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  • 1
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    Solid rocket technology advancements for space tug and IUS applications (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: In order for the shuttle tug or interim upper stage (IUS) to capture all the missions in the current mission model for the tug and the IUS, an auxiliary or kick stage, using a solid propellant rocket motor, is required. Two solid propellant rocket motor technology concepts are described. One concept, called the 'advanced propulsion module' motor, is an 1800-kg, high-mass-fraction motor, which is single-burn and contains Class 2 propellent. The other concept, called the high energy upper stage restartable solid, is a two-burn (stop-restartable on command) motor which at present contains 1400 kg of Class 7 propellant. The details and status of the motor design and component and motor test results to date are presented, along with the schedule for future work.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-145561 , JPL-TM-33-746
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The JPL advanced propulsion module motor chamber (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A Kevlar 49/epoxy chamber has been developed for the advanced propulsion module motor. This chamber was successfully designed, fabricated, and hydroproof-tested at 511.6 N/sq cm. The fabrication, interior dimensional inspection, and proof test are discussed, showing that the chamber will be capable of achieving the design burst pressure of 639.8 N/sq cm. The projected chamber growth at 448.2 N/sq cm is presented based on the strain gage and volumetric growth data collected in that proof test.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 76-637 , Propulsion Conference; Jul 26, 1976 - Jul 29, 1976; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Cryogenic Fluid Management Facility (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Cryogenic Fluid Management Facility (CFMF) is a reusable test bed which is designed to be carried into space in the Shuttle cargo bay to investigate systems and technologies required to efficiently and effectively manage cryogens in space. The facility hardware is configured to provide low-g verification of fluid and thermal models of cryogenic storage, transfer concepts and processes. Significant design data and criteria for future subcritical cryogenic storage and transfer systems will be obtained. Future applications include space-based and ground-based orbit transfer vehicles (OTV), space station life support, attitude control, power and fuel depot supply, resupply tankers, external tank (ET) propellant scavenging, space-based weapon systems and space-based orbit maneuvering vehicles (OMV). This paper describes the facility and discusses the cryogenic fluid management technology to be investigated. A brief discussion of the integration issues involved in loading and transporting liquid hydrogen within the Shuttle cargo bay is also included.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 84-1340
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Shuttle solid rocket motor nozzle alternate ablative evaluation (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A series of subscale tests are shown to suggest that a lower-cost ablative material than the rayon-based carbon ablative currently used in the Space Shuttle Solid Rocket Motor (SRM) may be used as a substitute. Six such ablatives with outstanding performance characteristics, using spun PAN and continuous pitch and PAN fibers instead of the present, continuous rayon, were identified in the course of tests with HTPB/AL/AP solid propellant grains with a burn time of 12 sec. The test nozzle features an initial throat diameter of 2.2 in. and a 6.1 expansion ratio. In addition to nozzle structural feature drawings, extensive test data tables and propellant formulation and properties tables are provided.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 81-1461 , Joint Propulsion Conference; Jul 27, 1981 - Jul 29, 1981; Colorado Springs, CO; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Shuttle subscale ablative nozzle tests (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Recent subscale nozzle tests have identified new and promising carbon phenolic nozzle ablatives which utilize staple rayon, PAN, and pitch based carbon cloth. A 4-inch throat diameter submerged test nozzle designed for the 48-inch Jet Propulsion Laboratory char motor was used to evaluate five different designs incorporating 20 candidate ablatives. Test results indicate that several pitch and PAN-based carbon phenolic ablatives can provide erosion and char performance equivalent or superior to the present continuous rayon-based SRM ablative.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 80-1102 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Solid rocket technology advancement for Space Tug and IUS applications (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Two-burn restartable solid propellant rocket motors for the kick stage (auxiliary stage) of the Shuttle Tug, or Interim Upper Stage, are described, with details on features and test results of the ignition and quench (thrust termination) systems and procedures, fabrication of propellant and insulation, explosion hazards of propellants, and comparative data on present and future motor design. These rocket motor systems are designed for upper stage augmentation of launch vehicles and possible service in Shuttle-launched outer planet spacecraft.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AAS PAPER 75-159 , Meeting on Space Shuttle Missions of the 80''s; Aug 26, 1975 - Aug 28, 1975; Denver, CO
    Format: text
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    NASA TECHNICAL REPORTS
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