Title :
Analysis of landing impact performance for lunar lander based on flexible body
Author :
Xu Lei ; Nie Hong ; Wan Junlin ; Lin Qing ; Chen Jinbao
Author_Institution :
Key Lab. of Fundamental Sci. for Nat. Defense-Adv. Design Technol. of Flight Vehicle, Nanjing Univ. of Aeronaut. & Astronaut., Nanjing, China
Abstract :
It is necessary to investigate the lunar lander soft-landing by considering the flexible body and legs because the impact of deformation is significant. There is a new method for research on landing impact performance in this paper. Firstly a dynamical model of 1/4 lunar lander with four suspension legs is build and simplified. After getting oscillation equation of the model, founds two simulation models respectively by multi-rigid-body dynamics method and nonlinear finite element method. The simulation of soft-landing selects MSC.ADMAS and MSC.DYTRAN. Main analysis objects are buffer distance of primary strut in lunar lander and vertical acceleration of box´s centroid, then contrasts two simulation results based on the objects. Research results show that the influence of flexible body reduces the maximum of primary strut´s buffer distance, but amplifies the vertical acceleration of centroid with periodic oscillation.
Keywords :
aerospace components; aerospace engineering; deformation; finite element analysis; impact (mechanical); space vehicles; vehicle dynamics; deformation impact; flexible body; flexible legs; landing impact performance; lunar lander; multirigid-body dynamics method; nonlinear finite element method; oscillation equation; Aerodynamics; Analytical models; Equations; Leg; Mathematical model; Moon; Vehicle dynamics; buffer; flexible body; lunar lander; nonlinear analysis; soft landing;
Conference_Titel :
Computer Science and Automation Engineering (CSAE), 2011 IEEE International Conference on
Conference_Location :
Shanghai
Print_ISBN :
978-1-4244-8727-1
DOI :
10.1109/CSAE.2011.5953160
