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  • SPACE VEHICLES  (108)
  • 2020-2023
  • 2010-2014
  • 1970-1974  (108)
  • 1965-1969
  • 1935-1939
  • 1972  (108)
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  • 2020-2023
  • 2010-2014
  • 1970-1974  (108)
  • 1965-1969
  • 1935-1939
Year
  • 1
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    Status of reusable surface insulation thermal protection system technology programs (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of three low-density rigidized insulation materials for the shuttle TPS application is reported. These materials consist of one high purity silica system and two systems based on mullite, an aluminum silicate. Both systems consist of fibers joined together with appropriate binders to obtain a rigidized insulation composite. Both material systems require the application of a glassy coating to provide a wear resistant, high emittance surface and to prevent the absorption of water by the fiber matrix. The technology program has addressed the development of water impervious coatings, methods of assembling the materials in design concepts while minimizing the thermal stress in the insulation, achieving compatibility between the RSI material and the structural system, and test evaluations to demonstrate the feasibility of the surface insulation concept.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 435-474
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Orbital propellant depot system. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Review of some of the problems involved in the design of a long-term propellant storage depot in earth orbit to act as a resupply station for cargo/personnel shuttles between earth orbit and lunar orbit, between low earth orbit and synchronous orbit, and possibly for use with interplanetary probes. The problems discussed pertain essentially to the long-term storage and propellant transfer capabilities.
    Keywords: SPACE VEHICLES
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The computation of optimal control programmes using a modified successive sweep method. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A second-order method for numerically solving control optimization problems has been developed. The method, referred to as the modified sweep method (MSM), differs from the successive sweep method (SSM) proposed by McReynolds and Bryson (1965) in that the conditions for local control optimality are used to determine the control as an explicit function of the state variables and time. The control is eliminated from the problem and the solution to the resulting two-point boundary value problem can be obtained by linear perturbation methods. The modified sweep method proposed here uncouples the perturbation equations for the state variables and the Lagrange multipliers by using a generalized matrix-Riccati transformation of variables. The resulting algorithm for the numerical iteration process is concerned with determining the initial values of a set of Lagrange multipliers rather than correcting a numerical control programme over the entire time interval of interest.
    Keywords: SPACE VEHICLES
    Type: International Journal of Control; vol. 15
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Cometary Explorer to Grigg-Skjellerup 1977 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The mission analysis and technical summary of the spacecraft and its subsystems are presented for an Explorer flight to investigate the solar wind interaction with the Grigg-Skjellerup coma. The basic spacecraft system is the same as Explorer 43 and 47, and the mission characteristics which distinguish this mission from previous IMP missions are discussed. The physical and chemical characteristics of the comet's nucleus and coma are described, and the spacecraft trajectory and scientific payloads required to study the solar wind-cometary atmospheric interaction are considered.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-66023 , X-690-72-337
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Synthesis of shuttle vehicle damping using substructure test results (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An empirical method is developed for predicting the modal damping of a combined parallel-stage shuttle model by means of damping measurements performed on the individual substructures. Correlations are first determined for each component in terms of damping energy as a function of peak kinetic energy and modal amplitude. The results are then used to predict component damping energies corresponding to the respective kinetic energies and amplitudes that occur for the new modes of the combined system. Modal characteristics for the system, other than damping, are obtained by a real eigenvalue solution of dynamic equations developed by Hurty's procedure of substructures. System equations, which include component modal damping, are also solved by a complex eigenvalue approach for comparison with results of the empirical method.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-123791
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Heat transfer investigation of two Langley Research Center delta wing configurations at a Mach number of 10.5, volume 1 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat transfer tests for two delta wing configurations were conducted in the hypervelocity wind tunnel. The 24-inch long models were tested at a Mach number of approximately 10.5 and at angles of attack of 20, 40, and 60 degrees over a length Reynolds number range from 5 million to 23 million on 4 May to 4 June 1971. Heat transfer results were obtained from model surface heat gage measurements and thermographic phosphor paint.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120036 , DMS-DR-1224-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Absolute stability analysis of attitude control systems for large boosters. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A method for performing absolute stability analyses of attitude control systems for large launch vehicles is presented. Absolute stability of these systems is shown in a finite region of the state space. The regions are computed by using the Lur'e-Postnikov Liapunov function. This function is chosen to provide additional information about the exponential property of absolute stability. Significant advantages of the method proposed in this paper are: it is independent of the order of the system; algebraic operations involved in the computations are relatively simple and convenient for machine implementation; and the obtained results are valid not only for a particular nonlinearity but also for an entire class of nonlinear characteristics that satisfy certain general conditions. A system model representing the Saturn V launch vehicle is used to illustrate the method.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 9; July 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Space shuttle: Aerodynamic characteristics of 0.003367 scale models of the MMC retro-glide booster alone and mated with the MSC 040-A orbiter (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Plotted data results are presented of aerodynamic tests conducted on the 0.003367 scale models of the retro-glide booster alone and mated with the 040A orbiter. The test was conducted in the NASA/MSFC 14 Inch Trisonic Wind Tunnel over a Mach number range of 0.6 to 4.95 with angles of attack varying from -10 deg to 60 deg. The test was to obtain six degree of freedom force and moment data on the launch configuration and booster reentry configuration for preliminary stability and control analysis.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120031 , DMS-DR-1213
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Determination of contamination character of materials in space technology testing (1972)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The contamination character of selected materials used in space technology testing is presented. Many of these materials contain components that become volatile in a space environment. Most previous data were limited to weight loss or vapor pressure. However, these parameters are not necessarily a direct measure of the contamination character of these materials. Selected materials were exposed to a thermal-vacuum environment, and the degree of contamination was measured by collecting the outgases from these materials on a cold test mirror surface. The degradation of reflectivity of the mirror was measured over a spectral range from 1100 A to 2.5 microns. Half the mirror's surface was also exposed to UV irradiation to determine its effects on the contaminative character of the depositing outgases. The amount of deposit per unit area was measured by microbalances mounted near the mirror; the sensor of one microbalance was UV irradiated. A quadrupole mass spectrometer was used to determine the composition of the outgases.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-130132
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Coupling between structure and liquid propellants in a parallel-stage space shuttle design. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A study was conducted to determine the influence of liquid propellants on the dynamic loads for space shuttle vehicles. A parallel-stage configuration model was designed and tested to determine the influence of liquid propellants on coupled natural modes. A forty degree-of-freedom analytical model was also developed for predicting these modes. Currently available analytical models were used to represent the liquid contributions, even though coupled longitudinal and lateral motions are present in such a complex structure. Agreement between the results was found in the lower few modes.
    Keywords: SPACE VEHICLES
    Type: AIAA PAPER 72-347 , Structures, Structural Dynamics, and Materials Conference; Apr 10, 1972 - Apr 12, 1972; San Antonio, TX
    Format: text
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