Preliminary design of a meteoroid/orbital debris shield system for a Mars mission spacecraftA preliminary design of a spacecraft shield system to defeat meteoroids and orbital debris during a Mars mission is presented. The mission scenario is first defined in terms of stage times which include LEO, transit, low-Mars orbit, and Mars surface periods. The environment definitions for earth-orbital space debris, planetary meteoroids, and interplanetary meteoroids are next introduced. Shield system design approaches incorporate stochastic simulation, hydrocode analyses, hypervelocity impact testing, and optimization techniques. Structural design trades presented include spacecraft configuration, mission schedule, penetration risk, and total standoff distance between the bumper and wall.
Document ID
19920055936
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Robinson, J. H. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Mog, R. A. (Science Applications International Corp. Huntsville, AL, United States)