Analysis of landing impact performance for lunar lander based on flexible body

Xu, Lei; Nie, Hong; Wan, Junlin; Lin, Qing; Chen, Jinbao

doi:10.1109/csae.2011.5953160

Cited by 7 publications

(2 citation statements)

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“…Several authors tried to study the soft landing problem by means of simulation software, and chose as a case study a four-legged lander. For example, Xu et al in 2011 simulated the soft-landing of a lunar lander first using MSC-ADAMS considering the lunar soil as a rigid body, and then MSC-DYTRAN considering the lunar soil as a flexible body [16]. Wan et al in 2010, chose MSC-DYTRAN to simulate soft-landing of a lunar lander with the finite elements method and a nonlinear transient dynamics approach [17].…”

Section: Introductionmentioning

confidence: 99%

Dynamic Modeling and Simulation of a Robotic Lander Based on Variable Radius Drums

et al. 2020

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Soft-landing on planetary surfaces is the main challenge in most space exploration missions. In this work, the dynamic modeling and simulation of a three-legged robotic lander based on variable radius drums are presented. In particular, the proposed robotic system consists of a non-reversible mechanism that allows a landing object to constant decelerate in the phase of impact with ground. The mechanism is based on variable radius drums, which are used to shape the elastic response of a spring to produce a specific behavior. A dynamic model of the proposed robotic lander is first presented. Then, its behavior is evaluated through numerical multibody simulations. Results show the feasibility of the proposed design and applicability of the mechanism in landing operations.

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Section: Introductionmentioning

confidence: 99%

Dynamic Modeling and Simulation of a Robotic Lander Based on Variable Radius Drums

et al. 2020

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“…In addition, the above research did not consider the influence of landing strut lateral flexibility on the friction force. Xu et al 12 and Dong et al 13 studied lunar lander model with nonlinear finite element method which can predict the friction force between cylinders precisely through the establishment of nonlinear contact model. Although this method can ensure good calculation accuracy, its modeling and calculation process is complex, time-consuming, and inefficient, lacking in adaptability of multiple working conditions analysis.…”

Section: Introductionmentioning

confidence: 99%

Dynamic analysis for vertical soft landing of reusable launch vehicle with landing strut flexibility

Yue

Nie

Zhang

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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Based on oleo-honeycomb dampers, a 6-DOF vertical soft landing dynamic model for reusable launch vehicle considering landing strut flexibility is constructed. In order to better analyze the lateral deflection and friction force of the “cantilever beam” type landing strut, a new model for strut is incorporated. Static analysis is first performed based on the rotation angle compatibility equations to attain the equivalent inertia moment. Then the strut lateral vibration model and friction force model are obtained by simplifying it as viscoelastic beam with a tip mass. After that, the ADAMS models are established to perform the comparison and verification analysis of the 6-DOF dynamic model. The results show that the results of 6-DOF dynamic model can approximately approach to the results of rigid-flex coupling model established in ADAMS. Furthermore, the research of the influence of assembly gap between cylinders and bearings, bearing’s elastic modulus, friction coefficient and initial overlapping length on the vehicle landing performance is carried out. The results show that each parameter has different influence on the landing performance, and a reasonable selection of these parameters accordingly enables a higher landing performance.

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