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  • SPACE VEHICLES  (446)
  • 1990-1994
  • 1970-1974  (446)
  • 11
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    Action on mission evaluation and flight anomalies (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Apollo Program mission evaluation and flight anomalies team to indentify and understand unforeseen peculiarities and systems problems during spacecraft mission
    Keywords: SPACE VEHICLES
    Type: ; DIOTEKHNIKA (
    Format: text
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    NASA TECHNICAL REPORTS
  • 12
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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
  • 13
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    Introduction (1970)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: Saturn launch vehicle configurations, stages, and guidance and control systems, and wind effects on vehicle design
    Keywords: SPACE VEHICLES
    Type: AGARD WIND EFFECTS ON LAUNCH VEHICLES FEB. 1970; P 13-32
    Format: text
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    NASA TECHNICAL REPORTS
  • 14
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    Space vehicle integrated thermal protection/structural/meteoroid protection system, volume 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see .
    Keywords: SPACE VEHICLES
    Type: NASA-CR-121104 , D180-15172-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    Effects of certain control-system nonlinearities on stability and pointing of an attached double-gimbal experiment package in presence of random crew-motion disturbances (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of two types of control-system nonlinearities, sensor deadband and actuator breakout torque, on the pointing capability of a Apollo Telescope Mount (ATM) double-gimbal experiment isolation and control system are investigated. A composite structural model of a flexible experiment package connected through frictionless double gimbals to a flexible carrier vehicle is used for this investigation. Contributions of the primary carrier control system to experiment pointing are neglected. Pointing errors onboard the experiment package due to random crew-motion input into the carrier vehicle are computed. A stability investigation is performed to verify control-system stability with nominal nonlinearities and gains. Indications are that there is no stability problem due to the nonlinearities. A nonlinearity sensitivity study is carried out to determine the effects on pointing accuracy. Its results indicate that nominal ATM control system nonlinearities limit the pointing accuracy to approximately 0.4 arc second in the presence of crew motion. Methods of reducing the error to less than 0.1 arc second are discussed.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7247 , L-7899
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 16
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    Space vehicle integrated thermal protection/structural/meteoroid protection system, volume 1 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A program was conducted to determine the merit of a combined structure/thermal meteoroid protection system for a cryogenic vehicle propulsion module. Structural concepts were evaluated to identify least weight designs. Thermal analyses determined optimum tank arrangements and insulation materials. Meteoroid penetration experiments provided data for design of protection systems. Preliminary designs were made and compared on the basis of payload capability. Thermal performance tests demonstrated heat transfer rates typical for the selected design. Meteoroid impact tests verified the protection characteristics. A mockup was made to demonstrate protection system installation. The best design found combined multilayer insulation with a truss structure vehicle body. The multilayer served as the thermal/meteoroid protection system.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-121103 , D180-15172-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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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
  • 18
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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
  • 19
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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
  • 20
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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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