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  • SPACE VEHICLES  (69)
  • ASTROPHYSICS
  • 1970-1974  (69)
  • 1973  (69)
  • 1
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    A nonlinear programming approach for optimizing two-stage lifting vehicle ascent to orbit (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An optimal atmospheric flight branched trajectory-shaping capability is presented based on the Davidon-Fletcher-Powell variable metric parameter optimization technique. Gradient information is generated using finite difference methods. A typical atmospheric flight branched optimization problem is analyzed which requires the determination of 31 parameters. This parameter set includes the three-dimensional description of vehicle attitude control angles for three branches of flight: first-stage ascent, second-stage ascent, and first-stage flyback. The important inflight inequality contraints required to maintain the integrity of the vehicles are considered. Some of the numerical methods employed are discussed, along with several new auxiliary techniques developed to improve the compatibility of the numerical gradient and iterator.
    Keywords: SPACE VEHICLES
    Type: Automatica; 9; Nov. 197
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    NASA TECHNICAL REPORTS
  • 2
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    Development of a direct condensing radiator for use in a spacecraft vapor compression refrigeration system. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: SPACE VEHICLES
    Type: ASME PAPER 73-ENAS-5 , Intersociety Conference on Environmental Systems; Jul 16, 1973 - Jul 19, 1973; San Diego, CA; US
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    NASA TECHNICAL REPORTS
  • 3
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    Design, capability, and cost of a Versatile Upper Stage /VUS/ family of vehicles. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Trade-off studies and a preliminary design were accomplished to investigate the Versatile Upper Stage (VUS) concept. This concept entails the development by one contractor of a family of stages with a great deal of commonality to perform a spectrum of potential unmanned automated missions planned through 1990. The trade studies and analyses revealed areas where the penalty for commonality between stages was excessive in weight and performance loss. This occurred in the selection of the vehicle structural shell. In many of the expensive subsystems, especially astrionics, it was found that establishing the requirements for all family members and the application of commonality in subsystem selection could result in significant savings.
    Keywords: SPACE VEHICLES
    Type: AIAA PAPER 73-589 , Joint Space Mission Planning and Execution Meeting; Jul 10, 1973 - Jul 12, 1973; Denver, CO
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    NASA TECHNICAL REPORTS
  • 4
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    The cylindrical electrostatic probes for Atmosphere Explorer -C, -D, and -E. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: This paper briefly describes the cylindrical electrostatic probes to be used on the new Atmosphere Explorer-C, -D, and -E, and outlines the methods to be employed to analyze the experimental data in terms of electron temperature and ion and electron concentration. Two independent cylindrical sensors and partially redundant electronic systems permit greater reliability in measurements. Measurements are made at 1-sec and 2-sec intervals along the orbit. The sensors themselves have been modified from previous applications to cope with the lower electron temperature expected in these low-altitude orbits and to counter possible surface contamination caused by the hydrazine engines used for orbit adjustments.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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  • 5
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    The Bennett ion-mass spectrometer on Atmosphere Explorer-C and -E. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Bennett spectrometer to be flown on Atmosphere Explorer-C and -E (AE-C and AE-E) is designed to measure, throughout the 120 to 4000-km orbit, the concentrations of all thermal positive ions in the mass range 1 to 72 amu and number density range 5 to 5,000,000 ions per cu cm. To reduce the buildup of ram pressure and facilitate measurements at low altitude, the analyzer is vented, and a multigrid ion-current collector is employed. An extensive command capability permits optimization of instrument parameters for particular measurement objectives; commandable functions include mass-scan range and period, the sensitivity-resolution characteristic of the analyzer, orifice potential, and in-flight calibration.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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  • 6
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    Status report on shuttle program. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Following a brief summary of previous work, major attention is given to Phase-B extension, the Request for Proposal (RFP), the selected configuration and associated activities, and the future. NASA extended Phase-B contracts to examine other options that might lower peak annual funding and decrease program risk. Most of the discussion deals with the shuttle and orbiter systems. The efforts of the shuttle program in the past year have seen the completion of numerous trade studies and the selection of a prime shuttle contractor.
    Keywords: SPACE VEHICLES
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  • 7
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    Low-energy electron experiment for Atmosphere Explorer-C and -D. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The low-energy electron experiment will provide differential measurements of the energy influx and angular distributions of electrons and protons on the Atmosphere Explorer-C and -D missions. The detectors consist of cylindrical electrostatic analyzers for species and energy selection and Spiraltron electron multipliers as particle sensors. The C version will contain three detectors, two measuring electrons and protons from 0.2 to 25 keV in 16 logarithmically spaced steps and one measuring 5 keV electrons continuously. Angular distributions will be acquired utilizing the spin of the spacecraft. The D version will contain 19 detectors, one proton-stepped energy analyzer, and two electron-stepped energy analyzers at two different angles, again over the energy range 0.2 to 25 keV.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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  • 8
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    The Atmosphere Explorer spacecraft system. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Brief description of the design goals, spacecraft, data system, and data analysis concept for the Atmosphere Explorer (AE) mission. The AE mission is shown to have been conceived and to be implemented for making possible a variety of studies of the lower thermosphere. The spacecraft support system, including an onboard propulsion system, will enable investigations to be carried out deep in the thermosphere and at all points of aeronomic significance about the earth.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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  • 9
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    Unsteady aerodynamic analysis of space shuttle vehicles. Part 3: Booster interference effects (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation of the interference flow field on the space-shuttle boost configuration has been made. The results show that the interference effects can dominate the shuttle aerodynamics. Vortices shed from shock-induced flow separations on the forward portion of the vehicle affect the aerodynamic loads on the aft portion of the booster. Thus, the forebody and aft-body flow fields are coupled. This coupling and the associated time lag due to the finite convection speed of the vortices furnish a mechanism whereby the unsteady aerodynamics can cause undamping of certain low frequency elastic modes of the booster. A preliminary order-of-magnitude analysis of the aeroelastic stability of the shuttle booster indicates that negative aerodynamic damping could occur for at least one bending mode and be of sufficient magnitude to dominate the structural damping. The implication of these results, (with the possibility of undamped oscillations leading to structural failure), is serious enough to warrant further, more detailed analysis.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120124 , LMSC-D352320-PT-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Functional requirements for onboard management of space shuttle consumables, volume 2. (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was conducted to develop the functional requirements for onboard management of space shuttle consumables. A specific consumables management concept for the space shuttle vehicle was developed and the functional requirements for the onboard portion of the concept were generated. Consumables management is the process of controlling or influencing the usage of expendable materials involved in vehicle subsystem operation. The subsystems considered in the study are: (1) propulsion, (2) power generation, and (3) environmental and life support.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134145 , TRW-22104-H002-RO-00-VOL-2
    Format: application/pdf
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