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  • Other Sources  (216)
  • Analytical Chemistry and Spectroscopy
  • Biochemistry and Biotechnology
  • Cell & Developmental Biology
  • Chemical Engineering
  • Earth model, also for more shallow analyses !
  • Engineering
  • General Chemistry
  • Life and Medical Sciences
  • SPACE TRANSPORTATION
  • 2010-2014
  • 1990-1994  (47)
  • 1980-1984  (167)
  • 1970-1974
  • 1930-1934  (2)
  • 1994  (47)
  • 1982  (167)
  • 1933  (2)
  • 1927
Collection
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  • 2010-2014
  • 1990-1994  (47)
  • 1980-1984  (167)
  • 1970-1974
  • 1930-1934  (2)
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Year
  • 1
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    Constraints on Himalayan deformation inferred from vertical velocity fields in Nepal and Tibet (1994)
    In:  J. Geophys. Res., Amsterdam, Schweizerbart'sche Verlagsbuchhandlung, vol. 99, no. 2, pp. 13897-13912, pp. L07302, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Details
    Publication Date: 1994
    Keywords: China ; Tectonics ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Deep seismic sounding (espec. cont. crust) ; Velocity depth profile ; Earth model, also for more shallow analyses ! ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Structures and kinematics in the northeastern Mediterranean: A study of an irregular plate boundary (1994)
    In:  Tectonophys., New York, Allerton Press, vol. 234, no. 13, pp. 5-18, pp. L13315, (ISSN: 1340-4202)
    Details
    Publication Date: 1994
    Keywords: Earth model, also for more shallow analyses ! ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Plate tectonics ; Turkey
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Aspherical earth structure from fundamental spheroidal-mode data (1982)
    In:  Nature, Bonn, Inst. f. Theoret. Geodäsie, vol. 298, no. B1, pp. 609-613, pp. B01401, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Earth model, also for more shallow analyses ! ; Low frequency ... ; (The Earth's free) oscillations ; NOModelling
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    The density contrast at the Mohorovicic discontinuity (1994)
    In:  Geophys. J. Int., Zagreb, 3-4, vol. 117, no. 3, pp. 539-544, pp. B06305, (ISSN: 1340-4202)
    Details
    Publication Date: 1994
    Keywords: Mohorovicic disc. ; Earth model, also for more shallow analyses ! ; Physical properties of rocks ; Gravimetry, Gravitation ; GJI
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Attenuation in the earth at low frequencies (1982)
    In:  Phil. Trans. Roy. Soc. London, Bonn, Inst. f. Theoret. Geodäsie, vol. A308, no. B1, pp. 479-522, pp. B01401, (ISSN: 1340-4202)
    Details
    Publication Date: 1982
    Keywords: Quality factor ; Rheology ; Low frequency ... ; Earth model, also for more shallow analyses ! ; Physical properties of rocks
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Experiments testing seismographic methods for determining crustal structure (1933)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 44, no. 3, pp. 170-171, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1933
    Keywords: CRUST ; Earth model, also for more shallow analyses ! ; Seismology ; Velocity depth profile
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Regional scale tectonic evolution and the seismic velocity structure of the lithosphere and upper mantle: The Mediterranean region (1994)
    In:  J. Geophys. Res., London, Geological Society, vol. 99, no. 11, pp. 12091-12108, pp. L11303, (ISBN 1-86239-117-3)
    Details
    Publication Date: 1994
    Keywords: Tectonics ; Turkey ; Earth model, also for more shallow analyses ! ; Tomography ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Seismic velocities and Q-factors in the uppermost crust beneath the SVEKA profile in Finland (1994)
    In:  Tectonophys., Warszawa, Icelandic Meteorological Office, Ministry for the Environment,, vol. 230, no. 4, pp. 1-19, pp. 1567, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1994
    Keywords: Seismics (controlled source seismology) ; Attenuation ; Earth model, also for more shallow analyses ! ; Velocity depth profile ; Quality factor
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Pn velocities beneath continental collision zones: The Turkish-Iranian Plateau (1994)
    In:  Geophys. J. Int., Oxford and Edinburgh, Blackwell Scientific Publications, vol. 117, no. 1, pp. 273-283, pp. 1549, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1994
    Keywords: P-waves ; Plate tectonics ; Velocity analysis ; earth mantle ; Mohorovicic disc. ; Earth model, also for more shallow analyses ! ; Velocity depth profile ; GJI
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Seismological constraints on the gabbro-eclogite transition in subducted oceanic crust (1994)
    In:  Earth planet. Sci. Lett., Kleinmachnow, Dt. Geophys. Ges. e. V., vol. 122, no. 6, pp. 89-101, pp. B05401, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1994
    Keywords: Seismology ; Earth model, also for more shallow analyses ! ; Subduction zone ; phase ; transition
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Shear-wave velocity variations in the upper mantle beneath central Europe (1994)
    In:  Geophys. J. Int., Kunming, China, 3-4, vol. 117, no. 1, pp. 695-715, pp. B05S18, (ISSN: 1340-4202)
    Details
    Publication Date: 1994
    Keywords: Shear waves ; Earth model, also for more shallow analyses ! ; Velocity depth profile ; earth mantle ; GJI
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Erde (physikalische Beschaffenheit) (1933)
    Gustav Fischer
    In:  Professional Paper, Handwörterbuch der Naturwissenschaften Bd. 3, Jena, Gustav Fischer, vol. 3, no. VIIa, pp. 762-774, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1933
    Keywords: Handbook of geophysics ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    Differenti tipi di litosfera e differenti stili di subduzione negli Appennini (1994)
    Gruppo Nazionale di Geofisica della Terra Solida
    In:  Atti del 13. Convegno Annuale del Gruppo Nazionale di Geofisica della Terra Solida, Roma, Gruppo Nazionale di Geofisica della Terra Solida, vol. C 560, 183 pp., no. 70, pp. 13-24, (ISBN 3-933346-037)
    Details
    Publication Date: 1994
    Keywords: Subduction zone ; Italy ; Earth model, also for more shallow analyses ! ; Elasticity
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    BIBLIOGRAPHY SEISMOLOGY
  • 14
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    The Interior of the Earth: its Structure, Constitution and Evolution (1982)
    Edward Arnold
    In:  London, Edward Arnold, vol. 70, pp. 158, (ISBN 3-9808780-0-7)
    Details
    Publication Date: 1982
    Keywords: Textbook of geophysics ; Earth model, also for more shallow analyses ! ; Tectonics ; Plate tectonics ; Modelling ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; GeodesyY ; Seismology ; Finite Element Method
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  • 15
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    Angolo di subduzione in astenosfera in moto (1994)
    Gruppo Nazionale di Geofisica della Terra Solida
    In:  Atti del 13. Convegno Annuale del Gruppo Nazionale di Geofisica della Terra Solida, Roma, Gruppo Nazionale di Geofisica della Terra Solida, vol. C 560, 183 pp., no. 78 (?), pp. 193-210, (ISBN 3-933346-037)
    Details
    Publication Date: 1994
    Keywords: Subduction zone ; Italy ; Earth model, also for more shallow analyses ! ; Elasticity
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  • 16
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    Mission 59 to survey earth with multiband radar (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The preparations for Space Shuttle Mission 59 are described, as are the planned mapping operations of the Space Imaging Radar C (SIR-C). Crew tasks and shuttle maneuvers during the 18 million square mile Earth mapping mission are also outlined.
    Keywords: SPACE TRANSPORTATION
    Type: Aviation Week and Space Technology (ISSN 0005-2175); 140; 15; p. 64-65
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  • 17
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    Navier-Stokes simulations of Orbiter aerodynamic characteristics including pitch trim and bodyflap (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: An analysis of the longitudinal aerodynamics of the shuttle orbiter in the hypersonic flight regime is made through the use of computational fluid dynamics. Particular attention is given to establishing the cause of the 'pitching moment anomaly,' which occurred on the orbiter's first flight, and to computing the aerodynamics of a complete orbiter configuration at flight conditions. Data from ground-based facilities as well as orbiter flight data are used to validate the computed results. Analysis shows that the pitching moment anomaly is a real-gas chemistry effect that was not simulated in ground-based facilities, which used air as a test gas. Computed flight aerodynamics for the orbiter are within 5% of the measured flight values and trim bodyflap deflections are predicted to within 10%.
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 31; 3; p. 355-366
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  • 18
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    Unsteady environments and responses of the shuttle combined loads orbiter test (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Both separate and combined wind tunnel and vibration shaker tests were conducted on two structural panels representative of the Shuttle orbiter in the NASA LaRC 8-foot transonic pressure tunnel to determine the effects of combined loads on the thermal protection system (TPS). The primary objective of this test was to provide a combined full-scale load environment and realistic time history of the dynamic pressures, Mach numbers (through transonic), and dynamic structural responses of these panels. The panels were selected from orbiter locations where interactive load sources such as aerodynamic shock waves, turbulent boundary layers, strut-induced vorticity, and substrate deformation combined to provide high bonding loads between the TPS and the orbiter structure. The test panels were highly instrumented with static and dynamic pressure gages, accelerometers, deflectometers, strain gages, Schileren and high speed photography, and special instrumentation necessary to determine TPS/structure interface loads and tile motions. Two test specimens of each orbiter panel were utilized. Both were high-fidelity representations of the selected orbiter location.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 157-163
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  • 19
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    Buffet loads on shuttle thermal-protection-system tiles (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Results of wind-tunnel and acoustic tests to investigate buffet loads on Shuttle Thermal-Protection-System (TPS) tiles are given. Also described is the application of these results to the prediction of tile buffet loads for the first shuttle flight into orbit. The wind-tunnel tests of tiles were conducted at transonic and supersonic Mach numbers simulating flow regions on the Orbiter where shock waves and boundary-layer separations occur. The acoustic tests were conducted in a progressive wave tube at an overall sound pressure level (OASPL) approximately equal to the maximum OASPL measured during the wind-tunnel tests in a region of flow separation. The STS-1 buffet load predictions yielded peak tile stresses due to buffeting that were as much as 20 percent of the total stress for the design-load case when a shock wave was on a tile.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 147-153
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  • 20
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    Dynamic and static modeling of the shuttle orbiter's thermal protection system (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The dynamic and static analysis methods used to model the nonlinear structural behavior of the Shuttle Orbiter's tile/pad thermal protection system are discussed. The structural evaluation of the tile/pad system is complicated by the nonlinear stiffening, hysteresis and viscosity exhibited by the pad material. Application of the analysis to square tiles subject to sinusoidal and random excitation is presented along with appropriate test data. Correlation is considered good. In order to treat the stress analysis of thousands of individual tiles, a nonlinear static analysis was developed which utilizes equivalent static loads derived from the dynamic environment. Tensile stress at the bondline is examined in thousands of unique tiles.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 127-145
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  • 21
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    The development and verification of shuttle orbiter random vibration test requirements (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The unique space shuttle vehicle size, weight, and configuration gave rise to problems in determining vibration requirements and in verifying structural integrity for anticipated mission environments. The applications of large-scale vibration testing played a prominent part in qualifying the shuttle for its intended missions. Severe vibration excitation from rocket engines, aerodynamic noise, and onboard equipment are expected on each shuttle flight. Scale-model wind tunnel and rocket firing tests, as well as full-size rocket engine tests were relied on to define the random forcing functions. The determination of structural response to these environments is described as well as evaluations of measured flight data and comparison with predicted design and test criteria.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 71-80
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  • 22
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    Space shuttle solid rocket booster reentry and decelerator system loads and dynamics (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Recovery of the space shuttle solid rocket boosters required development of a heavy duty large decelerator subsystem. Successful recovery of the first launch pair of boosters demonstrated the adequacy of the design. Flight data consisting of accelerometers and parachute attach point loads provide a basis for evaluation of the decelerator subsystem performance. These results are summarized and compared to preflight predictions.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 27-33
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  • 23
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    Remote orbital servicing system concept (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Increased applications of automation technology identified as necessary for NASA to carry out its missions within the constraints of future funding and available physical resources are described. A concept for a Remote Orbital Servicing System (ROSS) based on present teleoperator and robotics technology is presented. A single servicer design compatible with three specified spacecraft, capable of performing service to the same extent as manned extravehicular activity, controlled from a ground control station, and using currently available technology is conceptualized.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; p 104-119
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  • 24
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    Open cherry picker simulation results (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: The simulation program associated with a key piece of support equipment to be used to service satellites directly from the Shuttle is assessed. The Open Cherry Picker (OCP) is a manned platform mounted at the end of the remote manipulator system (RMS) and is used to enhance extra vehicular activities (EVA). The results of simulations performed on the Grumman Large Amplitude Space Simulator (LASS) and at the JSC Water Immersion Facility are summarized.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 17 p
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  • 25
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    Satellite retrieval and servicing operations with proximity operations modules (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: The concept of manned and unmanned proximity modules (POM) to assist the Orbiter in retrieval, servicing, and emergency operations of orbiting payloads is discussed. An unmanned POM, capable of examining or capturing and returning to the Orbiter large satellites which are station-keeping at distances up to one kilometer from the Orbiter, is presented and its design features defined. Also presented is the concept of a manned POM which is capable of capturing and maneuvering smaller payloads in or about the Orbiter payload bay. The manned POM also serves as a free flying work station used to support satellite servicing and provide a back-up to Orbiter situations when the remote manipulator is inoperative.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 21 p
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  • 26
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    Design objectives of the multimission modular spacecraft (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Servicing economics for LANDSAT are examined. The following objectives of the multimission modular spacecraft are outlined: retrieval; multimission capability; standard flight support system; standard hardware; repair and refurbishment on orbit; instrument replacement; standard ground support system; and standard software.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; p 168-199
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  • 27
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    Spacecraft automatic umbilical system (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: A conceptual definition of an appropriate berthing technique and a prototype design of an automatic umbilical system suitable for use with payloads carried by the Space Shuttle are presented. A four-element berthing system is described. This concept consists of a set of four remote manipulator system (RMS)-type end-effector capture/tie-down devices on the power system and corresponding RMS-type grapple fittings on the payload. In operation, the RMS maneuvers the payload to a position where the four grapple fittings can be snared within the end-effectors and then secured to the power system. The concept takes advantage of mechanisms and operating techniques developed for attaching the RMS to a payload. Although the umbilical installation is attached to the docking interface structure, its operation is independent and it must comply with a set of primary requirements specified by Marshall Space Flight Center (MSFC), which is presented.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 39 p
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  • 28
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    Advanced service equipment (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Orbiter-based service equipment needs/usage are identified by considering a broad spectrum of on-orbit operational scenarios associated with three primary mission events: initial launch, revisits, and Earth return. Nominal and alternate modes of operation, contingency situations (as remote manipulator system inoperative), and Orbiter close proximity operations are included. Satellite classes considered are direct delivery and servicing of the orbiter, low Earth orbiter/propulsion, sorties and DOD, geosatellites, and planetary and other satellites.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; p 1-28
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  • 29
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    The Space Shuttle orbiter payload retention systems (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Payloads are secured in the orbiter payload bay by the payload retention system or are equipped with their own unique retention systems. The orbiter payload retention mechanisms provide structural attachments for each payload by using four or five attachment points to secure the payload within the orbiter payload bay during all phases of the orbiter mission. The payload retention system (PRS) is an electromechanical system that provides standarized payload carrier attachment fittings to accommodate up to five payloads for each orbiter flight. The mechanisms are able to function under either l-g or zero-g conditions. Payload berthing or deberthing on orbit is accomplished by utilizing the remote manipulator system (RMS). The retention mechanisms provide the capability for either vertical or horizontal payload installation or removal. The payload support points are selected to minimize point torsional, bending, and radial loads imparted to the payloads. In addition to the remotely controlled latching system, the passive system used for nondeployable payloads performs the same function as the RMS except it provides fixed attachments to the orbiter.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; p 216-227
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  • 30
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    Characteristics of the handling and positioning aid (1982)
    In:  CASI
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    Publication Date: 2006-04-12
    Description: The handling and positioning aid which (HPA) provides a wide range of adjustable work stations both inboard and outboard of the cargo bay is discussed. It can assist with berthing and docking, it is robust, stiff, has a simple control system, and is modular. An articulated arm version of HPA employed in a typical servicing mission is shown. Mounted on a base frame that spans the Orbiter cargo bay, the 6 m arm is long enough to hold the satellite being serviced and keep its solar array clear of the Orbiter radiators. By adjusting the length and angle of the support platform mast, and rotating the tip of the HPA arm, almost every item on the satellite can be reached. Spares and change-out units can be brought to and from the work site by the RMS, which is controlled from the aft flight deck. The fore and aft position of the base frame can be changed between Orbiter flights and this, together with the 5 degrees of freedom (DOF) of the long arm, allows work sites to be chosen that meet the clearance, reach and vision requirements of many missions. Flight article activities are shown are shown above the dashed horizontal line and Development Test Article (DTA) work below. Flight article requirements and concepts and the design of the DTA are developed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 15 p
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  • 31
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    Space operations center applications of satellite service equipment (1982)
    In:  CASI
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    Publication Date: 2006-04-12
    Description: Satellite servicing requirements for a continuously manned Space Operations Center (SOC) are discussed. Applications for Orbiter developed service equipment are described, together with representative satellite servicing operations for use on SOC. These services cover the full mission cycle from orbital deployment to on-orbit maintenance/repair and, eventually, removal from orbit. An orbiting base, such as the SOC, can provide many of the same services at less cost than the Space Shuttle transportation system.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 14 p
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  • 32
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    Low-Earth orbit satellite servicing economics (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Servicing economics of low Earth orbit satellites were studied. The following topics are examined: the economic importance of the repair missions; comparison of mission cost as opposed to satellite modulation transfer functions over a 10 year period; the effect of satellite flight rate change due to changes in satellite failure rate; estimated satellite cost reduction with shuttle operation projects from the 1960's to the 1970's; design objectives of the multimission modular spacecraft; and the economic importance of the repair mission.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; p 150-167
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  • 33
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    Servicing costs for representative service missions (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: User cost for three satellite services were assessed. The three missions are: advanced X-ray astrophysics facility (AXAF) revisit; upper atmosphere research satellite (UARS) revisit: and solar maximum mission (SMM) Earth return. Service scenarios for the missions to identify service equipment needs and on orbit usage were developed. The AXAF revisit is a service mission involving a contamination sensitive satellite. Following servicing and checkout, the spacecraft is redeployed from the orbiter. The total user charges for revisit missions is from 5 to 10% less than the cost to build and relaunch a replacement satellite. It is indicated that satellite servicing from the Orbiter is cost effective.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 11 p
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  • 34
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    A preliminary study of the particulate fallout from the space shuttle (STS-1) (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Prediction of acid fallout and the dry deposition of Al2O2 was the objective of this investigation. Sampling was done at the Kennedy Space Center in Florida. The models available were not appropriate and the data available was negligible. Thus, a bimodal particle distribution was assumed normalized to the few existing data points and used as a foundation for a crude zeroth order approximation for the acid fallout. In addition, a settling spectrum for the Al2O3 particles was devised as a table look-up since the graphs in the literature at first pass could not be fitted with reasonable analytic functions. Consulting services were rendered to researchers. Special emphasis was placed on improving current techniques and adding LIDAR (Light Radar). Suggestions for future studies are made.
    Keywords: SPACE TRANSPORTATION
    Type: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 8 p
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    Multiblock analysis for Shuttle Orbiter reentry heating from Mach 24 to Mach 12 (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A multiblock, laminar heating analysis for the shuttle orbiter at three trajectory points ranging from Mach 24.3 to Mach 12.86 on reentry is described. The analysis is performed using the Langley Aerothermodynamic Upwind Relaxation Algorithm with a seven species chemical nonequilibrium model. A finite-catalytic-wall model appropriate for shuttle tiles at a radiative equilibrium wall temperature is applied. Computed heating levels are generally in good agreement with the flight data, although a few rather large discrepancies remain unexplained. The multiblock relaxation strategy partitions the flowfield into manageable blocks requiring a fraction of the computational resources (time and memory) required by a full domain approach. In fact, the computational cost for a solution at even a single trajectory point would be prohibitively expensive at the given resolution without the multiblock approach. Converged blocks are reassembled to enable a fully coupled converged solution over the entire vehicle, starting from a nearly converged initial condition.
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 31; 3; p. 367-377
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    Space Shuttle progress report (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The Shuttle flight test plan is detailed, together with the results of tests of the flight control system (FCS). The initial Columbia flights carried 13,000 lb of instrumentation, and will be replaced with a 97 lb package during subsequent flights when further data are desired. The flight test program, besides gathering aerodynamic data, was heavily concerned with the perormance of the SSME (near-nominal), the thermal protection system (the performance and reusability have been demonstrated), and the data processing system (ground verification tests vindicated). Ascent has been nominal, as have orbital maneuvers, and descent roll/yaw has proven smoother than other high performance aircraft. Accelerometers and crewmembers have not been able to sense the smoothness of reentry RCS-controlled maneuvers. The manual controls are noted to serve only in off-nominal situations. The STS is concluded to be a basically sound vehicle, assuring a routine American presence in space.
    Keywords: SPACE TRANSPORTATION
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    Space Shuttle/high energy upper stage capabilities for the 1990's (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Possible performance gains and cost reductions available through the evolution of succeedingly larger unmanned, and then manned, orbital transfer vehicles (OTV) as Shuttle upper stages are projected. Future missions could include delivery of 10,000 lb to GEO, planetary missions in the 2000-12,000 lb class, 30-42 ft payloads in the 5000-10,000 lb class, and manned and unmanned satellite servicing by the turn of the century. The vehicles could evolve from the Centaur F vehicle through stages of all-propulsive configurations to aerobraked, fully reusable vehicles. Reusability introduces cost savings and the ability to make plane changes. Furthermore, aerobraking will double the payload capability for round trip journeys to GEO, bringing costs down to $7000/lb.
    Keywords: SPACE TRANSPORTATION
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  • 38
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    Single point random modal test technology application to failure detection (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Frequency response function data, normally acquired as a data base for use in development of empirically based mode shapes, has additional utility. Comparison and analysis of frequency response function data sets obtained prior to and after environmental tests of an Orbiter body flap have enabled identification of structural damage that was not detected by conventional visual, X-ray, and ultrasonic inspections. The analyses and conclusions reported demonstrate that specific damaged areas within a relatively complex structure identified on a timely basis.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 4; p 25-31
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  • 39
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    Studies of the ionization states of solar and galactic cosmic ray heavy nuclei (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Enhancement of abundances of heavy nuclei (e.g., Mg, Si, and Fe) at low energies relative to solar photospheric abundances and anomalously high abundances of iron relative to oxygen nuclei at low energies were recently discovered in solar energetic particles studied at low energy. These phenomena are not understood at present. The proposed experiment is designed to study the recently discovered anomalous component of low energy galactic cosmic ray ions of C, N, O, Ne, and Ca to Fe of energy 5- to 10-million electron volts per atomic mass unit in regard to their ionization states, composition, and intensity, and to study the ionization states of heavy elements from oxygen to iron in energetic solar particles emitted during flare events. The same detector system will serve for both studies, with the second objective being given priority if there are any solar particle events during the mission.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Marshall Space Flight Center Spacelab Mission 3 Expt. Descriptions; p 35-37
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  • 40
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    Atmospheric trace molecule spectroscopy (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The Spacelab investigation entitled Atmospheric Trace Molecule Spectroscopy (ATMOS) is designed to obtain fundamental information related to the chemistry and physics of the Earth's upper atmosphere using the techniques of infrared absorption spectroscopy. There are two principal objectives to be met. The first is the determination, on a global scale, of the compositional structure of the upper atmosphere and its spatial variability. The establishment of this variability represents the first step toward determining the characteristic residence times for the upper atmospheric constituents; the magnitudes of their sources and sinks; and, ultimately, an understanding of their effects on the stability of the stratosphere. The second objective is to provide the high-resolution, calibrated spectral information which is essential for the detailed design of advanced instrumentation for subsequent global monitoring of specific species found to be critical to atmospheric stability. This information will be disseminated in the form of a three dimensional atlas of solar absorption spectra obtained over a range of latitudes, longitudes, and altitudes.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Marshall Space Flight Center Spacelab Mission 3 Expt. Descriptions; p 29-33
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  • 41
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    Ames Research Center life sciences payload (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: In response to a recognized need for an in-flight animal housing facility to support Spacelab life sciences investigators, a rack and system compatible Research Animal Holding Facility (RAHF) has been developed. A series of ground tests is planned to insure its satisfactory performance under certain simulated conditions of flight exposure and use. However, even under the best conditions of simulation, confidence gained in ground testing will not approach that resulting from actual spaceflight operation. The Spacelab Mission 3 provides an opportunity to perform an inflight Verification Test (VT) of the RAHF. Lessons learned from the RAHF-VT and baseline performance data will be invaluable in preparation for subsequent dedicated life sciences missions.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Marshall Space Flight Center Spacelab Mission 3 Expt. Descriptions; p 21-26
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  • 42
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    Geophysical fluid flow cell experiment (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The primary purpose of the geophysical flow experiments is to simulate large-scale baroclinic (density-stratified) flows which occur naturally in the atmospheres of rotating planets and stars and to gain insights and obtain answers to crucial questions concerning the large-scale nonlinear mechanics of the global geophysical flows. Those external conditions related to fluid viscosity, rotation, gravity are identified, which allow qualitatively different modes of instability or waves in the model.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Marshall Space Flight Center Spacelab Mission 3 Expt. Descriptions; p 17-19
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  • 43
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    Dynamics of rotating and oscillating free drops (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The Dynamics of Rotating and Oscillating Free Drops (DROP) experiment is to be performed using the Drop Dynamics Module (DDM). The main scientific objectives of the DROP experiment are the study of the equilibrium figures of a rotating drop and the study of the large-amplitude oscillations of a liquid drop. The objective of the DROP experiment in relation to the DDM is to establish the advantages of conducting future drops and bubbles experiments in space. The DROP experiment will be subjected to continual to ensure that the experiments are scientifically current and available. The two component experiments (rotation and oscillation) of the DROP experiment have been chosen as the simplest experiments representative of the entire class of drop dynamics experiments. The component experiment on the equilibrium shapes of a rotating liquid drop of a simple liquid is not only an important and interesting experiment in its own right, but is also the simplest gyrostatic experiment that can be performed. In later experiments, more complicated liquids can be used; bubbles can be included; and the dynamics of rotating drops can be studied. This experiment, as it now stands, is an important exercise of the module's ability to provide drop rotation and the requisite science data.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Marshall Space Flight Center Spacelab Mission 3 Expt. Descriptions; p 13-16
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  • 44
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    The Space Shuttle - Description, operation, and evolution (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: System specifications, launch procedures, costs, payloads, and evolutionary developments in the STS are outlined. The Shuttle employs solid propellant boosters and an external cryogenic fuel tank to achieve LEO for the manned Orbiter, which can maneuver in space and return to earth like a glider. The Shuttle can place a maximum payload of 30 tons into a 275 km orbit. An Inertial Upper Stage and a Spinning Solid Upper Stage will be carried by the Orbiter in its bay and used to boost satellites into GEO. Additionally, the Orbiter is equipped with a remote manipulator system for removing cargo from the bay and for grappling satellites for retrieval or repair. The Shuttle is presently launched from Kennedy Space Center, while a second launch site is being prepared at Vandenberg AFB. The STS is intended to perform 28-40 flights per year by the end of the 1980s. An Orbital Transfer Vehicle is under study to increase the size and length of payloads which can be placed in GEO using the Shuttle. Utilization of the concept is noted to be connected with the development of a permanently manned space station.
    Keywords: SPACE TRANSPORTATION
    Type: L'Aeronautique et l'Astronautique; 95, 1; 1982
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  • 45
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    Mercury iodide crystal growth (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The purpose of the Mercury Iodide Crystal Growth (MICG) experiment is the growth of near-perfect single crystals of mercury Iodide (HgI2) in a microgravity environment which will decrease the convection effects on crystal growth. Evaporation and condensation are the only transformations involved in this experiment. To accomplish these objectives, a two-zone furnace will be used in which two sensors collect the temperature data (one in each zone).
    Keywords: SPACE TRANSPORTATION
    Type: Spacelab Mission 3 Expt. Descriptions; p 9-11
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  • 46
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    Mercuric iodide (HgI2) growth for nuclear detectors (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The purpose of this investigation is to grow more-perfect mercuric iodide crystals in a low-gravity environment by taking advantage of diffusion-controlled growth conditions and by avoiding the problem of strain dislocations produced by the crystal's weight. This crystal has considerable practical importance as a sensitive gamma-ray detector and energy spectrometer that can operate at ambient temperature, as compared to presently available detectors that must be cooled to near liquid nitrogen temperatures. However, the performance of mercuric iodide crystals only rarely approaches the expected performance, presumably because some of the free electrical charges produced within the crystal are not collected at the electrodes, but instead remain trapped or immobilized at crystal defects. An efficient high atomic number semiconductor detector capable of operating at room temperature utilizing single HgI2 crystals offers a greater potential than existing detector technology.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Marshall Space Flight Center Spacelab Mission 3 Expt. Descriptions; p 5-8
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  • 47
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    Space transportation (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The physical laws governing launch vehicles are reviewed, together with the performance of launch vehicles thus far used and expected developments in space transportation systems. Launches are generally made in the direction of earth rotation to take advantage of the initial velocity in that direction, which can amount to about 0.46 km/sec at the equator. Spacecraft usually attain a parking orbit, where spacecraft conditions are assessed before moving on to final orbit or interplanetary trajectory. Rocket batteries were first used in a battle near Beijing in 1232, and manned space flight began with the Vostok flight in 1961, followed by the Apollo lunar landings in the later 1960s. Rocket thrust performance is analyzed, together with the thrust/mass ratio for ascent and descent. The Shuttle, capable of placing 29.5 t in LEO, will be or is equipped to also carry IUS and PAM engines for transferring payloads from LEO to GEO. Parallel burn boosters may be added to increase the payload capability, and Shuttle-derived launch vehicles may be developed to carry construction materials to space and return to earth for a runway landing. Alternatively, the Shuttle engines may be modularized in order to develop a heavy-lift launch vehicle for unmanned cargo ascents.
    Keywords: SPACE TRANSPORTATION
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  • 48
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    Load-limiting landing gear footpad energy absorption system (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: As a precursor to future manned missions to the moon, an inexpensive, unmanned vehicle that could carry small, scientific payloads to the lunar surface was studied by NASA. The vehicle, called the Common Lunar Lander, required extremely optimized structural systems to increase the potential payload mass. A lightweight energy-absorbing system (LAGFEAS), which also acts as a landing load-limiter was designed to help achieve this optimized structure. Since the versatile and easily tailored system is a load-limiter, it allowed for the structure to be designed independently of the ever-changing landing energy predictions. This paper describes the LAGFEAS system and preliminary verification testing performed at NASA's Johnson Space Center for the Common Lunar Lander program.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Lewis Research Center, The 28th Aerospace Mechanisms Symposium; p 429-441; NASA-CP-3260
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  • 49
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    Simulation of Shuttle launch G forces and acoustic loads using the NASA Ames Research Center 20G centrifuge (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The high cost and long times required to develop research packages for space flight can often be offset by using ground test techniques. This paper describes a space shuttle launch and reentry simulating using the NASA Ames Research Center's 20G centrifuge facility. The combined G-forces and acoustic environment during shuttle launch and landing were simulated to evaluate the effect on a payload of laboratory rates. The launch G force and acoustic profiles are matched to actual shuttle launch data to produce the required G-forces and acoustic spectrum in the centrifuge test cab where the rats were caged on a free-swinging platform. For reentry, only G force is simulated as the aero-acoustic noise is insignificant compared to that during launch. The shuttle G-force profiles of launch and landing are achieved by programming the centrifuge drive computer to continuously adjust centrifuge rotational speed to obtain the correct launch and landing G forces. The shuttle launch acoustic environment is simulated using a high-power, low-frequency audio system. Accelerometer data from STS-56 and microphone data from STS-1 through STS-5 are used as baselines for the simulations. This paper provides a description of the test setup and the results of the simulation with recommendations for follow-on simulations.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Goddard Space Flight Center, Eighteenth Space Simulation Conference: Space Mission Success Through Testing; p 349-371
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  • 50
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    Solution growth of crystals in zero gravity (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A series of experiments will be performed in which triglycine sulfate (TGS) crystals will be grown by a low-temperature solution growth technique in the microgravity environment of the orbital Spacelab. Triglycine sulfate (TGS) crystals will be grown in the Fluid Experiment System (FES) facility on Spacelab 3 by slowly extracting heat at a controlled rate through a seed crystal of TGS suspended on an insulated sting in a saturated solution of TGS. The FES rack assembly designed for SL-3 is shown in Figure I-1, and a detailed view of the test cell layout is presented in Figure I-2. Variations in the liquid density, solution concentration and temperature around the growing crystal will be studied using a variety of techniques, such as schlieren, shadowgraph, and interferometric measurements. Growth in Earth gravity will also be studied by the same optical techniques, and in both cases the resulting crystalline features will be compared and correlated with the growth conditions.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Marshall Space Flight Center Spacelab Mission 3 Expt. Descriptions; p 3-4
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  • 51
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    Flight support system mechanisms (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Flight Support System (FSS) which contains twelve mechanisms (six different types) which are used for retention and positioning of a Multimission Modular Spacecraft (MMS) within the Space Shuttle's cargo bay during launch, retrieval, and servicing missions is described. Retention latches were designed to provide the capability for structural support of the MMS during launch and retrieval, and during servicing operations the mechanisms on the Positioning Platform provide the capability for positioning the MMS in virtually any orientation necessary for the work to be performed. In addition, there are mechanisms for matching and demating umbilical connectors and a mechanism for locking the Positioning Platform during maneuvers. Each Mechanism is driven by a Common Drive Unit. Manual overrides were provided for those mechanisms that would present a safety hazard for the crew, if they should fail.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Kennedy Space Center The 16th Aerospace Mech. Symp.; p 23-44
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  • 52
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    Baggie: A unique solution to an orbiter icing problem (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The orbiter icing problem, located in two lower surface mold line cavities, was solved. These two cavities are open during Shuttle ground operations and ascent, and are then closed after orbit insertion. If not protected, these cavities may be coated with ice, which may be detrimental to the adjacent thermal protection system (TPS) tiles if the ice breaks up during ascent, and may hinder the closing of the cavity doors if the ice does not break up. The problem of ice in these cavities was solved by the use of a passive mechanism called baggie, which is purge curtain used to enclose the cavity and is used in conjunction with gaseous nitrogen as the local purge gas. The baggie, the final solution, is unique in its simplicity, but its design and development were not. The final baggie design and its development testing are discussed. Also discussed are the baggie concepts and other solutions not used.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Kennedy Space Center The 16th Aerospace Mech. Symp.; p 1-22
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  • 53
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    STS-57 Post Flight Press Conference (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This video contains footage selected and narrated by crew members.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109838 , NONP-NASA-VT-94-12966
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  • 54
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    STS-59/SRL-1 (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This video covers the STS-59 mission. Video segments include breakfast, suit-up, departure, launch, on-orbit operations, and landing.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109837 , NONP-NASA-VT-94-12965
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  • 55
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    Minimum accommodation for aerobrake assembly, phase 2 (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A multi-element study was done to assess the practicality of a Space Station Freedom-based aerobrake system for the Space Exploration Initiative. The study was organized into six parts related to structure, aerodynamics, robotics and assembly, thermal protection system, inspection, and verification, all tied together by an integration study. The integration activity managed the broad issues related to meeting mission requirements. This report is a summary of the issues addressed by the integration team.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-107608 , NAS 1.15:107608
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  • 56
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    Development of a nondestructive vibration technique for bond assessment of Space Shuttle tiles (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This final report describes the achievements of the above titled project. The project is funded by NASA-KSC (Grant No. NAG 10-0117) for the period of 1 Jan. to 31 Dec. 1993. The purpose of this project was to develop a nondestructive, noncontact technique based on 'vibration signature' of tile systems to quantify the bond conditions of the thermal protection system) tiles of Space Shuttle orbiters. The technique uses a laser rapid scan system, modal measurements, and finite element modeling. Finite element models were developed for tiles bonded to both clamped and deformable integrated skin-stringer orbiter mid-fuselage. Results showed that the size and location of a disbonded tile can be determined from frequency and mode shape information. Moreover, a frequency response survey was used to quickly identify the disbonded tiles. The finite element results were compared with experimentally determined frequency responses of a 17-tile test panel, where a rapidscan laser system was employed. An excellent degree of correlation between the mathematical simulation and experimental results was realized. An inverse solution for single-tile assemblies was also derived and is being implemented into a computer program that can interact with the modal testing software. The output of the program displays the size and location of disbond. This program has been tested with simulated input (i.e., finite element data), and excellent agreement between predicted and simulated disbonds was shown. Finally, laser vibration imaging and acoustic emission techniques were shown to be well suited for detecting and monitoring the progressive damage in Graphite/Epoxy composite materials.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-195163 , NAS 1.26:195163
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  • 57
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    Space Shuttle Main Engine (SSME) Pogo testing and results (1982)
    In:  CASI
    Details
    Publication Date: 2015-07-14
    Description: To effectively assess the Pogo stability of the space shuttle vehicle, it was necessary to characterize the structural, propellant, and propulsion dynamics subsystems. Extensive analyses and comprehensive testing programs were established early in the project as an implementation of management philosophy of Pogo prevention for space shuttle. The role of the space shuttle main engine (SSMF) in the Pogo prevention plans, the results obtained from engine ground testing with analysis, and measured data from STS-1 flight are discussed.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 1-20
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  • 58
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    The design and development of an end effector for the shuttle remote manipulator system (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design requirements, the design, and qualification and development test problems encountered on the Remote Manipulator End Effector are described. The constraints and interfaces with the arm, the Orbiter, and the payload are identified. The design solution to meet the requirements is a unique device that provides a soft-docking feature termed capture and a hard-docking feature termed rigidization.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Kennedy Space Center The 16th Aerospace Mech. Symp.; p 45-62
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  • 59
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    The Shuttle Environment Workshop, executive summary and workshop procedures (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: One of the main experimental monitors used to determine the environment in the payload bay was the Induced Environment Contamination Monitor. This package of instruments has made environmental measurements during STS flights with a high degree of success. This has shown that the shuttle environment is relatively free of contaminants, except for special instances of increased abundance of methane, water vapor and particulates. Results of these measurements are rapidly becoming more available. In establishing the Shuttle Environment Workshop, the findings were shared with scientific experimenters, users and other individuals who need to know what the Shuttle is like and what experimenters may expect in the payload bay. The Workshop was centered around results obtained from the environmental measurements made on the Shuttle. The program agenda for the workshop is given. The procedures and flow of communications for the workshop are indicated.
    Keywords: SPACE TRANSPORTATION
    Type: The Shuttle Environ. Workshop; p 1-7
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  • 60
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    Fluids management technology (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Various techniques and methods in fluid management are discussed. Propellant on-orbit transfer efficiency from the space shuttle orbiter to orbital transfer vehicle is discussed. Techniques such as refueling, residuals recovery and propellant storage are described.
    Keywords: SPACE TRANSPORTATION
    Type: Satellite Serv. Workshop, Vol. 1; p 381-405
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  • 61
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    Space platform (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The space platform subsystem design characteristics are described in detail. Compatibility with the STS/orbiter is an important factor.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 320-334
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  • 62
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    Payload installation and deployment aid for space shuttle orbiter spacecraft remote manipulator system (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An aid concept known as the PIDA (Payload Installation and Deployment Aid) is presented as a way to assist the Remote Manipulator System (RMS) by relaxing the accuracy required during payload handling in the payload bay. The aid concept was designed and developed to move payloads through a prescribed path between the confined quarters of the payload bay and a position outside the critical maneuvering area of the Orbiter. An androgynous docking mechanism is used at the payload/PIDA interfaces for normal docking functions that also serves as the structural connection between the payload and the Orbiter, that is capable of being loosened to prevent transfer of loads between a stowed payload and the PIDA structure. A gearmotor driven drum/cable system is used in the docking mechanism in a unique manner to center the attenuator assembly, align the ring and guide assembly (docking interface) in roll, pitch, and yaw, and rigidize the mechanism at a nominal position. A description of the design requirements and the modes of operation of the various functions of the deployment and the docking mechanisms are covered.
    Keywords: SPACE TRANSPORTATION
    Type: Satellite Serv. Workshop, Vol. 1; p 335-349
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    Spacecraft Redundancy and Environmental Tests: An Historic Evaluation (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The necessity of providing highly redundant spacecraft in the shuttle era was evaluated. Environmental and acceptance tests were done. Histories of 67 spacecraft over a 12 year period were analyzed. The final result of this study is that LMSC (Lockheed Missiles and Space Co., Inc.) is convinced of the significant value of redundancy in spacecraft and systems environmental testing and such techniques should be carried forward into the shuttle era.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 229-246
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  • 64
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    Cryogenic fluid transfer - orbital transfer vehicle (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Fluid transfer requirements are presented for the orbital transfer vehicle (OTV) issues such as OTV configuration, hardware design and size are taken into consideration. Tank chilldown, tank fill and thermodynamic properties are all evaluated in relationship to fluid transfer needs.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 431-448
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  • 65
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    Berthing/docking (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Three studies were completed establishing sensor performance, technology status, and conceptual design requirements for rendezvous stationkeeping, and docking. A consideration of design constraints and the availale technology has led to the conclusion that the sensor should be a CW optical radar employing a semiconductor-laser transmitter and an image-dissector receiver. The performance obtainable for a representative sensor was compared to specifications generated during the study and it was found that this type of sensor can meet the needs of future Earth-orbital operations.
    Keywords: SPACE TRANSPORTATION
    Type: Satellite Serv. Workshop, Vol. 1; p 350-380
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  • 66
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    Orbiter OMS and RCS technology (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Orbiter Orbital Maneuver Subsystem (OMS) and Reaction Control Subsystem (RCS) tankage has proved to be highly successful in shuttle flights on-orbit propellant transfer tests were done. Tank qualification tests along with flight demonstrations were carried out future uses of storable propellants are cited.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 406-430
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  • 67
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    Electrophoresis operations in space (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Application of electrophoresis in space processing is described. Spaceborne experiments in areas such as biological products and FDA approved drugs are discussed. These experiments will be carried on shuttle payloads.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 307-319
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  • 68
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    Co-orbiting mechanics (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The motions of co-orbiting satellites is examined with reference to a free flying satellite requiring periodic servicing and an orbiting service base. The problems of differential orbit decay and nodal regression are emphasized.
    Keywords: SPACE TRANSPORTATION
    Type: Satellite Serv. Workshop, Vol. 1; p 166-181
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  • 69
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    Development of automated rendezvous and proximity operations techniques for rendezvous and close-in operations and satellite servicing (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The development of freeflyer maneuvering system and shuttle orbiter flight profiles and hardware/software requirements that will provide and automated rendezvous, station keeping, and docking capability is discussed. Automated control techniques, sensors, target vehicle requirements, and a soft docking system are addressed.
    Keywords: SPACE TRANSPORTATION
    Type: Satellite Serv. Workshop, Vol. 1; p 110-136
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  • 70
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    Manned maneuvering unit (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design of the manned maneuvering unit and associated flight support station is described. Thrust and maneuver capabilities per propellant supply are calculated and special consideration is given to the requirements for rotational maneuvers with large cargos. Satellite attachment devices and a remote controlled small payload maneuvering system are also discussed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 32-43
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  • 71
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    Space Shuttle External Tank Gaseous Oxygen Vent System (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Two problems had to be solved to assure successful elimination of ice on the External Tank (ET). First, an access/support structure was provided from the Launch Complex 39A Fixed Service Structure to the vicinity of the nose cone on the ET approximately 82.3 meters (270 feet) above the surface of the pad and 22.9 meters (75 feet) from the face of the FSS. Second, an umbilical was designed and tested that would seal around the ET gaseous oxygen (GOX) vent louvers and not allow ice to form on the tank or the umbilical. A modified Apollo service arm was chosen. An inflatable vent seal subsystem was chosen, providing a cloth seal around each vent louver with an internal annulus to provide a path for the gaseous oxygen from the ET to a hard duct on the swing arm.
    Keywords: SPACE TRANSPORTATION
    Type: The 16th Aerospace Mech. Symp.; p 299-313
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  • 72
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    Advanced extravehicular mobility unit study (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Components of the advanced extravehicular mobility unit (suit) are described. Design considerations for radiation protection, extravehicular operational pressure, mobility effects, tool/glove/effector, anthropometric definition, lighting, and equipment turnaround are addressed.
    Keywords: SPACE TRANSPORTATION
    Type: Satellite Serv. Workshop, Vol. 1; p 197-214
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  • 73
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    Solar maximum observatory repair mission (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A description of the Solar Maximum Observatory and the operational status of its instrument systems is presented. The major science objectives which could be made possible with repairs to the spacecraft are defined. Hardware requirements and procedures for a repair mission are detailed. In general the mission involves: (1) the capture and control of the observatory in free flight by an astronaut in the manned manipulator unit; (2) berthing the observatory to the orbiter with the remote manipulator system; and (3) repairing the scientific instruments and replacing the attitude control system through extravehicular activity.
    Keywords: SPACE TRANSPORTATION
    Type: Satellite Serv. Workshop, Vol. 1; p 137-165
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  • 74
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    The Extravehicular Mobility Unit (EMU): Proven hardware for Satellite Servicing (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A general technical description of the extravehicular mobility unit (EMU) is given. The description provides a basis for understanding EMU mobility capabilities and the environments a payload is exposed to in the vicinity of an EMU.
    Keywords: SPACE TRANSPORTATION
    Type: Satellite Serv. Workshop, Vol. 1; p 44-72
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    Teleoperator maneuvering system (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The teleoperator maneuvering system (TMS), consisting of the vehicle, the shuttle orbiter bay cradle with airborne support equipment, and the aft flight deck control station, is described. The vehicle is a reusable remotely controlled free flying vehicle capable of a variety of missions including payload placement, retrieval, servicing, viewing, and large space systems assembly support. The TMS flies preprogrammed trajectories as well as being controlled or reprogrammed from the aft flight deck or the ground. A building block design philosophy is described which permits the evolution of capability as it is needed and delays cost as much as possible. Various mission operations are discussed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 73-100
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  • 76
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    Satellite services system overview (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The benefits of a satellite services system and the basic needs of the Space Transportation System to have improved satellite service capability are identified. Specific required servicing equipment are discussed in terms of their technology development status and their operative functions. Concepts include maneuverable television systems, extravehicular maneuvering unit, orbiter exterior lighting, satellite holding and positioning aid, fluid transfer equipment, end effectors for the remote manipulator system, teleoperator maneuvering system, and hand and power tools.
    Keywords: SPACE TRANSPORTATION
    Type: Satellite Serv. Workshop, Vol. 1; p 1-9
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  • 77
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    Design of the materials experiment carrier for on-orbit servicing (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This paper discussed the MEC system and its mission from the viewpoint of orbit servicing. Information is provided on MEC system requirements, design for on orbit servicing, on orbit servicing operations and rationale and servicing costs.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 261-289
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  • 78
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    Design considerations for on-orbit servicing (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An overview of the general design of space vehicles serviced in orbit is presented. The basic space vehicle systems, subsystems, modules components, and associated appendages comprise the elements to be considered. Primary emphasis is given to the multi-disciplinary considerations in the development of requirements, and in particular, design of the space vehicle to facilitate orbital sevice by the extra-vehicular crew person(s).
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 290-306
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  • 79
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    Payload processing and integration at KSC (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The shuttle payload processing facilities at the Kennedy Space Center and the payload processing and integrating procedures are briefly outlined.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 182-196
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  • 80
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    Payload IVA training and simulation (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The development of a training program for the intravehicular operation of space shuttle payloads is discussed. The priorities for the program are compliance with established training standards, and accommodating changes. Simulation devices are also reviewed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 215-228
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    Analysis of satellite servicing cost benefits (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Under the auspices of NASA/JSC a methodology was developed to estimate the value of satellite servicing to the user community. Time and funding precluded the development of an exhaustive computer model; instead, the concept of Design Reference Missions was involved. In this approach, three space programs were analyzed for various levels of servicing. The programs selected fall into broad categories which include 80 to 90% of the missions planned between now and the end of the century. Of necessity, the extrapolation of the three program analyses to the user community as a whole depends on an average mission model and equivalency projections. The value of the estimated cost benefits based on this approach depends largely on how well the equivalency assumptions and the mission model match the real world. A careful definition of all assumptions permits the analysis to be extended to conditions beyond the scope of this study.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 1; p 247-260
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  • 82
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    The role of SRMS in satellite servicing (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The standard configuration of the shuttle remote manipulator system (RMS) is reviewed and the role of the RMS in satellite servicing is discussed. The RMS tasks include payload deployment, retrieval/berthing, large spacecraft assembly/module exchange, assist astronaut extravehicular servicing, and remote servicing. The potential growth of the RMS to increase its utilization and improve its performance is also addressed. The projected concepts include dual arm operation, a remote mounted RMS, and special purpose end effectors. In particular, a universal service tool system with both remote and manual modes of operation is described.
    Keywords: SPACE TRANSPORTATION
    Type: Satellite Serv. Workshop, Vol. 1; p 10-31
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  • 83
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    Centerline latch tool for contingency orbiter door closure (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The centerline latch tool was designed and developed as an EVA manual backup device for latching the Space Shuttle Orbiter's payload bay doors for reentry in case of a failure of the existing centerline latches to operate properly. The tool was designed to satisfy a wide variety of structural, mechanical, and EVA requirements. It provides a load path for forces on the payload bay doors during reentry. Since the tool would be used by an EVA crewmember, control, handgrips, operating forces, and procedures must be within the capabilities of a partially restrained, suited crewmember in a zero-gravity environment. The centerline latch tool described was designed, developed, and tested to meet these requirements.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Kennedy Space Center The 16th Aerospace Mech. Symp.; p 63-85
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  • 84
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    Memorial Service for the Mission 51-L Crew (Edited) (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The original memorial service held at NASA JSC for the STS-51L Challenger crew who died onboard the Shuttle is presented. President Ronald Reagan conducts this briefing.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109900 , NONP-NASA-VT-94-28241
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  • 85
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    STS-61 Mission Highlights Resource Tape (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This contains important visual events including launch, Hubble Space Telescope (HST) capture, repair and re-deployment, onboard activities, earth views, and landing. Also included is the air-to-ground transmission between the crew and Mission Control.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109963 , NONP-NASA-VT-94-28240
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  • 86
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    STS-62 Mission Highlights Resource Tape (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The important visual events of each mission including launch, onboard crew activities, and landing are depicted.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109943 , NONP-NASA-VT-94-23623 , VJSC-1413
    Format: text
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  • 87
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    STS-58 Space Shuttle Mission Report (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The STS-58 Space Shuttle Program Mission Report provides a summary of the payload activities as well as the orbiter, external tank (ET), solid rocket booster (SRB) and redesigned solid rocket motor (RSRM), and the space shuttle main engine (SSME) subsystems performance during the fifty-eighth mission of the space shuttle program and fifteenth flight of the orbiter vehicle Columbia (OV-102). In addition to the orbiter, the flight vehicle consisted of an ET (ET-57); three SSME's, which were designated as serial numbers 2024, 2109, and 2018 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-061. The lightweight RSRM's that were installed in each SRB were designated as 360L034A for the left SRB and 360W034B for the right SRB.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109867 , NAS 1.15:109867 , NSTS-08287
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  • 88
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    STS-60 Space Shuttle mission report (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The STS-60 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixtieth flight of the Space Shuttle Program and eighteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET designated at ET-61 (Block 10); three SSME's which were designated as serial numbers 2012, 2034, and 2032 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-062. The RSRM's that were installed in each SRB were designated as 360L035A (lightweight) for the left SRB, and 360Q035B (quarterweight) for the right SRB. This STS-60 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume VIII, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objectives of the STS-60 mission were to deploy and retrieve the Wake Shield Facility-1 (WSF-1), and to activate the Spacehab-2 payload and perform on-orbit experiments. Secondary objectives of this flight were to activate and command the Capillary Pumped Loop/Orbital Debris Radar Calibration Spheres/Breman Satellite Experiment/Getaway Special (GAS) Bridge Assembly (CAPL/ODERACS/BREMSAT/GBA) payload, the Auroral Photography Experiment-B (APE-B), and the Shuttle Amateur Radio Experiment-II (SAREX-II).
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-197233 , JSC-08289 , NSTS-08289 , NAS 1.26:197233
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    STS-59 Mission Highlights Resource Tape (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The important visual events of each mission including launch, onboard crew activities, and landing are depicted.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109945 , NONP-NASA-VT-94-23625
    Format: text
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  • 90
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    STS-60 Mission Highlights Resource Tape (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The important visual events of each mission including launch, onboard crew activities, and landing are depicted.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109942 , NONP-NASA-VT-94-23622
    Format: text
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  • 91
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    Debris/Ice/TPS assessment and integrated photographic analysis for Shuttle Mission STS-61 (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A debris/ice/thermal protection system (TPS) assessment and integrated photographic analysis was conducted for shuttle mission STS-61. Debris inspections of the flight elements and launch pad were performed before and after launch. Icing conditions on the external tank were assessed by the use of computer programs, nomographs, and infrared scanner data during cryogenic loading of the vehicle followed by on-pad visual inspection. High speed photography of the launch was analyzed to identify ice/debris sources and evaluate potential vehicle damage and/or in-flight anomalies. This report documents the ice/debris/TPS conditions and integrated photographic analysis of shuttle mission STS-61, and the resulting effect on the space shuttle program.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109195 , NAS 1.15:109195
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  • 92
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    STS-61 Space Shuttle mission report (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The STS-61 Space Shuttle Program Mission Report summarizes the Hubble Space Telescope (HST) servicing mission as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the fifty-ninth flight of the Space Shuttle Program and fifth flight of the Orbiter vehicle Endeavour (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET designated as ET-60; three SSME's which were designated as serial numbers 2019, 2033, and 2017 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-063. The RSRM's that were installed in each SRB were designated as 360L023A (lightweight) for the left SRB, and 360L023B (lightweight) for the right SRB. This STS-61 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume 8, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objective of the STS-61 mission was to perform the first on-orbit servicing of the Hubble Space Telescope. The servicing tasks included the installation of new solar arrays, replacement of the Wide Field/Planetary Camera I (WF/PC I) with WF/PC II, replacement of the High Speed Photometer (HSP) with the Corrective Optics Space Telescope Axial Replacement (COSTAR), replacement of rate sensing units (RSU's) and electronic control units (ECU's), installation of new magnetic sensing systems and fuse plugs, and the repair of the Goddard High Resolution Spectrometer (GHRS). Secondary objectives were to perform the requirements of the IMAX Cargo Bay Camera (ICBC), the IMAX Camera, and the Air Force Maui Optical Site (AMOS) Calibration Test.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-110545 , NSTS-08288 , NAS 1.15:110545
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    STS-62 Space Shuttle mission report (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The STS-62 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSHE) systems performance during the sixty-first flight of the Space Shuttle Program and sixteenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Orbiter, the flight vehicle consisted of an ET designated as ET-62; three SSME's which were designated as serial numbers 2031, 2109, and 2029 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-064. The RSRM's that were installed in each SRB were designated as 360L036A (lightweight) for the left SRB, and 36OWO36B (welterweight) for the right SRB. This STS-62 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume 8, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objectives of the STS-62 mission were to perform the operations of the United States Microgravity Payload-2 (USMP-2) and the Office of Aeronautics and Space Technology-2 (OAST-2) payload. The secondary objectives of this flight were to perform the operations of the Dexterous End Effector (DEE), the Shuttle Solar Backscatter Ultraviolet/A (SSBUV/A), the Limited Duration Space Environment Candidate Material Exposure (LDCE), the Advanced Protein Crystal Growth (APCG), the Physiological Systems Experiments (PSE), the Commercial Protein Crystal Growth (CPCG), the Commercial Generic Bioprocessing Apparatus (CGBA), the Middeck Zero-Gravity Dynamics Experiment (MODE), the Bioreactor Demonstration System (BDS), the Air Force Maui Optical Site Calibration Test (AMOS), and the Auroral Photography Experiment (APE-B).
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-110450 , NSTS-08290 , NAS 1.15:110450
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    STS-59 Space Shuttle mission report (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The STS-59 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-second flight of the Space Shuttle Program and sixth flight of the Orbiter vehicle Endeavor (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET designated as ET-63; three SSME's which were designated as serial numbers 2028, 2033, and 2018 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-065. The RSRM's that were installed in each SRB were designated as 360W037A (welterweight) for the left SRB, and 360H037B (heavyweight) for the right SRB. This STS-59 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume 8, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objective of the STS-59 mission was to successfully perform the operations of the Space Radar Laboratory-1 (SRL-1). The secondary objectives of this flight were to perform the operations of the Space Tissue Loss-A (STL-A) and STL-B payloads, the Visual Function Tester-4 (VFT-4) payload, the Shuttle Amateur Radio Experiment-2 (SAREX-2) experiment, the Consortium for Materials Development in Space Complex Autonomous Payload-4 (CONCAP-4), and the three Get-Away Special (GAS) payloads.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-110527 , NSTS-08291 , NAS 1.15:110527
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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    STS-65 Space Shuttle mission report (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The STS-65 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-third flight of the Space Shuttle Program and the seventeenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Orbits the flight vehicle consisted of an ET that was designated ET-64; three SSME's that were designated as serial numbers 2019, 2030, and 2017 in positions 1, 2, and 3, respectively; and two SRB's that were designated Bl-066. The RSRM's that were installed in each SRB were designated as 360P039A for the left SRB, and 360W039 for the right SRB. The primary objective of this flight was to complete the operation of the second International Microgravity Laboratory (IML-2). The secondary objectives of this flight were to complete the operations of the Commercial Protein Crystal Growth (CPCG), Orbital Acceleration Research Experiment (OARE), and the Shuttle Amateur Radio Experiment (SAREX) II payloads. Additional secondary objectives were to meet the requirements of the Air Force Maui Optical Site (AMOS) and the Military Application Ship Tracks (MAST) payloads, which were manifested as payloads of opportunity.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-197598 , NAS 1.26:197598 , NSTS-08292
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 96
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    STS-66 Post Flight Presentation (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This video contains mission footage selected by the STS-66 crew of pre-launch, launch, onboard activities and experiments, ATLAS-3, CRISTA/SPAS, SSBUV/A, ESCAPE II, Earth views, and landing. Crew members provide descriptive voice-over narration of the scenes.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-110077 , NONP-NASA-VT-94-33203
    Format: text
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    NASA TECHNICAL REPORTS
  • 97
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    Space Shuttle fatigue loads spectra for prelaunch and liftoff loads (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Fatigue loads spectra for the prelaunch and liftoff flight segments of the Space Shuttle were developed. A variety o methods were used to determine the distributions of several important parameters, such as time of exposure on the launch, pad, month of launch, and wind speed. Also, some lessons learned that would be applicable to development of fatigue loads spectra for other reusable space vehicles are presented.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center, FAA(NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance; p 289-306
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 98
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    STS-68 Post Flight Presentation (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This contains mission footage selected by the STS-68 crew of pre-launch, launch, onboard activities and experiments, Space Radar Laboratory-2 (SRL-2), Get Away Special canisters (GAS cans), Earth views, and landing. Crew members provide descriptive voice-over narration of the scenes.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109959 , NONP-NASA-VT-94-28239
    Format: text
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    NASA TECHNICAL REPORTS
  • 99
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    STS-65 Mission Highlights Resource Tape (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The important visual events of each mission including launch, onboard crew activities, and landing are depicted.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-108589 , NONP-NASA-VT-94-28238
    Format: text
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    NASA TECHNICAL REPORTS
  • 100
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    From Undersea to Outer Space: The STS-40 Jellyfish Experiment (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This is an educational production featuring 'Ari', animated jellyfish who recounts his journey into space. Jellyfish were flown aboard the shuttle to study the effects of microgravity on living organisms. Topics Ari explores are: microgravity, life sciences, similarities between jellyfish and humans, and the life cycle and anatomy of a jellyfish.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-109958 , NONP-NASA-VT-94-28236
    Format: text
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    NASA TECHNICAL REPORTS
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