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  • Spacecraft Design, Testing and Performance  (2)
  • Technology Utilization and Surface Transportation  (1)
  • 2020-2024
  • 2005-2009  (3)
  • 1
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    Ultra Lightweight Ballutes for Return to Earth from the Moon (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Ultra lightweight ballutes offer revolutionary mass and cost benefits along with flexibility in flight system design compared to traditional entry system technologies. Under funding provided by NASA s Exploration Systems Research & Technology program, our team was able to make progress in developing this technology through systems analysis and design, evaluation of materials and construction methods, and development of critical analysis tools. Results show that once this technology is mature, significant launch mass savings, operational simplicity, and mission robustness will be available to help carry out NASA s Vision for Space Exploration.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA Paper 2006-1698 , 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; May 01, 2006 - May 04, 2006; Newport, RI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Aerial Deployment and Inflation System for Mars Helium Balloons (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A method is examined for safely deploying and inflating helium balloons for missions at Mars. The key for making it possible to deploy balloons that are light enough to be buoyant in the thin, Martian atmosphere is to mitigate the transient forces on the balloon that might tear it. A fully inflated Mars balloon has a diameter of 10 m, so it must be folded up for the trip to Mars, unfolded upon arrival, and then inflated with helium gas in the atmosphere. Safe entry into the Martian atmosphere requires the use of an aeroshell vehicle, which protects against severe heating and pressure loads associated with the hypersonic entry flight. Drag decelerates the aeroshell to supersonic speeds, then two parachutes deploy to slow the vehicle down to the needed safe speed of 25 to 35 m/s for balloon deployment. The parachute system descent dynamic pressure must be approximately 5 Pa or lower at an altitude of 4 km or more above the surface.
    Keywords: Technology Utilization and Surface Transportation
    Type: NPO-44688 , NASA Tech Briefs, July 2009; 22-23
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aerocapture Systems Analysis for a Neptune Mission (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A Systems Analysis was completed to determine the feasibility, benefit and risk of an aeroshell aerocapture system for Neptune and to identify technology gaps and technology performance goals. The systems analysis includes the following disciplines: science; mission design; aeroshell configuration; interplanetary navigation analyses; atmosphere modeling; computational fluid dynamics for aerodynamic performance and aeroheating environment; stability analyses; guidance development; atmospheric flight simulation; thermal protection system design; mass properties; structures; spacecraft design and packaging; and mass sensitivities. Results show that aerocapture is feasible and performance is adequate for the Neptune mission. Aerocapture can deliver 1.4 times more mass to Neptune orbit than an all-propulsive system for the same launch vehicle and results in a 3-4 year reduction in trip time compared to all-propulsive systems. Enabling technologies for this mission include TPS manufacturing; and aerothermodynamic methods for determining coupled 3-D convection, radiation and ablation aeroheating rates and loads.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA/TM-2006-214300 , L-19236
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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