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  • LAUNCH VEHICLES AND SPACE VEHICLES  (4)
  • Man/System Technology and Life Support  (3)
  • 1
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    Ascent aeromaneuvering capabilities of transatmospheric vehicles (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 25; 19-23
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Aerothermodynamic heating and performance analysis of a high-lift aeromaneuvering AOTV concept (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 198-204
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Entry aeromaneuvering capabilities of transatmospheric vehicles (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The landing footprint of a conceptual high-lift transatmospheric vehicle is defined for aeromaneuvering entry from a typical low-earth orbit. The flight strategy for trajectory construction to maximize the landing area by extending downrange and crossrange as far as possible is developed in four phases by optimal programming of the vehicle's roll angle. Trajectories that reach any given landing site were calculated with the corresponding heating rates at three critical vehicle locations (stagnation point, wing leading edge, and body centerline). An optimization methodology was developed that demonstrates the trades between crossrange, peak heating and total heat loads as a function of three key flight parameters (altitude, flight-path angle, and vehicle roll angle). The maximum extent of the landing footprint was found to be 29,690 km downrange and 6560 km crossrange. Large variations in the ballistic coefficient had negligible effect on the extent of the footprint but could significantly affect heating. However, the footprint's longitude was displaced downstream or upstream with increasing or decreasing ballistic coefficient, respectively.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 88-0300
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Ascent aeromaneuvering capabilities of transatmospheric vehicles (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The low-earth orbit rendezvous capability of a conceptual transatmospheric vehicle is analyzed for two endo-/exo-atmospheric ascent missions. Both cases involve coasting aerodynamic maneuvers starting from the burn-out conditions corresponding to air-breathing propulsion systems that achieve orbital velocity within the atmosphere. The powered phase of the ascent trajectories approximate constant dynamic pressure, fuel-efficient flightpaths typically flown by supersonic aircraft. The aeromaneuvering coast phases of the ascent include both coplanar (to determine altitude capability without plane-inclination changes) and aeroturning to LEO rendezvous at 400 km altitude (to assess plane-change capability). The coast-phase ascent maneuvers are correlated with G-load requirements and aerothermodynamic heating characteristics at two critical locations on the vehicle surface (i.e., the nose stagnation point and the body centerline). The results are correlated and recommendations are made concerning thermal protection and structural requirements.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 87-0513
    Format: text
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  • 5
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    Spacesuit Radiation Shield Design Methods (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Meeting radiation protection requirements during EVA is predominantly an operational issue with some potential considerations for temporary shelter. The issue of spacesuit shielding is mainly guided by the potential of accidental exposure when operational and temporary shelter considerations fail to maintain exposures within operational limits. In this case, very high exposure levels are possible which could result in observable health effects and even be life threatening. Under these assumptions, potential spacesuit radiation exposures have been studied using known historical solar particle events to gain insight on the usefulness of modification of spacesuit design in which the control of skin exposure is a critical design issue and reduction of blood forming organ exposure is desirable. Transition to a new spacesuit design including soft upper-torso and reconfigured life support hardware gives an opportunity to optimize the next generation spacesuit for reduced potential health effects during an accidental exposure.
    Keywords: Man/System Technology and Life Support
    Type: 36th International Conference on Environmental Systems (ICES); Jul 17, 2006 - Jul 20, 2006; Norfolk, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Guidelines and Capabilities for Designing Human Missions (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: These guidelines and capabilities identify the points of intersection between human spaceflight crews and mission considerations such as architecture, vehicle design, technologies, operations, and science requirements. In these chapters, we will provide clear, top-level guidelines for human-related exploration studies and technology research that will address common questions and requirements. As a result, we hope that ongoing mission trade studies will consider common, standard, and practical criteria for human interfaces.
    Keywords: Man/System Technology and Life Support
    Type: NASA/TM-2003-210785 , NAS 1.15:210785 , S-895
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Description of Transport Codes for Space Radiation Shielding (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This slide presentation describes transport codes and their use for studying and designing space radiation shielding. When combined with risk projection models radiation transport codes serve as the main tool for study radiation and designing shielding. There are three criteria for assessing the accuracy of transport codes: (1) Ground-based studies with defined beams and material layouts, (2) Inter-comparison of transport code results for matched boundary conditions and (3) Comparisons to flight measurements. These three criteria have a very high degree with NASA's HZETRN/QMSFRG.
    Keywords: Man/System Technology and Life Support
    Type: JSC-CN-23008 , NCRP 2011 Annual Meeting: Scientific and Policy Challenges of Particle Radiations in Medical Therapy and Space Missions; Mar 07, 2011 - Mar 08, 2011; Bethesda, MD; United States
    Format: application/pdf
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