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  • General Chemistry  (7.564)
  • Inorganic Chemistry  (7.395)
  • Organic Chemistry  (4.475)
  • SPACE VEHICLES  (2.693)
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  • 101
    Publikationsdatum: 2019-06-27
    Beschreibung: The concepts, design, development, testing, and flight results of the command and service module stabilization and control system are discussed. The period of time covered was from November 1961 to December 1972. Also included are a functional description of the system, a discussion of the major problems, and recommendations for future programs.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7785 , JSC-S-410
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  • 102
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The study examines the first-month space performance of 57 Goddard Space Flight Center spacecraft. It is a sequel to a previous study of first-day space malfunctions of the same 57 spacecraft. A total of 154 malfunctions, of which 88 were classified as failures, have been summarized by year of occurrence, by major subsystem of a spacecraft, by type of defect, and by severity. Of the 57 spacecraft, 45 had one or more failures during the first month in space. However, the mission criticality data show that, of the 154 malfunctions, less than 10 percent would have resulted in major loss (50-100 percent) to the mission, and due to redundancy, only 5 percent did result in major loss to the mission. The data show that more than 50 percent of the first month's failures occurred in the first operational day in space. The data also show that, for the first month in space, the ratio of system-test failures to space failures for various devices ranged from 3 to 1 up to 10 to 1. For six spacecraft programs, the ratios of test to space failures ranged from 2 to 1 up to 8 to 1.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7750 , G-7446
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  • 103
    Publikationsdatum: 2019-06-27
    Beschreibung: Data obtained during a wind tunnel test of an 0.004-scale 140A/B configuration SSV Orbiter are reported. The test was conducted at a nominal Mach number of 20 and at Reynolds numbers of 0.7, 1.1, 2.0, and 4 x 10 to the 6th power per foot. The complete 140A/B model was tested with various elevon settings and additionally in wing off/bodyflap off configurations at angles of attack from 18 to 54 degrees at zero yaw. This test was performed to obtain high hypersonic longitudinal and lateral-directional stability and control characteristics of the SSV configuration.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134409 , DMS-DR-2125
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  • 104
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests were conducted in the 31-inch continuous Flow Hypersonic Wind Tunnel to determine RCS jet interaction effect on the hypersonic aerodynamic and stability and control characteristics prior to RTLS abort separation. The model used was an 0.010-scale replica of the Space Shuttle Vehicle Configuration 3. Hypersonic stability data were obtained from tests at Mach 10.3 and dynamic pressure of 150 psf for the integrated Orbiter and external tank and the Orbiter alone. RCS modes of pitch, yaw, and roll at free flight dynamic pressure simulation of 7, 20, and 50 psf were investigated. The effects of speedbrake, bodyflap, elevon, and airleron deflections were also investigated.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134103 , DMS-DR-2137-VOL-1-REV-A
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  • 105
    Publikationsdatum: 2019-06-27
    Beschreibung: Experimental aerodynamic investigations were conducted on a sting mounted 0.0405-scale representation of the -140A/B inner mold line (IML) space shuttle orbiter in 7.75 x 11 foot low speed wind tunnel, during the time period from 18 March 1974 to 20 March 1974. The primary test objectives were to establish basic longitudinal and lateral-directional stability and control characteristics for the IML orbiter. Additional configurations investigated were sealed elevon hingeline gaps, sealed rudder split line and hingeline gaps, larger radius leading edge on the vertical tail, and sealed speedbrake base. Aerodynamic force and moment data for the orbiter were measured in the body-axis system by an internally mounted, six-component strain gage balance. The model was sting mounted with the center of rotation located at approximately the wing trailing edge. The nominal angle of attack range was from -4 to +30 degrees. Yaw polars were recorded over a nominal yaw angle range from -14 to +14 degrees at constant angles of attack of 0, + or - 5, 10, 15 and 20 degrees.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134406 , DMS-DR-2155
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  • 106
    Publikationsdatum: 2019-06-27
    Beschreibung: A case study of data-communications network modeling and simulation is presented. The applicability of simulation techniques in early system design phases is demonstrated, and the ease with which model parameters can be changed and comprehensive statistics gathered is shown. The discussion of the model design and application also yields an insight into the design and implementation of the Apollo lunar surface experiments package ground-support system.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7783 , JSC-S-404
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  • 107
    Publikationsdatum: 2019-06-27
    Beschreibung: Apollo Program experience in the processing of scientific data from the Apollo lunar surface experiments package, in which computers and associated hardware and software were used, is summarized. The facility developed for the preprocessing of the lunar science data is described, as are several computer facilities and programs used by the Principal Investigators. The handling, processing, and analyzing of lunar science data and the interface with the Principal Investigators are discussed. Pertinent problems that arose in the development of the data processing schemes are discussed so that future programs may benefit from the solutions to the problems. The evolution of the data processing techniques for lunar science data related to recommendations for future programs of this type.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7781 , JSC-S-402
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  • 108
    Publikationsdatum: 2019-06-27
    Beschreibung: An experimental aerodynamic investigation was conducted to determine the interference effects of a wind tunnel support system. The test article was a 0.015 scale model of the space shuttle orbiter. The primary objective of the test was to determine the extent that aerodynamic simulation of the space shuttle orbiter is affected by base mounting the model, without nozzles, on a straight sting. Two support systems were tested. The characteristics of the support systems are described. Data from the tests are presented in the form of graphs and tables.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134403 , DMS-DR-2163
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  • 109
    Publikationsdatum: 2019-06-27
    Beschreibung: The repairability of boron/aluminum structural components was investigated. It was demonstrated that metal matrix composite material, damaged in service, can be repaired by techniques that are not very different from those currently in use for conventional materials. A list of repair guidelines was prepared to aid in determining the proper repair techniques for a given structure. The guidelines include specifying types of repair material and their applicability, corrosion prevention procedures, design criteria, and inspection criteria. Boron/aluminum structural components were repaired and tested to compare as-fabricated and repaired performance. All but one set of specimens, when repaired, exceeded the strength of the original specimens.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-120465 , GDCA-DBG73-006-VOL-4
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  • 110
    Publikationsdatum: 2019-06-27
    Beschreibung: Data obtained from a wind tunnel test of an 0.015-scale 140 A/B configuration space shuttle vehicle orbiter model (49-0) are presented. Runs were conducted at Mach numbers 0.6, 0.9, 1.2, 1.6, and 2.0 and Reynolds numbers of 8.4, 9.0, 9.0, 10.9, and 13.6 million per foot respectively. Various control surface settings were investigated from angles of attack of minus 4 degrees to plus 30 degrees at fixed angles of sideslip of zero and minus 5 degrees and through angles of sideslip from minus 2 to plus 8 degrees at fixed angles of attack of zero, plus 10, plus 15, and plus 20 degrees. The purpose of the test was to define the longitudinal and lateral-directional stability and control characteristics for the updated SSV configuration.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134405 , DMS-DR-2037
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  • 111
    Publikationsdatum: 2019-06-27
    Beschreibung: All general purpose equipment items contained in the final carry-on laboratory (COL) design concepts are described in terms of specific requirements identified for COL use, hardware status, and technical parameters such as weight, volume, power, range, and precision. Estimated costs for each item are given, along with projected development times.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-120453 , CASD-NAS-74-046-VOL-3
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  • 112
    Publikationsdatum: 2019-06-27
    Beschreibung: The results of the updated 30-day life sciences dedicated laboratory scheduling and costing activities are documented, and the 'low cost' methodology used to establish individual equipment item costs is explained in terms of its allowances for equipment that is commerical off-the-shelf, modified commercial, and laboratory prototype; a method which significantly lowers program costs. The costs generated include estimates for non-recurring development, recurring production, and recurring operations costs. A cost for a biomedical emphasis laboratory and a Delta cost to provide a bioscience and technology laboratory were also generated. All cost reported are commensurate with the design and schedule definitions available.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-120454 , CASD-NAS-74-046-VOL-4
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  • 113
    facet.materialart.
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The definition and integration tasks involved in the development of design concepts for a carry-on laboratory (COL), to be compatible with Spacelab operations, were divided into the following study areas: (1) identification of research and equipment requirements of the COL; (2) development of a number of conceptual layouts for COL based on the defined research of final conceptual designs; and (4) development of COL planning information for definition of COL/Spacelab interface data, cost data, and program cost schedules, including design drawings of a selected COL to permit fabrication of a functional breadboard.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-120451 , CASD-NAS-74-046-VOL-1
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  • 114
    Publikationsdatum: 2019-06-27
    Beschreibung: The task phase concerned with the requirements, design, and planning studies for the carry-on laboratory (COL) began with a definition of biomedical research areas and candidate research equipment, and then went on to develop conceptual layouts for COL which were each evaluated in order to arrive at a final conceptual design. Each step in this design/evaluation process concerned itself with man/systems integration research and hardware, and life support and protective systems research and equipment selection. COL integration studies were also conducted and include attention to electrical power and data management requirements, operational considerations, and shuttle/Spacelab interface specifications. A COL program schedule was compiled, and a cost analysis was finalized which takes into account work breakdown, annual funding, and cost reduction guidelines.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-120452 , CASD-NAS-74-046-VOL-2
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  • 115
    Publikationsdatum: 2019-06-27
    Beschreibung: The results of a wind tunnel test to determine the force, moment, and hinge-moment characteristics of the Configuration 2A Space Shuttle Vehicle Orbiter at Mach numbers 5, 7 and 10 are presented. The model was an 0.015-scale representation of the Orbiter Configuration 2A used in test 0A11A and later tests. Six-component aerodynamic force and moment data were recorded from a 1.50-inch internal strain-gage balance, and base pressures were taken for axial and drag force corrections. Hinge-moment data were obtained for the rudder and the inboard and outboard elevon panels of the starboard wing.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-128798 , DMS-DR-2059
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  • 116
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: An evaluation of the in-orbit performance of the instrumentation and communications systems installed on Skylab is presented. Performance is compared with functional requirements and the fidelity of communications. In-orbit performance includes processing engineering, scientific, experiment, and biomedical data, implementing ground-generated commands, audio and video communication, generating rendezvous ranging information, and radio frequency transmission and reception. A history of the system evolution based on the functional requirements and a physical description of the launch configuration is included. The report affirms that the instrumentation and communication system satisfied all imposed requirements.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64819
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  • 117
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N74-33319.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134115 , DMS-DR-2128-VOL-2
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  • 118
    Publikationsdatum: 2019-06-27
    Beschreibung: A wind tunnel test of an 0.030 scale model of the Rockwell International Configuration 140A/B Space Shuttle Vehicle Orbiter were conducted in the Ames Research Center 11- by 11-Foot Transonic Wind Tunnel. This part (part A) of test series 0A53 was conducted at Mach numbers of 0.6, 0.8, 0.9, 1.05, and 1.20, and at Reynolds numbers from 1.8 x to 6.5 million per foot. The objective of this test was to establish and verify longitudinal and lateral-directional aerodynamic performance, stability, and control characteristics for the Configuration 140A/B SSV Orbiter. Reynolds number studies were performed for certain nominal control-settings. An alternate leading-edge wing configuration and sealed elevon-split arrangement were tested. Bodyflap, elevon, speedbrake, and rudder hinge moments were measured in addition to standard six-component forces and moments and base pressure data. Furthermore, six-component force and moment data were measured for the vertical tail assembly.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134114 , DMS-DR-2128-VOL-1
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  • 119
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests were conducted to obtain hypersonic aerodynamic forces and moments on an 0.010-scale model of the space shuttle vehicle configuration 3. Hypersonic stability data were obtained from tests at Mach 10.3 and dynamic pressure of 150 psf for the integrated orbiter and external tank, orbiter alone, and external tank alone. The effects of solid plume simulation from the main propulsion system as well as elevon, aileron, and rudder deflections were also investigated.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134110 , DMS-DR-2133
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  • 120
    Publikationsdatum: 2019-06-27
    Beschreibung: The wind tunnel test of the 0.019 jet plume space shuttle integrated vehicle in the Ames 9 ft by 7 ft unitary wind tunnel was conducted at Mach numbers of 1.55 and 2.0 over a Reynolds number range from 3.5 million to 4.1 million/ft. Data were obtained at angles of attack from minus 8 deg to plus 8 deg at 0 deg sideslip and at angles of sideslip from minus 9 deg to plus 8 deg at 0 deg angle of attack. The basic configuration tested was the 2A vehicle with the orbiter at 0 deg angle of incidence with respect to the external tank. The other deviations to the 2A configuration were the solid rocket motor shrouds, which were designed to vehicle '3' lines, and the tank nose, which consisted of the retro-package being removed and replaced by a 16.5 inch full scale radius nose.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134104 , DMS-DR-2048
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  • 121
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: Apparatus for compression molding of thermosetting plastics compositions including interfitting hollow male and female components is reported. The components are adapted to be compressed to form a rocket nozzle in a cavity. A thermal jacket is provided exteriorly adjacent to the female component for circulating a thermal transfer fluid to effect curing of a thermosetting plastics material being molded. Each of the male and female components is provided with suitable inlets and outlets for circulating a thermal transfer fluid.
    Schlagwort(e): SPACE VEHICLES
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  • 122
    Publikationsdatum: 2019-06-27
    Beschreibung: Experimental aerodynamic investigations were conducted on a sting-mounted 0.0405 scale representation of the 140A/B space shuttle orbiter in a 7.75 ft by 11 ft low speed wind tunnel during the time period from November 14, 1973, to December 6, 1973, with the primary test objectives being to establish basic longitudinal stability characteristics in and out of ground effect, as well as lateral-directional stability characteristics in free air. Two dual podded nacelle configurations were also tested, one with three dual podded nacelles on the lower wing surface, and the other with a single dual nacelle on the lower centerline with dual nacelle pylons mounted above each wing. Stability and control characteristics were investigated at nominal elevon, rudder, aileron, and body flap deflections. Pressure bugs were used to determine pressures on the vertical tail at spanwise stations, and aerodynamic force and moment data were measured in the stability axis system by an internally mounted, six component strain gage balance.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134112 , DMS-DR-2104-VOL-1
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  • 123
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The activities of the ATS-6 spacecraft for the checkout period of approximately four weeks beginning May 30, 1974 are described, along with the results of a performance evaluation of its subsystems and components. The following specific items are discussed: (1) subsystem requirements/specifications and in-orbit performance summary; (2) flight chronology; (3) spacecraft description; (4) structural/deployment subsystems; (5) electrical power subsystem; (6) thermal control subsystem; (7) telemetry and command subsystems; (8) attitude control subsystem; (9) spacecraft propulsion subsystem; (10) communication subsystem; and (12) experiment subsystem.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-70740 , X-460-74-232
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  • 124
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: A technical history and managerial critique of the MSFC role in the Skylab program is presented. The George C. Marshall Space Flight Center had primary hardware development responsibility for the Saturn Workshop Modules and many of the designated experiments in addition to the system integration responsibility for the entire Skylab Orbital Cluster. The report also includes recommendations and conclusions applicable to hardware design, test program philosophy and performance, and program management techniques with potential application to future programs.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64808
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  • 125
    Publikationsdatum: 2019-06-27
    Beschreibung: A users guide to the Sampled Data Stability Analysis Program (SADSAP) is provided. This program is a general purpose sampled data Stability Analysis Program capable of providing frequency response on root locus data.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-140190 , REPT-5-2581-HOU-154-VOL-4
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  • 126
    Publikationsdatum: 2019-06-27
    Beschreibung: An optimum powered explicit guidance algorithm capable of handling all space shuttle exoatospheric maneuvers is presented. The theoretical and practical basis for the currently baselined space shuttle powered flight guidance equations and logic is documented. Detailed flow diagrams for implementing the steering computations for all shuttle phases, including powered return to launch site (RTLS) abort, are also presented. Derivation of the powered RTLS algorithm is provided, as well as detailed flow diagrams for implementing the option. The flow diagrams and equations are compatible with the current powered flight documentation.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-140191 , REPT-5-2581-HOU-154-VOL-5
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  • 127
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The characteristics of the solid rocket propellant for use with the space shuttle rocket engine are discussed. Design ramifications have created different web thicknesses and motor operating pressures which have necessitated small changes in the required propellant burning rate at 1,000 psia. However, the SRM burning rate remains well within the range demonstrated in the Poseidon and Minuteman first stage motors. Any change in propellant burning rate can be accomplished readily by a slight modification in the oxidizer particle size distribution. The ballistic and mechanical properties of the propellant remain unchanged from the baseline (Configuration 0).
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-120405 , TWR-10075-PT-2 , PUBL-74334-PT-2
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  • 128
    Publikationsdatum: 2019-06-27
    Beschreibung: The engineering equations and mathematical models developed for use in the space shuttle functional simulator (SSFS) are presented, and include extensive revisions and additions to earlier documentation. Definitions of coordinate systems used by the SSFS models and coordinate tranformations are given, along with documentation of the flexible body mathematical models. The models were incorporated in the SSFS and are in the checkout stage.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134399 , REPT-5-2581-HOU-154-VOL-2
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  • 129
    Publikationsdatum: 2019-06-27
    Beschreibung: A theoretical investigation of the influence of the aerodynamic torque on a Skylab-type satellite is presented. Only the case of free flow of uniform velocity and completely diffuse reflection is considered. It is found by linear stability analysis that the satellite has no stable equilibrium.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64865
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  • 130
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The performance of the LM-11 descent propulsion system during the Apollo 16 missions was evaluated and found satisfactory. The average engine effective specific impulse was 0.1 second higher than predicted, but well within the predicted one sigma uncertainty of 0.2 seconds. Several flight measurement discrepancies existed during the flight as follows: (1) the chamber pressure transducer had a noticeable drift, exhibiting a maximum error of about 1.5 psi at approximately 130 seconds after engine ignition, (2) the fuel and oxidizer interface pressure measurements appeared to be low during the entire flight, and (3) the fuel propellant quantity gaging system did not perform within expected accuracies.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134367 , MSC-07230-SUPPL-4 , TRW-20029-H156-RO-00
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  • 131
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: Literal criteria are developed for the controllability and observability of general models of flexible spacecraft. Results are interpreted in special cases and in physical terms, permitting in some cases the identification of uncontrollable and unobservable states simply by examination of scalars composed of modal parameters and location matrices for sensors and actuators. A procedure is established for isolation of uncontrollable states, whereby sensor and actuator configurations assure that uncontrollable flexible mode states are also unobservable; in many applications such states can then be removed by coordinate truncation.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-120320 , UCLA-ENG-7413
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  • 132
    Publikationsdatum: 2019-06-27
    Beschreibung: An account of activities and data gathered in the Room Temperature Stretch Forming of One-third Scale External Tank Bulkhead Gores for space shuttle study, and a tooling design and production cost study are reported. The following study phases are described: (1) the stretch forming of three approximately one-third scale external tank dome gores from single sheets of 2219-T37 aluminum alloy; (2) the designing of a full scale production die, including a determination of tooling requirements; and (3) the determination of cost per gore at the required production rates, including manufacturing, packaging, and shipping.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-120365 , CASD-NAS-74-029-VOL-1
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  • 133
    Publikationsdatum: 2019-06-27
    Beschreibung: All space shuttle events from launch through solid rocket booster recovery and orbiter landing are considered in terms of constraints placed on those operations by the natural environment. Thunderstorm activity is discussed as an example of a possible hazard. The activities most likely to require advanced detection and monitoring techniques are identified as those from deorbit decision to Orbiter landing. The inflexible flight plan will require the transmission of real time wind profile information below 24 km and warnings of thunderstorms or turbulence in the Orbiter flight path. Extensive aerial reconnaissance and communication facilities and procedures to permit immediate transmission of aircraft reports to the mission control authority and to the Orbiter will also be required.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64864
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  • 134
    Publikationsdatum: 2019-06-27
    Beschreibung: Compatibility data for aluminum alloy 2219-T87 and titanium alloy Ti-6Al-4V were obtained while these alloys were exposed to both liquid and vapor fluorine and FLOX at -320 F + or -10 F. These data were obtained using a new low cost compatibility method which incorporates totally sealed containers and double dogbone test specimens and propellants in the simultaneous exposure to vapor and liquid phases. The compatibility investigation covered a storage period in excess of one year. Pitting was more severe in the 2219-T87 aluminum alloy than in the Ti-6Al-4V titanium alloy for both fluorine and FLOX exposure. The degree of chemical attack is more severe in the presence of FLOX than in fluorine and phase. The mechanical properties of the two alloys were not affected by storage in either of the two propellants.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-139391 , TRW-23162-6020-RU-00
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  • 135
    Publikationsdatum: 2019-06-27
    Beschreibung: Wind tunnel tests were conducted to determine the stability and control characteristics of a monoplane missile with large delta wings and various tail configurations. The tests were conducted at angles of attack of approximately 24 degrees and angles of sideslip of about 22 degrees. Tail control configurations were the cruciform, conventional airplane type, and an inverted airplane configuration. Control effectiveness was measured for pitch, yaw, and roll.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-71984
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  • 136
    Publikationsdatum: 2019-06-27
    Beschreibung: Experimental aerodynamic investigations were conducted on a stingmounted 0.0405-scale representation (model 43-0) of the 140A/B Space Shuttle Orbiter in a Low Speed Wind Tunnel. The NASA designation for this test was 0A62A. The primary test objective was to continue studies, initiated on tests 0A16 and 0A71A and 0A71C, in optimizing the air breathing propulsion system (ABPS) and investigating the aerodynamic effects of various nacelle number/location configurations on the orbiter stability and control characteristics. Orbiter stability and control characteristics, both with and without ABPS, were investigated at elevon deflections of 0, + or -5, + or -19, + or -5, and -20 deg; aileron deflections of 0 and 10 deg (about 0 deg elevon); and rudder deflections of 0, -7.5, and -15 deg. Aerodynamic force and moment data was measured in the body axis system by a 2.5-inch task type internal balance. The model was sting supported through the base region with a nominal angle of attack range of -4 to 30 deg. Yaw polars were recorded over the beta range of -10 to 10 deg at fixed angles of attack of 0, 5, 10, and 15 deg.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134102 , DMS-DR-2097
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  • 137
    facet.materialart.
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: A qualitative assessment of the tendency for pogo instability of the shuttle vehicle in the absence of suppression devices, and the effectiveness of two passive suppressors (the compliant accumulator and the resistive accumulator) in counteracting any tendency toward instability is provided. In addition, the relative effectiveness of three suppressor locations (the low pressure pump (LWOP) inlet and discharge and the high pressure pump (HPOP) inlet) is also evaluated. The primary conclusion of the study is that effective pogo suppression, with passive devices, can be accomplished at the HPOP inlet location but not at the LPOP locations. Other conclusions are drawn regarding the relative effectiveness of the two accumulator types and with respect to tentative accumulator design requirements. Finally, a number of recommendations are made regarding future studies.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-132452 , ATR-74(7416)-1
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  • 138
    Publikationsdatum: 2019-06-27
    Beschreibung: The apparatus comprises a high speed gate valve for isolating the interior of the furnance from an air lock chamber on the opposite side of the gate valve. The air lock chamber is provided with valve ports connected to a vacuum source, a source of inert quenching gas, and the atmosphere, respectively. Attached to the end of the air lock chamber away from the furnace is a cylindrical tube having disposed within it a rod carrying specimen pan at the end towards the furnace and having mounted at its top end an annular magnet having a diameter slightly less than the interior diameter of the tube. The top end of the tube is closed by a removeable cap. Encircling the tube in the vicinity of the magnet is a carbon steel ring which when axially moved along the tube causes the magnet to follow it and thereby controls the position of the rod and specimen pan within the tube.
    Schlagwort(e): SPACE VEHICLES
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  • 139
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The design and development of the equipment necessary to simulate the S-band multiple access link between user spacecraft, the Tracking and Data Relay Satellite, and a ground control terminal are discussed. The core of the S-band multiple access concept is the use of an Adaptive Ground Implemented Phased Array. The array contains thirty channels and provides the multiplexing and demultiplexing equipment required to demonstrate the ground implemented beam forming feature. The system provided will make it possible to demonstrate the performance of a desired user and ten interfering sources attempting to pass data through the multiple access system.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-139032
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  • 140
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The design and operation of the power subsystem for the Atmospheric Explorer spacecraft are discussed. The additional functional redundancy which was added in several component areas to improve the overall subsystem reliability is analyzed. The battery charging technique has been modified to include third electrode overcharge control. The automatic removal of all battery charge is provided to correct abnormally high battery voltages. An undervoltage detector has been added which removes all nonessential spacecraft loads when the battery voltage falls below a given level. All automatic functions can be over-ridden by ground command.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-70693 , X-711-74-193
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  • 141
    Publikationsdatum: 2019-06-27
    Beschreibung: Longitudinal and lateral-directional stability characteristics of the 139-B orbiter (model 32-0) were obtained in a continuous flow hypersonic tunnel at Mach 10.3. Tests were made at Reynolds numbers of 1.04 million and 2.17 million (based on body length) over an angle of attack range of 12 deg to 36 deg at sideslip angles of 0 deg and minus 5 deg. Data were obtained at three elevon/body flap settings.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-71954 , DMS-DR-2127
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  • 142
    Publikationsdatum: 2019-06-27
    Beschreibung: Development, delivery, and use of food systems in support of the Apollo 7 to 14 missions are discussed. Changes in design criteria for this unique program as mission requirements varied are traced from the baseline system that was established before the completion of the Gemini Program. Problems and progress in subsystem management, material selection, food packaging, development of new food items, menu design, and food-consumption methods under zero-gravity conditions are described. The effectiveness of various approaches in meeting food system objectives of providing flight crews with safe, nutritious, easy to prepare, and highly acceptable foods is considered. Nutritional quality and adequacy in maintaining crew health are discussed in relation to the establishment of nutritional criteria for future missions. Technological advances that have resulted from the design of separate food systems for the command module, the lunar module, The Mobile Quarantine Facility, and the Lunar Receiving Laboratory are presented for application to future manned spacecraft and to unique populations in earthbound situations.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7720
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  • 143
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: Design criteria statement applicable to a wide variety of flight systems, experiments and other payloads, associated ground support equipment and facility support systems are presented. The document reflects a composite of experience gained throughout the aerospace industry prior to Skylab and additional experience gained during the Skylab Program. It has been prepared to provide current and future program organizations with a broad source of safety-related design criteria and to suggest methods for systematic and progressive application of the criteria beginning with preliminary development of design requirements and specifications. Recognizing the users obligation to shape the checklist to his particular needs, a summary of the historical background, rationale, objectives, development and implementation approach, and benefits based on Skylab experience has been included.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64850
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  • 144
    Publikationsdatum: 2019-06-27
    Beschreibung: The main aspects of the attitude control system used on both the IMP-H and J spacecraft are presented. The mechanical configuration is described. Information on all the specific components comprising the flight system is provided. The acceptance and qualification testing of both individual components and the installed system are summarized. Functional information regarding the operation and performance in relation to the orbiting spacecraft and its mission is included. Related topics which are discussed are: (1) safety requirements, (2) servicing procedures, (3) anomalous behavior, and (4) pyrotechnic devices.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-70691 , X-731-74-173
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  • 145
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests were conducted to investigate various base drag reduction techniques in an attempt to improve Orbiter lift-to-drag ratios and to calculate sting interference effects on the Orbiter aerodynamic characteristics. Test conditions and facilites, and model dimensional data are presented along with the data reduction guidelines and data set/run number collation used for the studies. Aerodynamic force and moment data and the results of stability and control tests are also given.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134098 , DMS-DR-2114
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  • 146
    Publikationsdatum: 2019-06-27
    Beschreibung: The primary objective of the test was to obtain stability and control data for the basic configuration and an alternate configuration for the Space Shuttle Orbiter. Pitch runs were made with 0 deg of sideslip at Mach numbers of 5.3, 7.3 and 10.3. Six-component force data and fuselage base pressures were recorded for each run. Shadowgraph pictures were taken at selected points. Model 420 was used for the tests.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134091 , DMS-DR-2060
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  • 147
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N74-27386.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134100 , DMS-DR-2077-VOL-3
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  • 148
    Publikationsdatum: 2019-06-27
    Beschreibung: Supersonic aerodynamic tests were conducted in the NASA/LaRC Unitary Plan Wind Tunnel on a 0.015-scale model of the Space Shuttle Vehicle 4 configuration. Surface pressure data were obtained for both the launch (test IA35) and entry (test OA64) configurations at Mach numbers from 2.5 to 4.5. The surface pressure was measured in the vicinity of the cargo bay door hinge and parting lines and on the side of the fuselage at the crew compartment and below the OMS pods at the aft compartment. Data were obtained for angles of attack and sideslip consistent with the expected excursions about the nominal trajectory values at the test Mach numbers. These tests were a part of a test series supporting the orbiter venting analysis over a Mach number range from 0.6 to 10.4
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134084 , DMS-DR-2108
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  • 149
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N74-27386.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134099 , DMS-DR-2077-VOL-2
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  • 150
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests were conducted in the NASA/ARC 6- by 6-foot transonic wind tunnel from September 12 to September 28, 1973 on an 0.015-scale model of the space shuttle configuration 140 A/B. Surface pressure data were obtained for the orbiter for both launch and entry configuration at Mach numbers from 0.6 to 2.0. The surface pressures were obtained in the vicinity of the cargo bay door hinge and parting lines, the side of the fuselage at the crew compartment and below the OMS pods at the aft compartment. Data were obtained at angles of attack and sideslip consistent with the expected divergencies along the nominal trajectory. These tests were first in a series of tests supporting the orbiter venting analysis. The series will include tests in three facilities covering a total Mach number range from 0.6 to 10.4.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134095 , DMS-DR-2077-VOL-1
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  • 151
    Publikationsdatum: 2019-06-27
    Beschreibung: Data obtained from the wind tunnel tests of a scale model of the space shuttle orbiter configuration 140 A/B are presented. The test was conducted at Mach numbers of 2.5, 3.9, and 4.6 with Reynolds numbers from 1.25 million per foot to 5.0 million per foot. Various control surface settings were used ranging from an angle of attack range from minus 4 to plus 42 degrees at zero angle of yaw. Longitudinal stability and control characteristics of the space shuttle configuration were analyzed.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134097 , DMS-DR-2147
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  • 152
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: A survey was conducted to determine the possible missions which could be accomplished by the space shuttle. The areas of scientific endeavor which were considered are as follows: (1) atmospheric and space physics, (2) high energy astrophysics, (3) infrared astronomy, (4) optical and ultraviolet astronomy, (5) solar physics, (6) life sciences, and (7) planetary exploration. Specific projects to be conducted in these broader areas are defined. The modes of operation of the space shuttle are analyzed. Instruments and equipment required for conducting the experiments are identified.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-138905
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  • 153
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The Applications Explorer Missions (AEM) Program is a planned series of space applications missions whose purpose is to perform various tasks that require a low cost, quick reaction, small spacecraft in a dedicated orbit. The Heat Capacity Mapping Mission (HCMM) is the first mission of this series. The spacecraft described in this document was conceived to support a variety of applications instruments and the HCMM instrument in particular. The maximum use of commonality has been achieved. That is, all of the subsystems employed are taken directly or modified from other programs such as IUE, IMP, RAE, and Nimbus. The result is a small versatile spacecraft. The purpose of this document, the AEM Mission Planners Handbook (AEM/MPH) is to describe the spacecraft and its capabilities in general and the HCMM in particular. This document will also serve as a guide for potential users as to the capabilities of the AEM spacecraft and its achievable orbits. It should enable each potential user to determine the suitability of the AEM concept to his mission.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-69906
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  • 154
    Publikationsdatum: 2019-06-27
    Beschreibung: The standardized functional support section for the improved Small Astronomy Satellite (SAS) spacecraft, which can be used virtually without change for a wide variety of experimental packages and missions, is described. This functional support section makes the spacecraft remarkably flexible for a small satellite. Able to point its thrust axis to any direction in space, it can also spin or slow its outer body rotation to zero for star- or earth-locked pointing of side-viewing experiments. It features a reprogrammable telemetry system, a delayed command system, and an improved control system. Experiments can be built independently and attached to the SAS spacecraft just prior to final acceptance testing and launch. The spacecraft subsystems are described in detail. Included are a summary of the spacecraft characteristics, special design considerations, project reliability requirements, and environmental test conditions. It is intended that this new functional support section afford virtual off-the-shelf availability of the SAS spacecraft to independently built experiments, thus providing quick response time and minimum cost in meeting a wide variety of experimenter needs.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7725 , G-7454
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  • 155
    Publikationsdatum: 2019-06-27
    Beschreibung: Experimental aerodynamic investigations were conducted on a 0.015 scale model of the Space Shuttle Orbiter in a low turbulence pressure tunnel. Six component static aerodynamic force and moment data were recorded while the model was pitched from -2 deg to +26 deg angle of attack. The yaw angles during these pitch sweeps were 0 deg, -5 deg, and 7 1/2 deg. Base, sting cavity, vertical tail, wing trailing edge, and elevon pressures, as well as elevon and rudder hinge moment data were also obtained. The tests were conducted at a nominal Mach number of 0.25. The Reynolds number was varied throughout the test program from 2.5 million to 4.7 million to 10.0 million to 12.5 million.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134079 , DMS-DR-2058
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  • 156
    Publikationsdatum: 2019-06-27
    Beschreibung: Experimental aerodynamic investigations were conducted on a 0.015 scale representation (Model 42-0) of the VL70-000139B space shuttle orbiter configuration. The test objective was to determine the effect of three air breathing propulsion system ferry/flight test configurations on the transonic drag rise, the elevon effectiveness, the longitudinal stability, and the lateral-directional stability of the -139B shuttle orbiter. The model was sting mounted on a Task 1.5 inch internal strain gage balance, and six-component aerodynamic force and moment data were recorded over an angle of attack range of minus 3 deg to 14 deg at Mach numbers of 0.5, 0.6, 0.7, 0.8, and 0.9 with a Reynolds number of 6.4 million/ft. Data were also recorded at a sides lip angle of five degrees.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134088 , DMS-DR-2116
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  • 157
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: System design and performance of the Skylab Airlock Module and Payload Shroud are presented for the communication and caution and warning systems. Crew station and storage, crew trainers, experiments, ground support equipment, and system support activities are also reviewed. Other areas documented include the reliability and safety programs, test philosophy, engineering project management, and mission operations support.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64810-VOL-2
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  • 158
    Publikationsdatum: 2019-06-27
    Beschreibung: The original motivation for studying control laws for pulse plasma systems was based on the improved life characteristics possible with pulse plasma jets. These pulse plasma units are relatively massive compared with cold gas thrustors. As a result, therefore, significant mass savings can be achieved by minimizing the the number of thrustors. The control laws, therefore, were developed for thrust available from two thrustors only. In a spinning satellite, these thrustors are sufficient to completely control the vehicle as long as the spin rate is sufficiently high for a given level of external disturbance. The thrustors are canted so that a component of each is along the plus and minus spin axis. The other component of each thrustor acts in the radial direction. It is sufficient to analyze the behavior in the plane of spin assuming a single thrustor.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-139018
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  • 159
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: Cluster external contamination control evaluation was made throughout the Skylab Mission. This evaluation indicated that contamination control measures instigated during the design, development, and operational phases of this program were adequate to reduce the general contamination environment external to the Cluster below the threshold senstivity levels for experiments and affected subsystems. Launch and orbit contamination control features included eliminating certain vents, rerouting vents for minimum contamination impact, establishing filters, incorporating materials with minimum outgassing characteristics and developing operational constraints and mission rules to minimize contamination effects. Prior to the launch of Skylab, contamination control math models were developed which were used to predict Cluster surface deposition and background brightness levels throughout the mission. The report summarizes the Skylab system and experiment contamination control evaluation. The Cluster systems and experiments evaluated include Induced Atmosphere, Corollary and ATM Experiments, Thermal Control Surfaces, Solar Array Systems, Windows and Star Tracker.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64826
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  • 160
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The Spacelab data management system is described. The data management subsystem (DMS) integrates the avionics equipment into an operational system by providing the computations, logic, signal flow, and interfaces needed to effectively command, control, monitor, and check out the experiment and subsystem hardware. Also, the DMS collects/retrieves experiment data and other information by recording and by command of the data relay link to ground. The major elements of the DMS are the computer subsystem, data acquisition and distribution subsystem, controls and display subsystem, onboard checkout subsystem, and software. The results of the DMS portion of the Spacelab Phase B Concept Definition Study are analyzed.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64848
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  • 161
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: Launch operations of the ATS 6 satellite and the Titan 3 C launch vehicle are analyzed. The subjects discussed are: (1) launch vehicle trajectory, (2) launch vehicle mark events, (3) standard orbital parameter messages, (4) STADAN ground station visibility, (5) launch window, (6) separation attitude, and (7) separation events. The VHF Omni earth coverage antenna is described. Graphs of visibility from various ground stations are developed.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-70653 , X-460-74-104
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  • 162
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N74-26328.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64812-VOL-2
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  • 163
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The history is presented of the development of the Skylab Multiple Docking Adapter from initial concept through its final design, related test programs, mission performance, and lessons learned.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64812-VOL-1
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  • 164
    Publikationsdatum: 2019-06-27
    Beschreibung: The effect of plume-induced flow separation and aspiration effects due to operation of both orbiter and the solid rocket motors on a 0.019-scale model of the launch configuration of the Space Shuttle Vehicle is determined. Longitudinal and lateral-directional stability data were obtained at Mach numbers of 1.6, 2.0, and 2.2 with and without the engines operating. The plumes exiting from the engines were simulated by a cold-gas jet supplied by an auxiliary 200-atm air supply system and solid-body plume simulators. The aerodynamic effects produced by these two simulation procedures are compared. The parameters most significantly affected by the jet plumes are pitching moment, elevon control effectiveness, axial force, and orbiter wing loads. The solid rocket motor (SRM) plumes have the largest effect on the aerodynamic characteristics. The effect of the orbiter plumes in combination with the SRM plumes is also significant. Variations in the nozzle design parameters and configuration changes can reduce the jet plume-induced aerodynamic effects.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-3032 , A-5212
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  • 165
    Publikationsdatum: 2019-06-27
    Beschreibung: An investigation has been made of abort procedures for space shuttle-type vehicles using a point mass trajectory optimization program known as POST. This study determined the minimum time gap between immediate and once-around safe return to the launch site from a baseline due-East launch trajectory for an alternate space shuttle concept which experiences an instantaneous loss of 25 percent of the total main engine thrust.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-71952
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  • 166
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests were conducted, during April and May 1973, on an 0.030-scale replica of the Space Shuttle Vehicle Configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The investigation included tests on the integrated (launch) configuration, and on the isolated orbiter (entry configuration). The integrated vehicle was tested at angles of attack and sideslip from -8 degrees to +8 degrees. The isolated orbiter was tested at angles of attack from -15 degrees to +40 degrees and angles of sideslip from -10 degrees to +10 degrees as dictated by trajectory considerations. The effect of orbiter/external tank incidence angle and deflected control surfaces on aerodynamic loads were also investigated.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-128794 , DMS-DR-2032-VOL-18
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  • 167
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests were conducted, from November 15 to December 4, 1973, to obtain surface pressure data on an 0.015-scale replica of the Space Shuttle Vehicle 4. Data were obtained at Mach numbers of 5.3, 7.4, and 10.3, to support the venting analysis for both launch and entry conditions. These tests were the final tests in a series covering a Mach number range from 0.6 to 10.3. The model was instrumented with pressure orifices in the vicinity of the cargo bay door hinge and parting lines, and on the side of the fuselage at the crew compartment, and below the orbital maneuvering system pods at the aft compartment. The model was tested at angles of attack and sideslip consistent with expected divergencies from the nominal trajectory.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134093 , DMS-DR-2124
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  • 168
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: A catalog is presented of subsystem and environment math models used or planned for space shuttle simulations. The purpose is to facilitate sharing of similar math models between shuttle simulations. It provides information on mach model requirements, formulations, schedules, and contact persons for further information.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-70085 , JSC-08965-REV-1
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  • 169
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    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The history and development of the Skylab Airlock Module and Payload Shroud is presented from initial concept through final design. A summary is given of the Airlock features and systems. System design and performance are presented for the Spent Stage Experiment Support Module, structure and mechanical systems, mass properties, thermal and environmental control systems, EVA/IVA suite system, electrical power system, sequential system, sequential system, and instrumentation system.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64810-VOL-1
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  • 170
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: Orbital operations concepts for the shuttle launched Large Automated Satellites (LAS) are discussed. It includes the orbital operations elements and the major options for accomplishing each element. This study is based on the preliminary payload information available in Level I and II documents and on orbital operations methods used on past programs, both manned and unmanned. It includes a definition of detailed trade studies which need to be performed as satellite design details and organization responsibilities are defined. The major objectives of this study were to define operational methods and requirements for the long duration LAS missions which are effective and primarily economical to implement.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64847
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  • 171
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The Apollo Telescope Mount (ATM) Calibration Rocket (CALROC) performances and anomalies encountered are discussed. The performance period included six CALROC flights during the Skylab 2, 3 and 4 missions as well as those rocket flights prior to the Skylab mission which carried CALROC hardware for test purposes. Background material such as project purpose, management, launch facilities, booster and payload configuration is included for better understanding of the CALROC payload and its mission objectives.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64846
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  • 172
    Publikationsdatum: 2019-06-27
    Beschreibung: A state-of-the-art preliminary design for typical wing areas is developed. Seven medium-density ablators (with/without honeycomb, flown on Apollo, Prime, X15A2) are evaluated. The screening tests include: (1) leading-edge models sequentially subjected to ascent heating, cold soak, entry heating, post-entry pressure fluctuations, and touchdown shock, and (2) virgin/charred models subjected to bondline strains. Two honeycomb reinforced 30 pcf elastomeric ablators were selected. Roughness/recession degradation of low speed aerodynamics appears acceptable. The design, including attachments, substructure and joints, is presented.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-132379
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  • 173
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The problem areas encountered during the development of the acceptance testing and preflight checkout requirements and procedures for Apollo spacecraft are discussed. Recommendations are given for cases in which methods used in the Apollo program are considered to apply to future space flight programs.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7683 , JSC-S-392
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  • 174
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: Apollo program experience in recovery-support communications is reviewed, and the working relationships among NASA, the Department of Defense, and commercial communications facilities are discussed. The organization, facilities, philosophy, and funding of recovery-support communications are described. The relocation of two recovery control centers is discussed, as are the functions of primary and secondary recovery ships, aircraft, and relay satellities. The possibility of using ships of opportunity for recovery operations is considered. Finally, the means by which money, manpower, and resources have been saved and longlines leased are delineated.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7686 , JSC-S-398
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  • 175
    Publikationsdatum: 2019-06-27
    Beschreibung: The Apollo management of data for postflight engineering evaluation is described. The sources of Apollo telemetry data, the control of data processing by a single data team, the data techniques used to assist in evaluation of the large quantity of data, and the operation of the data team before the mission and during the evaluation phase are described. The techniques used to ensure the output of valid data and to determine areas in which data were of questionable quality are also included.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7684 , JSC-S-393
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  • 176
    Publikationsdatum: 2019-06-27
    Beschreibung: Performance, stability, and control tests at supersonic and hypersonic speeds have been performed on two versions of a shuttle orbiter configuration designed for reduced length. One of the test configurations had twin dorsal fins rolled out 15 deg the other a centerline single dorsal fin. Effects of elevon and body deg flap deflection, rudder flare, planform fillet, and aileron deflection were examined. The supersonic tests were over the Mach number range from 1.6 to 4.63 at a Reynolds number based on model length of 4,300,000. The hypersonic tests were conducted at a Mach number of 10.3 and Reynolds number of 670,000.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-71956
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  • 177
    Publikationsdatum: 2019-06-27
    Beschreibung: The development of flight-control facilities for the Apollo program is reviewed from the viewpoint of the user organization. These facilities are treated in three categories: data systems, ground-based display and control systems, and configuration management. The effects of certain Apollo program factors on the selection, sizing, and configuration management of these systems are discussed. Recommendations are made regarding improvement of the systems and the reduction of system sensitivity to the program factors.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7685 , JSC-S-396
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  • 178
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N74-23389.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-128794-VOL-17 , DMS-DR-2032-VOL-17
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  • 179
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests were conducted in the NASA/ARC Unitary Plan Wind Tunnels on an 0.030 scale replica of the space shuttle vehicle Configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The integrated vehicle was tested at angles of attack and sideslip from -8 degrees to +8 degrees. The isolated orbiter was tested at angles of attack from -15 degrees to +40 degrees and angles of sideslip from -10 degrees to +10 degrees as dictated by trajectory considerations. The effects of orbiter/external tank incidence angle and deflected control surfaces on aerodynamic loads were also investigated.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-128794-VOL-16 , DMS-DR-2032-VOL-16
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  • 180
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: Data from the particle detectors on ATS-5 in synchronous orbit and from the meridian line of magnetometers at a ground station are correlated for periods of well defined substorm activity. Specific substorm events are presented whose region of maximum perturbation can be accurately identified using current systems modelling techniques. It was found that the impulsive particle response at ATS-5 is correlated with changes in the auroral electrojet structure during the development of the substorm expansive phase. The response of the particle detectors appears to differ from event to event depending on the geometry of the disturbed region of the magnetosphere. It is concluded that the substorm disturbance typically begins at low latitude and propagates poleward in impulsive steps and that energetic electron enhancements are observed at ATS-5 when the poleward border of the electrojet intensifies in the latitude range of the ATS-5 field line.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-138243 , LMSC-D358586
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  • 181
    Publikationsdatum: 2019-06-27
    Beschreibung: The transmission loss of Pioneer Venus Probe radiation windows if their exposed surfaces become contaminated with droplets of water, hydrochloric acid, sulfuric acid, and mercury which may be found in the Venusian atmosphere was investigated. Transmission loss was studied as a function of mass concentration of liquid droplets deposited on one surface of test window materials while the wavelength of the transmitting radiation is in the range of 0.3 to 30 microns. The parameters that affect the transmittance of radiation through a window are: (1) particle size, (2) surface concentration of particles, (3) wavelength of the radiation, (4) angle of acceptance of the radiation by the detector, and (5) the refractive index of the aerosol.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-138254
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  • 182
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: Summary listings of published documentation of SADSAC processed data arranged chronologically and by shuttle configuration are presented to provide an up-to-date record of all applicable aerothermodynamic data collected, processed, or summarized in the course of the space shuttle program. The various tables or listings are designed to provide survey information to the various space shuttle managerial and technical levels. The various listings of the shuttle test data information, the list contents, and the purpose are described.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134225 , DMS-DFR-2012
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  • 183
    Publikationsdatum: 2019-06-27
    Beschreibung: Experimental aerodynamic investigations were conducted on a scale model of the space shuttle orbiter, Configuration 140A/B. The objectives of this test were to: 1) verify supersonic stability and control characteristics, 2) analyze aerodynamic problem areas, 3) verify control surface effectiveness, and 4) investigate Reynolds number effects. Six-component aerodynamic force and moment data were recorded over an angle of attack range from 22 deg to 46 deg at a constant sideslip angle of 0 deg. The test Mach number was varied from 5.3 to 7.3 to 10.3. The Reynolds number per unit length was varied from 805,000 to 10 million per foot.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134085 , DMS-DR-2115
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  • 184
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests of several tank nose shapes were conducted as a part of the investigation of configuration changes to reduce drag for the integrated vehicle. The effect on the integrated vehicle aerodynamic characteristics of several tank nose shapes was investigated. The tank nose shapes investigated were the 600 inch (baseline) and 1204 inch radius ogives, and the 600 inch ogive plus a spike 360 inches long and 12.0 inches in diameter. Data were obtained over a Mach number range of 0.6 through 4.96 and for angles-of-attack and sideslip from -10 through +10 degrees. The model used was the 0.004-scale integrated vehicle model number 34-OTS.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134090 , DMS-DR-2093
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  • 185
    Publikationsdatum: 2019-06-27
    Beschreibung: An Integrated Power and Attitude Control System (IPACS) concept with potential application to a broad class of space missions is discussed. A description is given of the basic concept of combining the onboard energy storage and attitude control functions by storing energy in spinning flywheels which are used to provide control torques. A shuttle-launched Research and Applications Module (RAM) A303B solar-observatory mission having stringent pointing requirements (1.0 arc second) is selected to investigate possible interactions between energy storage and attitude control. A simulation of this spacecraft involving actual laboratory-model control-system hardware is presented. Simulation results are discussed which indicate that the IPACS concept, even in a failure-mode configuration, can readily meet the RAM A303B pointing requirements.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7459 , L-8791
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  • 186
    Publikationsdatum: 2019-06-27
    Beschreibung: A series of simple wing/elevon flutter models of the shuttle orbiter were tested in a 26-inch transonic blowdown tunnel. Flutter points were obtained for two levels of scaled elevon actuator stiffness. A description of the wind tunnel models and the test procedures utilized in the experiment are given.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134073 , DMS-DR-2094
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  • 187
    Publikationsdatum: 2019-06-27
    Beschreibung: Results from tests in the NASA/MSFC Trisonic Wind Tunnel on 0.004-Scale Orbiter and External Tank Force Models in Close Proximity (RTLS Abort Separation Conditions) are presented. The primary test objectives were to obtain data concerning proximity effects on the aerodynamic forces and moments experienced by Vehicle 2A Configuration Shuttle Orbiter and External Tank during an abort separation (Return to Launch Site) at a Mach number of 5. Additionally, data on orbiter control effectiveness during such an abort was obtained. Proximity effects were investigated for relative angles of incidence from minus 5 deg to plus 10 deg of the orbiter FRL with respect to the external tank centerline over a range of vertical and longitudinal displacements from the mated position to 2.5 tank diameters below and 3 tank diameters aft of the mated position.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134071 , DMS-DR-2039
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  • 188
    Publikationsdatum: 2019-06-27
    Beschreibung: Details are presented of flow visualization techniques developed during wind tunnel test IA-52 conducted in a 14 x 14 inch trisonic wind tunnel. Testing was conducted from Mach = 0.9 to 5.0 on the orbiter alone and integrated vehicle configurations. Thin film oil paint and ultraviolet light sensitive oil applications were used on a .004 scale model vehicle. Test results presented are in the form of black and white photographs taken after the completion of a test run.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134087 , DMS-DR-2042
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  • 189
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: The second in a planned series of heated jettison tests on the Centaur Standard Shroud was conducted on January 16, 1974. The first 250-second portion of the test sequence involved heating the shroud with a specially-built fixture designed to provide a simulation of the heating environment encountered by the shroud during its ascent through the earth's atmosphere. The two heater halves, which were mounted on a rail system, were then retracted. This was followed by the jettison of the two shroud halves into catch nets positioned at 90 deg to the heater rails. The condition which made this test unique compared to the others in the test series was the alignment of the maximum thermal line with the shroud separation plane. Information on the test hardware, configuration, and sequence is presented. Shroud thermal and deflection data encountered during the heating portion of the test sequence are compared with free-skin design temperatures in various graphical formats.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-71521 , E-7902
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  • 190
    Publikationsdatum: 2019-06-27
    Beschreibung: An experimental investigation was performed in the Langley Research Center Unitary Plan Wind Tunnel (Test 0A70) to obtain the detailed effects that RCS jet flow interactions with local orbiter flow field have on supersonic stability and control characteristics of the space shuttle orbiter. Six-component force data were obtained through an angle-of-attack range from 15 to 35 degrees at angles of sideslip of 0, +5, and -5 degrees. The test was conducted with yaw jet simulation at free-stream Mach numbers of 2.5 and 4.6, simulating SSV re-entry flight conditions at these Mach numbers. In addition to the basic force measurements, fuselage base pressures and pressures on the non-metric RCS pods were obtained.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134070 , DMS-DR-2073
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  • 191
    Publikationsdatum: 2019-06-27
    Beschreibung: Manned thermal-vacuum tests of the Apollo spacecraft presented many first-time problems in the areas of test philosophy, operational concepts, and program implementation. The rationale used to resolve these problems is explained and examined critically in view of actual experience. The series of 12 tests involving 1517 hours of chamber operating time resulted in the disclosure of numerous equipment and procedural deficiencies of significance to the flight mission. Test experience and results in view of subsequent flight experience confirmed that thermal-vacuum testing of integrated manned spacecraft provides a feasible, cost-effective, and safe technique with which to obtain maximum confidence in spacecraft flight worthiness early in the program.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TN-D-7610 , JSC-S-388
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  • 192
    Publikationsdatum: 2019-06-27
    Beschreibung: Phase B effort of the Sortie Lab program has concluded. Results of that effort are presented which pertain to the definitions of the environmental control system (ECS). Numerous design studies were performed in Phase B to investigate system feasibility, complexity, weight, and cost. The results and methods employed for these design studies are included. An autonomous Sortie Lab ECS was developed which utilizes a deployed space radiator. Total system weight was projected to be 1814.4 kg including the radiator and fluids. ECS power requirements were estimated at 950 watts.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64832
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  • 193
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    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: An assessment of two proposed Spacelab configurations with diameters of 14 and 12 feet was conducted by using two inexpensive wooden mockups containing cardboard fixtures. Also examined was an alternate mounting arrangement for the 12-foot diameter configuration, taking advantage of conforming equipment racks to the cylinder walls. A volume comparison of the three configurations was made using a life sciences payload which is considered to be one of the more voluminous payloads. It was found that crew volume in the 12-foot baseline configuration appeared marginal for the life sciences payload, especially where crewmen were engaged in activities with competing demands. The 12-foot configurations of life sciences payloads offered little margin for stowage or equipment growth. Increased demands would necessitate longer module lengths. Similar results could be expected with other large volume payloads.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-64828
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  • 194
    Publikationsdatum: 2019-06-27
    Beschreibung: The Tracking and Data System supported the deep space phases of the Pioneer 6, 7, 8, and 9 missions, with two spacecraft in an inward trajectory and two spacecraft in an outward trajectory from the earth in heliocentric orbits. During the period of this report, scientific instruments aboard each of the spacecraft continued to register information relative to interplanetary particles and fields, and radiometric data generated by the network continued to contribute to knowledge of the celestial mechanics of the solar system. In addition, to network support activity detail, network performance and special support activities are covered.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-137982 , JPL-TM-33-426-VOL-12
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  • 195
    Publikationsdatum: 2019-06-27
    Beschreibung: A preliminary study was made of a radar imaging satellite for earth applications. A side-looking synthetic-aperture radar was considered and the feasibility of obtaining a wide area coverage to reduce the time required to image a given area was investigated. Two basic approaches were examined; low altitude sun-synchronous orbits using a multibeam/multifrequency radar system and equatorial orbits up to near-synchronous altitude using a single beam system. Surveillance and mapping of ice on the Great Lakes was used as a typical application to focus the study effort.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-71515 , E-7903
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  • 196
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N74-20534. For complete abstract, see .
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-120173 , MCR-74-2
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  • 197
    Publikationsdatum: 2019-06-27
    Beschreibung: The design effort to develop, design, and fabricate a prototype Universal Stowage Module with universal restraints that are readily adaptable for most sizes and shapes of items that would be launched into space and returned aboard shuttle payloads is presented.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-138006 , MCR-74-1
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  • 198
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N74-20529. For complete abstract, see .
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-128794-VOL-15 , DMS-DR-2032-VOL-15
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  • 199
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests were conducted in wind tunnels during April and May 1973, on a 0.030-scale replica of the Space Shuttle Vehicle Configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The investigation included tests on the integrated (launch) configuration and the isolated orbiter (entry configuration). The integrated vehicle was tested at angles of attack and sideslip from -8 degrees to +8 degrees. The isolated orbiter was tested at angles of attack from -15 degrees to +40 degrees and angles of sideslip from -10 degrees to +10 degrees as dictated by trajectory considerations. The effects of orbiter/external tank incidence angle and deflected control surfaces on aerodynamic loads were also investigated. Tabulated pressure data were obtained for upper and lower wing surfaces and left and right vertical tail surfaces.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-128794-VOL-14 , DMS-DR-2032-VOL-14
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  • 200
    Publikationsdatum: 2019-06-27
    Beschreibung: An investigation was made in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.9 and 2.86 to study the supersonic aerodynamic characteristics of a Rockwell International shuttle orbiter configuration. Tests were made at a Reynolds number of 1.5 million per foot with an angle-of-attack range of minus 4 to 28 deg and sideslip variations of minus 6 to 8 deg. The effects of elevon and aileron deflections were investigated.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-CR-134080 , DMS-DR-2090
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