By Topic

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

Sign In

Cookies must be enabled to login.After enabling cookies , please use refresh or reload or ctrl+f5 on the browser for the login options.

Formats Non-Member Member
$31 $13
Learn how you can qualify for the best price for this item!
Become an IEEE Member or Subscribe to
IEEE Xplore for exclusive pricing!
close button

puzzle piece

IEEE membership options for an individual and IEEE Xplore subscriptions for an organization offer the most affordable access to essential journal articles, conference papers, standards, eBooks, and eLearning courses.

Learn more about:

IEEE membership

IEEE Xplore subscriptions

5 Author(s)
Xu Lei ; Key Lab. of Fundamental Sci. for Nat. Defense-Adv. Design Technol. of Flight Vehicle, Nanjing Univ. of Aeronaut. & Astronaut., Nanjing, China ; Nie Hong ; Wan Junlin ; Lin Qing
more authors

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.

Published in:

Computer Science and Automation Engineering (CSAE), 2011 IEEE International Conference on  (Volume:1 )

Date of Conference:

10-12 June 2011