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  • Other Sources  (320)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (320)
  • 2015-2019
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  • 1986  (320)
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  • 1
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    GAS ejection system overview and design enhancements (1986)
    In:  CASI
    Details
    Publication Date: 2006-06-12
    Description: The structural design of the Get Away Special (GAS) ejection system is described. Equipment specifications and modifications are illustrated. Future goals are listed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 185-190
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The GLOMR satellite payload G-308 (1986)
    In:  CASI
    Details
    Publication Date: 2006-06-12
    Description: The Global Low Orbiting Message Relay (GLOMR) Satellite and its participation in the pioneering development of a Get Away Special (GAS) satellite launch capability is described. The GLOMR is a data relay communication satellite. Experiment objectives are to demonstrate the store-forward relay of data/messages and the communication to ground user equipment. The 150 pound brass satellite, powered by lead acid batteries and solar cells, includes processing, control and radio frequency electronics for data message handling and storage. The GLOMR is mounted through a Marman clamp ejection/retention pedestal to a five cubic foot GAS canister bottom plate. The GAS canister includes a Full Diameter Motorized Door Assembly lid which is opened remotely by astronauts for satellite launch.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: The 1985 Get Away Special Experimenter's Symposium; p 285-291
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    NASA TECHNICAL REPORTS
  • 3
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    The making of a precedent: The Synthetic-Aperture Radar (SAR) on Magellan (1986)
    In:  CASI
    Details
    Publication Date: 2004-10-30
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: V-Gram: Magellan Quarterly Bulletin about Venus and the Radar Mapping Mission, Issue 9; p 3-10
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Magellan update (1986)
    In:  CASI
    Details
    Publication Date: 2004-10-30
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: V-Gram: Magellan Quarterly Bulletin about Venus and the Radar Mapping Mission, Issue 9; p 1-3
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    NASA TECHNICAL REPORTS
  • 5
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    Mission and space vehicle concepts (1986)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A number of top-level considerations which affect Mars and vehicle selection are discussed. Indications are provided of the nature and severity of the impact of these considerations on missions and vehicles. Various types of missions, such as Mars fly-bys, Mars orbiting and landing mission, and missions to the moons of Mars are identified and discussed. Mission trajectories and opportunities are discused briefly. The different types of vehicles required in a Mars program are also discussed. Discussion includes several potential Earth-to-Orbit (ETO) vehicles, Mars surface vehicles, and 2 types of Orbit-to-Orbit (OTO) vehicles. Indications are provided as to preference for some of the concepts discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 275-291
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    NASA TECHNICAL REPORTS
  • 6
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    Tethers and gravity in space (1986)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The life science objectives concerning gravitational effects in space are summarized. The use of rotation, centrifuge, and tether techniques to produce variable gravity in space are presented. The station and tether platform concept are presented for the Gravlab design.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Vol. 2; p 125-135
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  • 7
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    Artificial or variable gravity attained by tether systems (1986)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The simplest orbiting tethered system demands for stability that the mass centers of two end bodies be displaced above and below the position of zero acceleration. Therefore, the contents of the end bodies are subjected necessarily to acceleration fields or artificial gravity whose magnitudes depend on the dimensions and masses of the system. If the length of the tether changes, so do the fields. Even for a fixed tether length, the acceleration field at a location in the system may be somewhat variable unless special means are employed to maintain a constant value. These fundamental properties of a tethered system can be used to advantage if small or variable acceleration fields are desired for experimental or operational reasons. This potential use involves a few expressions from a formulation of tether system dynamics. Some of these formulae were collected for convenient use. Two and three body tethered equilibrium equations are explained. A special application of acceleration field control using a tether system is attainment of near-zero gravity. In this applicaition, even small variations about zero become a critical matter.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Vol. 2; p 79-86
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  • 8
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    Roles for tethers on an evolving space station (1986)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A scenario was developed for evolution of space station tether capabilities. As tether imposed constaints on station developments and operations were minimized, maximum benefits were derived from a mutually compatible combination of: (1)electrodynamic tethers for power, thrust, and libration control; (2)momentum transfer operations involving the STS or upper stages; (3)aeromaneuvering devices for space station orbital plan change; and (4)tethered constellations and tether/free-flyer combinations. Some concepts determined for advance tether facilities orbiting the moon: (1)stationkeeping deltaVs to stay in precise equatorial or polar orbits; (2)ratio of facility mass to maximum payload mass (surface-orbit-escape); (3)electric-thruster power requirements and maximum rendezvous frequencies; and (4)overall capabilities and major constraints on such facilities.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Vol. 2; p 457-472
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  • 9
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    Tethered elevator and platforms as space station facilities: Systems studies and demonstrative experiments (1986)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Several key concepts of the science and applications tethered platforms were studied. Some conclusions reached are herein listed. Tether elevator and platform could improve the space station scientific and applicative capabilities. The space elevator presents unique characteristics as microgravity facility and as a tethered platform servicing vehicle. Pointing platforms could represent a new kind of observation facility for large class of payloads. The dynamical, control and technological complexity of these concepts advised demonstrative experiments. The on-going tethered satellite system offers the opportunity to perform such experiments. And feasibility studies are in progress.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Vol. 2; p 413-455
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    NASA TECHNICAL REPORTS
  • 10
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    Tethered orbital refueling study (1986)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Objectives are to evaluate the feasibility and limitations of fluid acquisition and transfer under an accleration induced in a tethered orbital refueling facility and to provide conceptual designs. Program tasks consist of recommendation of fluid transfer method and parameters; evaluation of disturbances, fluid motion, and damping; selection of passive devices to augment inherent fluid damping and determination of the resultant envelope of operation; assessment of the effect of tether lengths on hazards; and identification of ground and flight tests necessary to prove the tethered orbital refueling concepts.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Vol. 2; p 89-123
    Format: text
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