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Micrometeoroid and Orbital Debris Threat Assessment: Mars Sample Return Earth Entry VehicleThis report provides results of a Micrometeoroid and Orbital Debris (MMOD) risk assessment of the Mars Sample Return Earth Entry Vehicle (MSR EEV). The assessment was performed using standard risk assessment methodology illustrated in Figure 1-1. Central to the process is the Bumper risk assessment code (Figure 1-2), which calculates the critical penetration risk based on geometry, shielding configurations and flight parameters. The assessment process begins by building a finite element model (FEM) of the spacecraft, which defines the size and shape of the spacecraft as well as the locations of the various shielding configurations. This model is built using the NX I-deas software package from Siemens PLM Software. The FEM is constructed using triangular and quadrilateral elements that define the outer shell of the spacecraft. Bumper-II uses the model file to determine the geometry of the spacecraft for the analysis. The next step of the process is to identify the ballistic limit characteristics for the various shield types. These ballistic limits define the critical size particle that will penetrate a shield at a given impact angle and impact velocity. When the finite element model is built, each individual element is assigned a property identifier (PID) to act as an index for its shielding properties. Using the ballistic limit equations (BLEs) built into the Bumper-II code, the shield characteristics are defined for each and every PID in the model. The final stage of the analysis is to determine the probability of no penetration (PNP) on the spacecraft. This is done using the micrometeoroid and orbital debris environment definitions that are built into the Bumper-II code. These engineering models take into account orbit inclination, altitude, attitude and analysis date in order to predict an impacting particle flux on the spacecraft. Using the geometry and shielding characteristics previously defined for the spacecraft and combining that information with the environment model calculations, the Bumper-II code calculates a probability of no penetration for the spacecraft.
Document ID
20140001399
Acquisition Source
Johnson Space Center
Document Type
Other
Authors
Christiansen, Eric L. (NASA Johnson Space Center Houston, TX, United States)
Hyde, James L. (NASA Johnson Space Center Houston, TX, United States)
Bjorkman, Michael D. (NASA Johnson Space Center Houston, TX, United States)
Hoffman, Kevin D. (NASA Johnson Space Center Houston, TX, United States)
Lear, Dana M. (NASA Johnson Space Center Houston, TX, United States)
Prior, Thomas G. (NASA Johnson Space Center Houston, TX, United States)
Date Acquired
March 13, 2014
Publication Date
September 1, 2011
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
JSC-CN-29176
JSC-66287
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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