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  • 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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    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
  • 3
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    A Survey of Titan Balloon Concepts and Technology Status (2011)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper surveys the options for, and technology status of, balloon vehicles to explore Saturn's moon Titan. A significant amount of Titan balloon concept thinking and technology development has been performed in recent years, particularly following the spectacular results from the descent and landing of the Huygens probe and remote sensing observations by the Cassini spacecraft. There is widespread recognition that a balloon vehicle on the next Titan mission could provide an outstanding and unmatched capability for in situ exploration on a global scale. The rich variety of revealed science targets has combined with a highly favorable Titan flight environment to yield a wide diversity of proposed balloon concepts. The paper presents a conceptual framework for thinking about balloon vehicle design choices and uses it to analyze various Titan options. The result is a list of recommended Titan balloon vehicle concepts that could perform a variety of science missions, along with their projected performance metrics. Recent technology developments for these balloon concepts are discussed to provide context for an assessment of outstanding risk areas and technological maturity. The paper concludes with suggestions for technology investments needed to achieve flight readiness.
    Keywords: Aerodynamics; Spacecraft Design, Testing and Performance
    Type: AIAA Balloon Systems Conference; Sep 20, 2011 - Sep 22, 2011; Virginia Beach, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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