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  • PROPULSION SYSTEMS  (104)
  • ASTROPHYSICS
  • 1970-1974  (104)
  • 1955-1959
  • 1973  (52)
  • 1972  (52)
Collection
Keywords
Years
  • 1970-1974  (104)
  • 1955-1959
Year
  • 1
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    Optimal low thrust geocentric transfer (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computer code which will rapidly calculate time-optimal low thrust transfers is being developed as a mission analysis tool. The final program will apply to NEP or SEP missions and will include a variety of environmental effects. The current program assumes constant acceleration. The oblateness effect and shadowing may be included. Detailed state and costate equations are given for the thrust effect, oblateness effect, and shadowing. A simple but adequate model yields analytical formulas for power degradation due to the Van Allen radiation belts for SEP missions. The program avoids the classical singularities by the use of equinoctial orbital elements. Kryloff-Bogoliuboff averaging is used to facilitate rapid calculation. Results for selected cases using the current program are given.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1074 , Electric Propulsion Conference; Oct 31, 1973 - Nov 02, 1973; Lake Tahoe, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Development of propulsion for high atmospheric pressure or dense environments (1973)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: The development of a propulsion system that employs a detonating propellant is described, and the need for such a system and its use in certain planetary atmospheres are demonstrated. A theoretical formulation of the relevant gas-dynamic processes was developed, and a related series of experimental tests were pursued.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 45-52
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Impact resistance of fiber composite blades used in aircraft turbine engines (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Resistance of advanced fiber reinforced epoxy matrix composite materials to ballistic impact was investigated as a function of impacting projectile characteristics, and composite material properties. Ballistic impact damage due to normal impacts, was classified as transverse (stress wave delamination and splitting), penetrative, or structural (gross failure). Steel projectiles were found to be gelatin ice projectiles in causing penetrative damage leading to reduced tensile strength. Gelatin and ice projectiles caused either transverse or structural damage, depending upon projectile mass and velocity. Improved composite transverse tensile strength, use of dispersed ply lay-ups, and inclusion of PRD-49-1 or S-glass fibers correlated with improved resistance of composite materials to transverse damage. In non-normal impacts against simulated blade shapes, the normal velocity component of the impact was used to correlate damage results with normal impact results. Stiffening the leading edge of simulated blade specimens led to reduced ballistic damage, while addition of a metallic leading edge provided nearly complete protection against 0.64 cm diameter steel, and 1.27 cm diameter ice and gelatin projectiles, and partial protection against 2.54 cm diameter projectiles of ice and gelatin.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134502 , PWA-4727
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Upper-stage space shuttle propulsion by means of separate scramjet and rocket engines (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary mission study of a reusable vehicle from staging to orbit indicates payload advantages for a dual-propulsion system consisting of separate scramjet and rocket engines. In the analysis the scramjet operated continuously and the initiation of rocket operation was varied. For a stage weight of 500,000 lb the payload was 10.4 percent of stage weight or 70 percent greater than that of a comparable all-rocket-powered stage. When compared with a reusable two-state rocket vehicle having 50,000 lb payload, the use of the dual propulsion system for the second stage resulted in significant decreases in lift-off weight and empty weight, indicating possible lower hardware costs.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-6762 , E-6555
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Solid propellant rocket motor (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The characteristics of a solid propellant rocket engine with a controlled rate of thrust buildup to a desired thrust level are discussed. The engine uses a regressive burning controlled flow solid propellant igniter and a progressive burning main solid propellant charge. The igniter is capable of operating in a vacuum and sustains the burning of the propellant below its normal combustion limit until the burning propellant surface and combustion chamber pressure have increased sufficiently to provide a stable chamber pressure.
    Keywords: PROPULSION SYSTEMS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Highly noise suppressed bypass 6 engine for STOL application (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A TF-34 engine with an acoustically treated ground test nacelle was built and tested to determine the feasibility of suppressing fan and core engine noise to the stringent levels required for STOL or short-haul commercial aircraft. The design incorporates wall treatment for the fan and core plus three treated splitter rings in the inlet and two treated splitters in the aft fan duct. Maximum suppression of fan tone noise of 40-45 dB was obtained from both the inlet and aft fan treatment. At rated fan speed, overall noise was reduced by 21 PNdB to a value of 94 PNdB on a 500-foot sideline. The overall noise reduction value was limited by the jet noise floor. Thrust losses due to the acoustic treatment are also discussed.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1031 , Aero-Acoustics Conference; Oct 15, 1973 - Oct 17, 1973; Seattle, WA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    An injector design model for predicting rocket engine performance and heat transfer (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A model is formulated for estimating the performance and chamber heat transfer in rocket injectors/chambers operating with gaseous H2-O2 propellants. The model quantifies the combustion performance and chamber heat flux for variables such as chamber length, element type, element area ratio, impingement angle, thrust/element, mixture ratio, moment ratio, element spacing, and physical size. Design equations are given and curves are plotted for evaluation of combustion performance in injectors comprised of F-O-F triplet, premix, coaxial and swirl coaxial element types. Curve plots and equations are also included for estimation of the chamber wall heat fluxes generated by these element types.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1242 , Propulsion Conference; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Evaluation of acoustic cavities for combustion stabilization. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The stabilizing influence of acoustic cavities (quarterwave acoustic resonators) on acoustic modes of combustion instability has been studied. The ability to analytically predict cavity damping was improved. Relatively good agreement between predicted damping and measured stability was demonstrated. Full-scale motor firings were made to evaluate the influence of several parameters on stability. Results from these firings showed that stability was changed, but not dramatically, by changes in the engine operating conditions. Variations in the film-coolant flowrate do not significantly affect cavity stabilization. The ability to stabilize an engine with unconventional cavity configurations was demonstrated.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 72-1147 , Joint Propulsion Specialist Conference; Nov 29, 1972 - Dec 01, 1972; New Orleans, LA; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Velocity diagrams (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The selection and design of velocity diagrams for axial flow turbines are considered. Application is treated in two parts which includes: (1) mean-section diagrams, and (2) radial variation of diagrams. In the first part, the velocity diagrams occurring at the mean section are assumed to represent the average conditions encountered by the turbine. The different types of diagrams, their relation to stage efficiency, and their selection when staging is required are discussed. In the second part, it is shown that in certain cases the mean-section diagrams may or may not represent the average flow conditions for the entire blade span. In the case of relatively low hub- to tip-radius ratios, substantial variations in the velocity diagrams are encountered. The radial variations in flow conditions and their effect on the velocity diagrams are considered.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 1; p 69-99
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Mariner 9 propulsion subsystem performance during interplanetary cruise and Mars orbit insertion (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: On 14 November 1971 the Mariner 9 1334-N-(300-lbf)-thrust rocket engine was fired for just over 15 min to place the first man-made satellite into orbit about Mars. Propulsion subsystem data gathered during the 5-month interplanetary cruise and orbit insertion are of significance to future missions of this type. Specific results related to performance predictability, zero g heat transfer, and nitrogen permeation, diffusion, and solubility values are presented.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 113-122
    Format: text
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    NASA TECHNICAL REPORTS
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