon University) ;
- Uchiyama, Kenji (Department of Aerospace Engineering College of Science and Technology, Nihon University) ;
- Shimada, Yuzo (Department of Aerospace Engineering College of Science and Technology, Nihon University)
- Published : 2003.10.22
Abstract
In this paper, a redesigned guidance and control system for a lunar lander is presented. In past studies, the authors developed a trajectory and attitude control system which achieves the vertical soft landing on the lunar surface. It is confirmed that the system has a good tracking ability to a predefined profile and good robustness against a thruster failure mode where a partial failure of clustered engines was assumed. However, under the previous control laws, the landing point tends to be shifted, in response to the system parameter values, from a target point. Also, an unbalanced moment due to a thruster failure mode was not considered in the simulation. Therefore, in this study, the downrange control is added to the system to enable the vehicle to land at a pre-assigned target point accurately. Furthermore, inhibiting the effect of the unbalanced moment is attempted thorough redesigning the attitude control system. A numerical simulation was performed to confirm the ability of the proposed system with regard to the above problems. Moreover, in the past simulations, a low initial altitude was assumed as an initial condition: in this study, however, the performance of the proposed system is examined over the whole trajectory from an initial altitude of 10 [km] to the lunar surface.
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