CEV Airbag Landing System Modeling

Abstract

The dynamic analysis of impact attenuation airbag landing systems is studied. An experimental airbag test program is presented where the objectives were analytical model validation and airbag performance demonstration. Airbag systems are currently under consideration for the impact attenuation of earth landing for the Orion Crew Exploration Vehicle. The purpose of the system is to limit landing loads and provide stability, to protect the crew and to allow vehicle reuse. An important element of the airbag system design process is accurate modeling of the proposed configuration to determine if the resulting performance meets requirements. An explicit dynamic finite element analysis model is presented. Once all the post processing of the experimental data is complete, the time history data from the dynamic analysis models will be compared with this measurement data from the test program. Some preliminary checks have yielded good correlation with the experiment. ILC Dover is in competition for the potential airbag landing system design and fabrication work of the Orion Crew Exploration Vehicle. This ongoing competition prevents the disclosure of the detailed result magnitudes at this time.