Mass growth in space vehicle and exploration architecture development
Mass growth in space vehicle and exploration architecture development
- New search for: Thompson, Robert W.
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- New search for: Stanley, Douglas O.
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- New search for: Thompson, Robert W.
- New search for: Wilhite, Alan W.
- New search for: Reeves, David
- New search for: Stanley, Douglas O.
- New search for: Wagner, John
AbstractInert or dry mass in aerospace systems has historically grown during aerospace vehicle development because of a number of factors: changing requirements, uncertainty in the performance of the initial technology selection, addition of redundancy, errors in the original design, as well as uncertain masses and loads. In the case of exploration architectures for lunar missions, compounding effects of a multi-staged mission design makes mass-efficient vehicles a necessity for achieving the total delta-V performance required to reach the lunar surface and return to Earth. Current standards and guidelines for mass growth risk mitigation are compared, including the industry and NASA standard methods for risk management and mitigation through the application of mass margin. Historical mass growth trends are analyzed, and average levels of growth are compared to the standard margin allocation levels. Analysis of the available historical data shows that the mean inert mass growth is 28%, and 30% of historical programs experience inert mass growth in excess of the allowable growth and margin recommended level of 32.5%. As an illustrative example of the mass growth of lunar exploration architectures the mass growth sensitivity of the Apollo architecture is calculated. Results show that a kilogram of mass growth on the lunar ascent stage is compounded over 800 times in gross mass.
Document information
Mass growth in space vehicle and exploration architecture development
Acta Astronautica ; 66 , 7-8 ; 1220-1236
2009-10-13
17 pages
Article (Journal)
Electronic Resource
English
Design , Launch vehicle , Spacecraft , Mass growth , Margin , AIAA , American Institute of Aeronautics and Astronautics , APTF , Apollo Planning Task Force , ARR , ATLO Readiness Review , ASRM , Abort Solid Rocket Motor , ATLO , Assembly, Testing, and Launch Operation , ATP , Authorization to Proceed , CBE , current best estimate , CDF , cumulative distribution function , CDR , critical design review , CEV , Crew Exploration Vehicle , CM , command module , DMM , dry mass margin , ESAS , Exploration Systems Architecture Study , FF , first flight , ISO , International Standards Organization , JPL , Jet Propulsion Laboratory , LAM , lunar ascent module , LaRC , Langley Research Center , LDM , lunar descent module , LEO , low Earth orbit , LEM , lunar excursion module , LES , Launch Escape System , LM , lunar module , MGA , mass growth allowance , NASA , National Aeronautics and Space Administration , NASP , National Aerospace Plane , PDF , probability density function , PDR , Preliminary Design Review , PMSR , Preliminary Mission System Review , SM , service module , SSTO , single stage to orbit , STS , Shuttle Transportation System , SWIP , Super Weight Improvement Program , TEI , trans-Earth injection , TLI , trans-lunar injection , ZBV , Zero Base Vehicle
Similar titles
Mass growth in space vehicle and exploration architecture development
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