Development of a Coarse Lunar Soil Model Using Discrete Element Method

Jeong, Hyun-Jae; Lim, Jae Hyuk; Kim, Jin-Won

doi:10.5139/jksas.2019.47.1.26

Cited by 2 publications

(1 citation statement)

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“…The primary struts have shock absorbers made of aluminum (Al) honeycombs (HCs) and were modeled with truss elements (T3D2 element) that can realize elastoplastic behavior. The others were simplified as dummy mass elements in terms of mass and mass moment of inertia [24][25][26], which are efficient for landing dynamics' simulation. Among Al-HCs, CRIII-5/32-5052-.0007P-2.6 was chosen in Hexcel [27].…”

Section: Touchdown Landing Dynamics' Simulation 21 Finite-element Model Of the Lunar Landermentioning

confidence: 99%

Prediction and Validation of Landing Stability of a Lunar Lander by a Classification Map Based on Touchdown Landing Dynamics’ Simulation Considering Soft Ground

et al. 2021

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In this paper, a method for predicting the landing stability of a lunar lander by a classification map of the landing stability is proposed, considering the soft soil characteristics and the slope angle of the lunar surface. First, the landing stability condition in terms of the safe (=stable), sliding (=unstable), and tip-over (=statically unstable) possibilities was checked by dropping a lunar lander onto flat lunar surfaces through finite-element (FE) simulation according to the slope angle, friction coefficient, and soft/rigid ground, while the vertical touchdown velocity was maintained at 3 m/s. All of the simulation results were classified by a classification map with the aid of logistic regression, a machine-learning classification algorithm. Finally, the landing stability status was efficiently predicted by Monte Carlo (MC) simulation by just referring to the classification map for 10,000 input datasets, consisting of the friction coefficient, slope angles, and rigid/soft ground. To demonstrate the performance, two virtual lunar surfaces were employed based on a 3D terrain map of the LRO mission. Then, the landing stability was validated through landing simulation of an FE model of a lunar lander requiring high computation cost. The prediction results showed excellent agreement with those of landing simulations with a negligible computational cost of around a few seconds.

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Section: Touchdown Landing Dynamics' Simulation 21 Finite-element Model Of the Lunar Landermentioning

confidence: 99%