Airbag Landing Impact Test/Analysis for the Crew Exploration Vehicle

Lee, Timothy J.; McKinney, J.B.; Farkas, Michael A.

doi:10.2514/6.2008-1745

Cited by 2 publications

References 1 publication

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Airbag Landing Impact Performance Optimization for the Orion Crew Module

Lee

McKinney

Corliss

2008

Earth &Amp;amp; Space 2008

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This report will discuss the use of advanced simulation techniques to optimize the performance of the proposed Orion Crew Module airbag landing system design. The Boeing Company and the National Aeronautic and Space Administration's Langley Research Center collaborated in the analysis of the proposed airbag landing system for the next generation space shuttle replacement, the Orion spacecraft. Using LS-DYNA to simulate the Crew Module landing impacts, two main objectives were established and achieved: the investigation of potential methods of optimizing the airbag performance in order to reduce rebound on the anti-bottoming bags, lower overall landing loads, and increase overall Crew Module stability; and the determination of the Crew Module stability and load boundaries using the optimized airbag design, based on the potential Crew Module landing pitch angles and ground slopes in both the center of gravity forward and aft configurations. This paper describes the optimization and stability and load boundary studies and presents a summary of the results obtained and key lessons learned from this analysis.

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Airbag Landing Impact Performance Optimization for the Orion Crew Module

Lee

McKinney

Corliss

2008

Earth &Amp;amp; Space 2008

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Strength Testing of Fabric Composite Material and Impact Simulation for Airbag Landing System

Wei

Tan

Song

et al. 2015

AMR

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The “Orion crew exploration vehicle” of NASA takes airbag as one way of landing system, which can reduce the landing weight, maintain the reposefully landing of the vehicle, protect the detector during recycling. In this paper, taking into account the material quality and the change during soft-landing of the airbag, the tensile mechanical properties tests of plain weave composite material airbag have been conducted at different temperature and different silicone coating thickness. Based on the material parameters of the test, the finite element model has been created to obtain the inner pressure and the overload curve of the airbag which has a certain angle with the ground. The result shows that the airbag made of fabric composite material can realize the landing and recycling of the vehicle.

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Airbag Landing Impact Test/Analysis for the Crew Exploration Vehicle

Cited by 2 publications

References 1 publication

Airbag Landing Impact Performance Optimization for the Orion Crew Module

Airbag Landing Impact Performance Optimization for the Orion Crew Module

Strength Testing of Fabric Composite Material and Impact Simulation for Airbag Landing System

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