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  • PROPULSION SYSTEMS  (295)
  • 1970-1974  (295)
  • 1965-1969
  • 1960-1964
  • 1973  (295)
Collection
Keywords
Years
  • 1970-1974  (295)
  • 1965-1969
  • 1960-1964
Year
  • 1
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    Liquid rocket pressure regulators, relief valves, check valves, burst disks, and explosive valves (1973)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The development of and operational programs for effective use in design are presented for liquid rocket pressure regulators, relief valves, check valves, burst disks, and explosive valves. A review of the total design problem is presented, and design elements are identified which are involved in successful design. Current technology pertaining to these elements is also described. Design criteria are presented which state what rule or standard must be imposed on each essential design element to assure successful design. These criteria serve as a checklist of rules for a project manager to use in guiding a design or in assessing its adequacy. Recommended practices are included which state how to satisfy each of the criteria.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-SP-8080
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    On the Design and Test of a Liquid Injection Electric Thruster (1973)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A liquid injection electric thruster (LINJET) was designed and tested. The results of the tests were very encouraging with thruster performance levels well in excess of design goals. Supporting activities to the engine design and test included a five-million pulse life test on the main capacitor, a 46-million pulse test on the trigger electronics, design and fabrication of a zero resistance torque connector for use with the torsional pendulum thrust stand, design and fabrication of a logic box for control of engine firing, and a physical and chemical properties characterization of the perfluorocarbon propellant. While the results were encouraging, testing was limited, as many problems existed with the design. The most significant problem was involved with excessive propellant flow which contributed to false triggering and shorting. Low power active thermal control of the propellant storage cavity, coupled with a re-evaluation of the injection ring pore size and area exposed to the main capacitor discharge are areas that should be investigated should this design be carried forward.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-132316
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Space shuttle RCS engine (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: The design of the space shuttle RCS engine has the primary objective of reusability with minimum servicing. Engine S/N FT-2A has successfully completed all ten environmental (salt water spray, sand and dust, vibration and humidity) and hot fire cycles with no change in engine performance (steady state or pulse mode).
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-136021 , REPT-8701-910013
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    The Space Shuttle Main Engine (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Space Shuttle Main Engine is the highest performance large rocket engine being developed in the world. This engine will be used to put the Space Shuttle orbiter vehicle into earth orbit and will be the workhorse propulsion system of the 1970s and 1980s. The propulsion requirements demand maximum performance from the liquid oxygen/hydrogen propellants with a minimum hardware weight. The system is being developed at low cost with a required early flight schedule of 1978. The engine system and components are based on the latest technology using advanced materials and high-pressure combustion. Engine weight and performance are discussed. This paper describes engine design, the program and present progress, the technology of advanced components, experimental results, and development areas underway.
    Keywords: PROPULSION SYSTEMS
    Type: International Symposium on Space Technology and Science; Sep 03, 1973 - Sep 08, 1973; Tokyo; Japan
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Extension of a simplified computer program for analysis of solid-propellant rocket motors (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A research project to develop a computer program for the preliminary design and performance analysis of solid propellant rocket engines is discussed. The following capabilities are included as computer program options: (1) treatment of wagon wheel cross sectional propellant configurations alone or in combination with circular perforated grains, (2) calculation of ignition transients with the igniter treated as a small rocket engine, (3) representation of spherical circular perforated grain ends as an alternative to the conical end surface approximation used in the original program, and (4) graphical presentation of program results using a digital plotter.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-129024
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Electrostatic propulsion beam divergence effects on spacecraft surfaces, volume 3 (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Tests were conducted to determine the effects of electrostatic propulsion beam divergence effects on spacecraft surfaces. The subjects discussed are: (1) sensitive surfaces on the ATS 6 spacecraft, (2) the cesium ion source and testing facility, (3) cesium ion effects on thermophysical properties, and (4) simulated charge-exchange ion exposure. The compatibility of the ATS 6 ion engine experiment with the engineering subsystems and other experiments aboard the ATS 6 spacecraft was analyzed.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-136933 , TRW-11985-6003-RU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Power processor for a 20CM ion thruster (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A power processor breadboard for the JPL 20CM Ion Engine was designed, fabricated, and tested to determine compliance with the electrical specification. The power processor breadboard used the silicon-controlled rectifier (SCR) series resonant inverter as the basic power stage to process all the power to the ion engine. The breadboard power processor was integrated with the JPL 20CM ion engine and complete testing was performed. The integration tests were performed without any silicon-controlled rectifier failure. This demonstrated the ruggedness of the series resonant inverter in protecting the switching elements during arcing in the ion engine. A method of fault clearing the ion engine and returning back to normal operation without elaborate sequencing and timing control logic was evolved. In this method, the main vaporizer was turned off and the discharge current limit was reduced when an overload existed on the screen/accelerator supply. After the high voltage returned to normal, both the main vaporizer and the discharge were returned to normal.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-121160 , TRW-20384-6002-RU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Hollow cathode restartable 15 cm diameter ion thruster (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effects of substituting high perveance dished grids for low perveance flat ones on performance variables and plasma properties within a 15 cm modified SERT II thruster are discussed. Results suggest good performance may be achieved as an ion thruster is throttled if the screen grid transparency is decreased with propellant flow rate. Thruster startup tests, which employ a pulsed high voltage tickler electrode between the keeper and the cathode to initiate the discharge, are described. High startup reliability at cathode tip temperatures of about 500 C without excessive component wear over 2000 startup cycles is demonstrated. Testing of a single cusp magnetic field concept of discharge plasma containment is discussed. A theory which explains the observed behavior of the device is presented and proposed thruster modifications and future testing plans are discussed.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134532
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Design considerations for the airframe-integrated scramjet (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Research programs at the NASA Langley Research Center on the development of airframe-integrated scramjet concepts (supersonic combustion ramjet) are reviewed briefly. The design and performance of a specific scramjet configuration are examined analytically by use of recently developed and substantiated techniques on boundary-layer development, heat transfer, fuel-air mixing, heat-release rates, and engine-cycle analysis. These studies indicate that the fixed-geometry scramjet module will provide practical levels of thrust performance with low cooling requirements. Areas which need particular emphasis in further development work are the combustor design for low speeds and the integrated nozzle design.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2895 , L-8152 , Intern. Symp. on Air Breathing Engines; Jun 01, 1972; Marseille; France
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Advanced hydrogen/oxygen thrust chamber design analysis (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results are reported of the advanced hydrogen/oxygen thrust chamber design analysis program. The primary objectives of this program were to: (1) provide an in-depth analytical investigation to develop thrust chamber cooling and fatigue life limitations of an advanced, high pressure, high performance H2/O2 engine design of 20,000-pounds (88960.0 N) thrust; and (2) integrate the existing heat transfer analysis, thermal fatigue and stress aspects for advanced chambers into a comprehensive computer program. Thrust chamber designs and analyses were performed to evaluate various combustor materials, coolant passage configurations (tubes and channels), and cooling circuits to define the nominal 1900 psia (1.31 x 10 to the 7th power N/sq m) chamber pressure, 300-cycle life thrust chamber. The cycle life capability of the selected configuration was then determined for three duty cycles. Also the influence of cycle life and chamber pressure on thrust chamber design was investigated by varying in cycle life requirements at the nominal chamber pressure and by varying the chamber pressure at the nominal cycle life requirement.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-121213 , R-9258
    Format: application/pdf
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