International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Optimal Perilune Altitude of Lunar Landing Trajectory

  • Cho, Dong-Hyun (Satellite Technology Research Center, KAIST) ;
  • Jeong, Bo-Young (Division of Aerospace Engineering, School of Mechanical, Aerospace and Systems Engineering, KAIST) ;
  • Lee, Dong-Hun (Division of Aerospace Engineering, School of Mechanical, Aerospace and Systems Engineering, KAIST) ;
  • Bang, Hyo-Choong (Division of Aerospace Engineering, School of Mechanical, Aerospace and Systems Engineering, KAIST)
  • Published : 2009.05.30
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Abstract

In general, the lunar landing stage can be divided into two distinct phases: de-orbit and descent, and the descent phase usually comprises two sub-phases: braking and approach. And many optimization problems of minimal energy are usually focused on descent phases. In these approaches, the energy of de-orbit burning is not considered. Therefore, a possible low perilune altitude can be chosen to save fuel for the descent phase. Perilune altitude is typically specified between 10 and 15km because of the mountainous lunar terrain and possible guidance errors. However, it requires more de-orbit burning energy for the lower perilune altitude. Therefore, in this paper, the perilune altitude of the intermediate orbit is also considered with optimal thrust programming for minimal energy. Furthermore, the perilune altitude and optimal thrust programming can be expressed by a function of the radius of a parking orbit by using continuation method and co-state estimator.

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References

  1. Bennett, F. V., 1972, “Mission planning for Lunar module descent and ascent”, NASA Technical Note, Houston
  2. Ramanan, R. V. and Lal, M., 2005, “Analysis of optimal strategies for soft landing on the Moon from lunar parking orbits”, Journal of Earth Systems Science, Vol. 114, No. 6, pp. 807-813 https://doi.org/10.1007/BF02715967
  3. Shan, Y and Duan, G., 2007, “Study on the Optimal Fuel Consumption of the Singularity Condition for Lunar Soft Landing”, Proc. of the 2007 IEEE International Conference on Robotics and Biomimetics, pp. 2254-2258.
  4. Hwakins, A.M., 2005, "Constrained Trajectory Optimization of a Soft Lunar Landing from a Parking Orbit”, the degree of Master of Science in Aeronautics and Astronautics, Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics
  5. Liu, X., Duan, G., 2006, “Nonlinear Optimal Control for the Soft Landing of Lunar Lander”, Systems and Control in Aerospace and Astronautics, pp. 1381-1387. https://doi.org/10.1109/ISSCAA.2006.1627542
  6. Liu, X., Duan, G., and Teo, K., 2008, "Brief paper: Optimal soft landing control for moon lander”, Automatica, Vol.4, pp. 1097-1103. https://doi.org/10.1016/j.automatica.2007.08.021
  7. McInnes, C.R., 1995, "Path Shaping Guidance for Terminal Lunar Descent”, Acta Astronautica, Vol. 36, No. 7, pp. 367-377. https://doi.org/10.1016/0094-5765(95)00119-0
  8. Lee, Donghun and Bang, Hyochoong, 2008, “Optimal Earth Escape Trajectory Using Continuation method and costate estimator”, 18th AAS/AISS Space Flight Mechanics Meeting
  9. Hull, D. G., 2003, Optimal Control Theory for Applications, Springer, New York, pp. 258-274.

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