International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Landing Stability Simulation of a 1/6 Lunar Module with Aluminum Honeycomb Dampers

  • Pham, Van Lai (Department of Advanced Technology Fusion, Division of Interdisciplinary studies, Konkuk University) ;
  • Zhao, Jun (Department of Advanced Technology Fusion, Division of Interdisciplinary studies, Konkuk University) ;
  • Goo, Nam Seo (Department of Advanced Technology Fusion, Division of Interdisciplinary studies, Konkuk University) ;
  • Lim, Jae Hyuk (Korea Aerospace Research Institute) ;
  • Hwang, Do-Soon (Korea Aerospace Research Institute) ;
  • Park, Jung Sun (Aerospace and Mechanical Engineering, Korea Aerospace University)
  • Received : 2013.11.07
  • Accepted : 2013.12.12
  • Published : 2013.12.30
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Abstract

The Korea Aerospace Research Institute plans to launch a lunar module by 2025, and so is carrying out a preliminary study. Landing stability on the lunar surface is a key design factor of a lunar module. In this paper, a 1/6 scale model of a lunar module is investigated, for its landing stability on non-level surfaces. The lunar module has four tripod legs, with aluminum honeycomb shock absorbers in each leg strut. ADAMS$^{TM}$, the most widely used multi-body dynamics and motion analysis software, is used to simulate the module's lunar landing. Three types of dampers in the struts (rigid, viscous, and aluminum honeycomb dampers), and two types of lunar surfaces (rigid and elastic) are considered. The Sforce function is adopted, to model the aluminum honeycomb dampers. Details on the modeling and analysis of the landing stability of the 1/6 scale lunar module and the simulation results are provided in this paper.

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References

  1. Robert, W. H., and Leonard, H. W., "Dynamic model investigation of touchdown stability of lunar landing vehicles", NASA Technical Note D-4215, 1967.
  2. Sun, Y., Hu, Y., Liu, R. Q., and Den, Z. Q., "Touchdown dynamic modeling and simulation of lunar Lander", Systems and Control in Aeronautics and Astronautics (ISSCAA), 2010 3rd International Symposium on, 2010, pp.1320-1324.
  3. Jiang,W., Huang,W., and Shen, Z.,"Application of ADAMS user-written subroutine to simulation of softlanding dynamics", Spacecraft Recovery & Remote Sensing 04, 2009, pp. 328-333.
  4. Lunar and Planetary Institute, Lunar Mission Summaries. Lunar Science and Exploration. URL : http://www.lpi.usra.edu/lunar/missions/.
  5. ESA-NEXT Team, Next Lunar Lander with in-situ science and mobility: Lunar Environment Specification, European Space Agency, 2008.
  6. William, F. R., "Apollo Experience Report-Lunar Module Landing Gear Subsystem", NASA Technical Note D-6850, 1972.
  7. Johnson, K. L., Contact Mechanics, The Press Syndicate of The University of Cambridge, Cambridge, United Kingdom, 1987.
  8. Jiang, T., Hirotsugu , O., and Masahiko, H., "Dynamic-Contact Stiffness at the Interface Between a Vibrating Rigid Sphere and a Semi-Infinite Viscoelastic Solid", IEEE Transactions on Ultrasonics, Ferroelectrics, and Frequency Control, Vol. 51, No. 14, 2004, pp. 1557-1563. https://doi.org/10.1109/TUFFC.2004.1367497

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  2. Optimization and Performance Analysis of Oleo-Honeycomb Damper Used in Vertical Landing Reusable Launch Vehicle vol.31, pp.2, 2018, https://doi.org/10.1061/(ASCE)AS.1943-5525.0000825