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  • Other Sources  (164)
  • SPACE TRANSPORTATION  (164)
  • 1995-1999
  • 1980-1984  (164)
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  • 1982  (164)
  • 1
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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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  • 2
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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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  • 3
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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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  • 4
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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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  • 5
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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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  • 6
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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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  • 7
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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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  • 8
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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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  • 9
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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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  • 10
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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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  • 11
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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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  • 12
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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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  • 13
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    Characteristics of the handling and positioning aid (1982)
    In:  CASI
    Details
    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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  • 14
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    Space operations center applications of satellite service equipment (1982)
    In:  CASI
    Details
    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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  • 15
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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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  • 16
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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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  • 17
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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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  • 18
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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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  • 19
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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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  • 20
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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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  • 21
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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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  • 22
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    Atmospheric trace molecule spectroscopy (1982)
    In:  Other Sources
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    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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  • 23
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    Ames Research Center life sciences payload (1982)
    In:  Other Sources
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    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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  • 24
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    Geophysical fluid flow cell experiment (1982)
    In:  Other Sources
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    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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  • 25
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    Dynamics of rotating and oscillating free drops (1982)
    In:  Other Sources
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    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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  • 26
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    The Space Shuttle - Description, operation, and evolution (1982)
    In:  Other Sources
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    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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  • 27
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    Mercury iodide crystal growth (1982)
    In:  Other Sources
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    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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  • 28
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    Mercuric iodide (HgI2) growth for nuclear detectors (1982)
    In:  Other Sources
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    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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  • 29
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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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  • 30
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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
    Format: text
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  • 31
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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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  • 32
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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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  • 33
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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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  • 34
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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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  • 35
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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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  • 36
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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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  • 37
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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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  • 38
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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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  • 39
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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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  • 40
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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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  • 41
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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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  • 42
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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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  • 43
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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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  • 44
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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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  • 45
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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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  • 46
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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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  • 47
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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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  • 48
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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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  • 49
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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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  • 50
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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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  • 51
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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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  • 52
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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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  • 53
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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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  • 54
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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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  • 55
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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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  • 56
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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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  • 57
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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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  • 58
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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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  • 59
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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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  • 60
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    Life sciences flight experiments program mission science requirements document. The first life sciences dedicated Spacelab mission, part 1 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Mission Science Requirements Document (MSRD) for the First Dedicated Life Sciences Mission (LS-1) represents the culmination of thousands of hours of experiment selection, and science requirement definition activities. NASA life sciences has never before attempted to integrate, both scientifically and operationally, a single mission dedicated to life sciences research, and the complexity of the planning required for such an endeavor should be apparent. This set of requirements completes the first phase of a continual process which will attempt to optimize (within available programmatic and mission resources) the science accomplished on this mission.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-87494 , JSC-18295-PT-1 , NAS 1.15:87494
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  • 61
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    Study of outgassing and decomposition of space shuttle heat protection tiles, fillers and adhesive (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this project was to determine the chemicals desorbing from the space shuttle heat protection tiles. The original protocol for this project involved direct insertion probe mass spectrometry (DIPMS) analysis of the outgassing products from the tiles. However, this method proved unsatisfactory due to the large number of compounds desorbing from the tiles. A purge and trap technique was then employed to collect and separate the chemicals desorbing from the tiles. The maximum temperature in this analysis was 180 C which is the gas chromatograph fused silica capillary column's temperature limit. The desorption was also carried out at atmospheric pressure with helium as the purge gas. A description of the modified protocol is given. All compounds are tentatively identified.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-175565 , NAS 1.26:175565
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  • 62
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    Mission definition study for a VLBI station utilizing the Space Shuttle (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The uses of the Space Shuttle transportation system for orbiting VeryLong-Baseline Interferometry (OVLBI) were examined, both with respect to technical feasibility and its scientific possibilities. The study consisted of a critical look at the adaptability of current technology to an orbiting environment, the suitability of current data reduction facilities for the new technique, and a review of the new science that is made possible by using the Space Shuttle as a moving platform for a VLBI terminal in space. The conclusions are positive in all respects: no technological deficiencies exist that would need remedy, the data processing problem can be handled easily by straightforward adaptations of existing systems, and there is a significant new research frontier to be explored, with the Space Shuttle providing the first step. The VLBI technique utilizes the great frequency stability of modern atomic time standards, the power of integrated circuitry to perform real-time signal conditioning, and the ability of magnetic tape recorders to provide essentially error-free data recording, all of which combine to permit the realization of radio interferometry at arbitrarily large baselines.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-175126 , NAS 1.26:175126
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    Outside users payload model (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-170171 , NAS 1.26:170171 , BCL-NLVP-IM-82-1
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    Evaluation of Space Transportation System (STS) OV-102 orbiter payload bay acoustic environment (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of a statistical analysis and evaluation performed by the Mechanical Engineering Branch (Code 731) on the payload bay internal acoustic data measured on the STS-1 through STS-4 flights. The results are used as a basis for developing the required baseline acoustic environment specification to be used in establishing design and test criteria for STS payloads and components.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-84958 , NAS 1.15:84958
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    A method for determining the flight readiness of the integrated Space Shuttle system (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Space Shuttle Dynamic Integrated Test (DIT) system is described. The DIT is an open-loop system which makes no attempt to simulate Shuttle sensors, and by which the Shuttle redundancy management system is left unmodified. Open-loop operation is shown to inherently require less computing capacity during a test than the closed-loop alternative. DIT tests have generated a high degree of confidence in the Shuttle hardware, allowing the identification of such problems as a sluggish main fuel valve, which caused a countdown hold seconds before the simulated T-zero, and Main Engine Controller software malfunctions. Attention is given to the combination and substitution of sensor data, the modification of nominal flight software, and the preparation of simulation data. It is noted that greater performance would have been achieved if the interface with DIT had been a design requirement from the outset of Space Shuttle development.
    Keywords: SPACE TRANSPORTATION
    Type: vol. 35; July 198
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  • 66
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    Atmospheric constraint statistics for the Space Shuttle mission planning (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The procedures used to establish statistics of atmospheric constraints of interest to the Space Shuttle mission planning are presented. The statistics considered are for the frequency of occurrence, runs, and time conditional probabilities of several atmospheric constrants for each of the Space Shuttle mission phases. The mission phases considered are (1) prelaunch, (2) launch, (3) return to launch site, (4) abort once around landing, and (5) end of mission landing.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TP-2069 , NAS 1.60:2069
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  • 67
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    STS-3 main parachute failure (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A failure analysis of the parachute on the Space Transportation System 3 flight's solid rocket booster's is presented. During the reentry phase of the two Solid Rocket Boosters (SRBs), one 115 ft diameter main parachute failed on the right hand SRB (A12). This parachute failure caused the SRB to impact the Ocean at 110 ft/sec in lieu of the expected 3 parachute impact velocity of 88 ft/sec. This higher impact velocity relates directly to more SRB aft skirt and more motor case damage. The cause of the parachute failure, the potential risks of losing an SRB as a result of this failure, and recommendations to ensure that the probability of chute failures of this type in the future will be low are discussed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-82490 , NAS 1.15:82490
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  • 68
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    NASA Educational Briefs for the Classroom. Shuttle's Fourth Test Flight (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The STS-4 is described. The environmental characteristics of the Shuttle cargo bay and near space were measured. Experiments performed during the flight are briefly summarized.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-EB-82-5
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  • 69
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    Space operations center: Shuttle interaction study extension, executive summary (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Space Operations Center (SOC) is conceived as a permanent facility in low Earth orbit incorporating capabilities for space systems construction; space vehicle assembly, launching, recovery and servicing; and the servicing of co-orbiting satellites. The Shuttle Transportation System is an integral element of the SOC concept. It will transport the various elements of the SOC into space and support the assembly operation. Subsequently, it will regularly service the SOC with crew rotations, crew supplies, construction materials, construction equipment and components, space vehicle elements, and propellants and spare parts. The implications to the SOC as a consequence of the Shuttle supporting operations are analyzed. Programmatic influences associated with propellant deliveries, spacecraft servicing, and total shuttle flight operations are addressed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-167766 , NAS 1.26:167766 , SSD-81-0194
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  • 70
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    Evolutionary space platform concept study. Volume 2, part A: SASP special emphasis trade studies (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Efforts are in progress to define an approach to provide a simple and cost effective solution to the problem of long duration space flight. This approach involves a Space Platform in low Earth orbit, which can be tended by the Space Shuttle and which will provide, for extended periods of time, stability, utilities and access for a variety of replaceable payloads. The feasibility of an evolutionary space system which would cost effectively support unmanned payloads in groups, using a Space Platform which provides centralized basic subsystems is addressed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-170828 , NAS 1.26:170828 , MDC-H0072 , DPD-610 , DR-4
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  • 71
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    Pressure scaled water impact test of a 12.5 inch diameter model of the Space Shuttle solid rocket booster (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A total of 59 tail first drops were made. Model entry conditions simulated full scale vertical velocities of approximately 75 to 110 ft/sec with horizontal velocities up to 45 ft/sec and impact angles to + or - 10 deg. These tests were conducted at scaled atmospheric pressures (1.26 psia or 65 mm.Hg). The model, test program, test facility, test equipment, instrumentation system, data reduction procedures, and test results are described.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-170761 , NAS 1.26:170761 , TN-SM-82-9
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  • 72
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    Survey of Spaceflight Safety Systems /Survey period: July 1981 June 1982/ (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Information from the Survey of Spaceflight Safety Systems considered most applicable to present and future spaceflight activities is summarized. Mission reports for the first three Shuttle Orbiter flights discuss all anomalies which occurred and their resolution, such as the solid rocket booster ignition overpressure spike, and thermal tile damage. Two emergency rescue systems for orbiting space stations are proposed: a dish type rescue capsule and a reusable orbit vehicle. Prebreathing and stage decompression are considered as means of protecting astronauts against decompression effects. The Spacelab Space Sled experiments are described, as is a test program on the assembly of large space structures completed in mid-1981. Finally, collision hazards for space missions are estimated, and operational procedures for minimizing these hazards are discussed.
    Keywords: SPACE TRANSPORTATION
    Type: IAF PAPER 82-259
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  • 73
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    Capability of the manned maneuvering unit to support satellite servicing operations (1982)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Features, capabilities, and projected performances and missions of the Manned Maneuvering Unit (MMU) are described. A zero gravity, autonomous, six degree of freedom mobility system using gaseous nitrogen for propulsion, the MMU is equipped with jets for attitude and rotational control, 24 thrusters total, with each providing 7.5 N thrust. The unit is controled from hand controllers used by the pilot, in addition to an automatic attitude control using outputs from a gyroscope pack in the control electronics assembly. EVA periods of 6 hrs are possible with the 150 kg MMU and its fuel complement of 12 kg of gaseous N. Refueling is allowed through an Orbiter interface at the same location the MMU is stowed. The MMU has a delta-V capability of 20 m/sec, with a thrust duration of 7085 N-sec, implying the EVA suit limit will be reached before propellant can be exhausted. The results of various mission simulations for the MMU are reported.
    Keywords: SPACE TRANSPORTATION
    Type: IAF PAPER 82-30
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  • 74
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    The tethered retrievable platform concept and utilization (1982)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Main components of the current configuration of a proposed tethered satellite system (TSS) for deploying instrumentation up to 100 km upward or downward from the Orbiter in LEO are described. The TSS consists of the Deployer Module, the Tether, and the Satellite Module, and remains connected to the equipment in the Orbiter bay for the entire mission. The Deployer Module is mounted on a pallet, and has a boom, a tether control mechanism, and a tether control capability, in addition to data acquisition and control systems. The Satellite Module features a thermal control, electrical power and distribution, data management and communication, attitude determination, propulsion, and payload capability. Deployment is unpowered, taking advantage instead of gravity gradients to move the payload from the Orbiter. Safety features include a cutter mechanism to disengage the tether from the Orbiter if retrieval of the payload is judged to endanger the crew and the Orbiter.
    Keywords: SPACE TRANSPORTATION
    Type: IAF PAPER 82-13
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  • 75
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    Advanced Space Shuttle simulation model (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of atmospheric turbulence in horizontal and near-horizontal flight during the return of the Space Shuttle are important for determining design, control, and pilot-in-the-loop effects. A nonrecursive model (based on vonKarman spectra) for atmospheric turbulence along the flight path of the Shuttle Orbiter has been developed which provides for simulation of instantaneous vertical and horizontal gusts at the vehicle center-of-gravity and also for simulation of instantaneous gust gradients. Based on this model the time series for gusts and gust gradients have been generated and stored on a series of magnetic tapes which are entitled Shuttle Simulation Turbulence Tapes (SSTT). The time series are designed to represent atmospheric turbulence from ground level to an altitude of 120,000 meters. A description of the turbulence generation procedure is provided, the results of validating the simulated turbulence are described, and conclusions and recommendations are presented. Appendices provide tabulated one-dimensional vonKarman spectra, a discussion of the minimum frequency simulated, and the results of spectral and statistical analyses of the SSTT.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-3541 , M-377 , NAS 1.26:3541
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    Application of multi-function display and control technology (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The NASA orbiter spacecraft incorporates a complex array of systems, displays, and controls. The incorporation of discrete dedicated controls into a multifunction display and control system (MFDCS) offers the potential for savings in weight, power, panel space, and crew training time. Technology identified as applicable to a MFDCS is applied to the orbiter orbital maneuvering system (OMS) and the electrical power distribution and control system (EPDCS) to derive concepts for a MFDCS design. Several concepts of varying degrees of performance and complexity are discussed and a suggested concept for further development is presented in greater detail. Both the hardware and software aspects and the human factors considerations of the designs are included.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-167583 , NAS 1.26:167583 , D180-26988-1
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  • 77
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    Sensitivity analysis of the space shuttle to ascent wind profiles (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A parametric sensitivity analysis of the space shuttle ascent flight to the wind profile is presented. Engineering systems parameters are obtained by flight simulations using wind profile models and samples of detailed (Jimsphere) wind profile measurements. The wind models used are the synthetic vector wind model, with and without the design gust, and a model of the vector wind change with respect to time. From these comparison analyses an insight is gained on the contribution of winds to ascent subsystems flight parameters.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TP-1988 , M-374 , NAS 1.60:1988
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  • 78
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    Space Shuttle STS-1 SRB damage investigation (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The physical damage incurred by the solid rocket boosters during reentry on the initial space shuttle flight raised the question of whether the hardware, as designed, would yield the low cost per flight desired. The damage was quantified, the cause determined and specific design changes recommended which would preclude recurrence. Flight data, postflight analyses, and laboratory hardware examinations were used. The resultant findings pointed to two principal causes: failure of the aft skirt thermal curtain at the onset of reentry aerodynamic heating, and overloading of the aft shirt stiffening rings during water impact. Design changes were recommended on both the thermal curtain and the aft skirt structural members to prevent similar damage on future missions.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-82461 , NAS 1.15:82461
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  • 79
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    Survey of multi-function display and control technology (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The NASA orbiter spacecraft incorporates a complex array of systems, displays and controls. The incorporation of discrete dedicated controls into a multi-function display and control system (MFDCS) offers the potential for savings in weight, power, panel space and crew training time. The technology applicable to the development of a MFDCS for orbiter application is surveyed. Technology thought to be applicable presently or in the next five years is highlighted. Areas discussed include display media, data handling and processing, controls and operator interactions and the human factors considerations which are involved in a MFDCS design. Several examples of applicable MFDCS technology are described.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-167510 , D180-26864-1
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  • 80
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    Advanced Space Shuttle simulation model (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A non-recursive model (based on von Karman spectra) for atmospheric turbulence along the flight path of the shuttle orbiter was developed. It provides for simulation of instantaneous vertical and horizontal gusts at the vehicle center-of-gravity, and also for simulation of instantaneous gusts gradients. Based on this model the time series for both gusts and gust gradients were generated and stored on a series of magnetic tapes, entitled Shuttle Simulation Turbulence Tapes (SSTT). The time series are designed to represent atmospheric turbulence from ground level to an altitude of 120,000 meters. A description of the turbulence generation procedure is provided. The results of validating the simulated turbulence are described. Conclusions and recommendations are presented. One-dimensional von Karman spectra are tabulated, while a discussion of the minimum frequency simulated is provided. The results of spectral and statistical analyses of the SSTT are presented.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-161958 , EAI-TR-82-001
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  • 81
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    Space transportation system flight 2 OSTA-1 scientific payload data management plan: Addendum (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight events for the OSTA-1 scientific payload on the second flight of the Space Shuttle, STS-2 are described. Data acquisition is summarized. A discussion of problems encountered and a preliminary evaluation of data quality is also provided.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-169827 , NAS 1.26:169827 , OTA/TR-82/0025
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  • 82
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    An evaluation of Space Shuttle STS-1 payload bay acoustic data and comparison with predictions (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: During the first launch (STS-1) of the Space Shuttle orbiter vehicle, sound pressure levels were measured at several locations in the payload bay of the vehicle and on the exterior surface. The data were obtained in order to provide validation for prediction procedures for interior and exterior sound pressure levels and to determine, independently, the acoustic environment in the payload bay during actual launch conditions.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-166811 , NAS 1.26:166811 , REPT-4738
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  • 83
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    Preliminary design of flight hardware for two-phase fluid research (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This study defined the preliminary designs of flight software for the Space Shuttle Orbiter for three two-phase fluid research experiments: (1) liquid reorientation - to study the motion of liquid in tanks subjected to small accelerations; (2) pool boiling - to study low-gravity boiling from horizontal cylinders; and (3) flow boiling - to study low-gravity forced flow boiling heat transfer and flow phenomena in a heated horizontal tube. The study consisted of eight major tasks: reassessment of the existing experiment designs, assessment of the Spacelab facility approach, assessment of the individual carry-on approach, selection of the preferred approach, preliminary design of flight hardware, safety analysis, preparation of a development plan, estimates of detailed design, fabrication and ground testing costs. The most cost effective design approach for the experiments is individual carry-ons in the Orbiter middeck. The experiments were designed to fit into one or two middeck lockers. Development schedules for the detailed design, fabrication and ground testing ranged from 15 1/2 to 18 months. Minimum costs (in 1981 dollars) ranged from $463K for the liquid reorientation experiment to $998K for the pool boiling experiment.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-168072 , NAS 1.26:168072 , BAC-ER-15049
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  • 84
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    Simulation of time-varying ascent loads on arrays of shuttle tiles in a large transonic tunnel (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: For abstract, see A82-24682.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-84529 , L-15439 , NAS 1.15:84529 , AIAA 12th Aerodyn. Testing Conf.; Mar 22, 1982 - Mar 24, 1982; Williamsburg, VA; United States
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  • 85
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    Satellite Services Workshop, volume 2 (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Methods for on-orbit servicing of satellites are discussed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-84874 , JSC-18201-VOL-2 , NAS 1.15:84874 , Jun 22, 1982 - Jun 24, 1982; Houston, TX; United States
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  • 86
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    Satellite Services Workshop, Volume 1 (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Key issues associated with the orbital servicing of satellites are examined including servicing spacecraft and equipment, servicing operations, economics, satellite design, docking and berthing, and fluid management.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-84873 , JSC-18201-VOL-1 , NAS 1.15:84873 , Jun 22, 1982 - Jun 24, 1982; Houston, TX; United States
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  • 87
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    Small payloads for the Shuttle (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Goddard Space Flight Center, Special Payloads Division (sounding rockets) experience in applying rocket mechanical experience and technology to the Shuttle is presented. While the mechanical design loads are similar, new considerations for thermal extremes, material control and attachment structures must be included. These additional requirements have been successfully introduced in the free flyer class of payloads, Shuttle Pointed Automonous Research Tool for Astronomy (SPARTAN), and a motorized door for the Get Away Special (GAS) payloads.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-1762 , Sounding Rocket Conference; Oct 26, 1982 - Oct 28, 1982; Orlando, FL
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  • 88
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    GAS Verification Payload - From concept through flight (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The GAS Verification Payload (GVP), successfully flown on STS-3, was the forerunner of the Get Away Special class of payloads. Intended to provide GAS experiments with flight environmental information, it also served to shape out the GAS support systems and establish areas of programmatic understanding between the GSFC, JSC, and KSC. Originally envisaged as using a sounding rocket build-it, test-it, fly-it approach with minimum paperwork, this naivete dissipated when faced with the manned space flight world of JSC. What evolved was an understanding by both disciplines that safety and reliability could be achieved at lower cost without compromise.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-1758 , Sounding Rocket Conference; Oct 26, 1982 - Oct 28, 1982; Orlando, FL
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  • 89
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    Mission analysis techniques for attached Shuttle payloads (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Visibility times, i.e., times which desired targets are visible to a payload, are examined for attached Shuttle payloads. These times are affected by a number of constraints. Some constraints are examined along with mathematical or computer modeling techniques used to determine their effects. The constraints include: occultation of the earth, moon, and sun, and limb avoidance angles of each; orbit parameters such as inclination and ascending node, along with sensitivity to changes in each; TDRSS acquisition; South Atlantic Anomaly (SAA) avoidance, nighttime viewing only; bright earth avoidance angles; the field of view; Shuttle attitude, and Orbiter operational constraints. All of this information is integrated and, with computer programs, a schedule of observations and Shuttle attitudes is obtained.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-1759 , Sounding Rocket Conference; Oct 26, 1982 - Oct 28, 1982; Orlando, FL
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  • 90
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    The OSS-1/STS-3 mission (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Integration, test, flight operations, program and science management, and experiment results from the OSS-1/STS-3 flight are reviewed. The experimental pallet, manufactured by ESA members, carried instrumentation for astronomy, space plasma studies, physics, planetology, solar physics, and life sciences. The ability of the equipment to operate in a worst-case Orbiter thermal environment was tested, as was the plasma environment around the Orbiter. The solar UV spectral irradiance monitor microprocessor was found to reset concurrently with start-up of the Shuttle hydraulic pumps. Degradations were also observed in one of the three solar flare X ray polarimeter modules, the thermal cannister experiment microprocessor, and the scientific data recorder no. 2. The Orbiter was determined to perform well during firing of an electron beam. A contamination monitor recorded matter accretion to be dependent on the solar orientation of the Orbiter. Finally, the distribution of the responsibilities and tasks for mission management are reviewed.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-1800 , Space Systems Conference: The Space Transportation System: A Review of Its Present Capability and Probable Evolution; Oct 18, 1982 - Oct 20, 1982; Washington, DC
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  • 91
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    Capabilities and limitations of the Shuttle for future cargo programs (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper presents a view of future Shuttle cargo operations. Planned and potential performance improvements are addressed. On-orbit operations, performance and experience are discussed with a view of anticipated changes. Current and future cargo integration activities are also addressed. The future Shuttle user is provided a projection to assist in planning and payload development.
    Keywords: SPACE TRANSPORTATION
    Type: Making space work for mankind; Apr 28, 1982 - Apr 30, 1982; Cocoa Beach, FL
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  • 92
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    Shuttle entry GN&C performance during STS-1 and STS-2 (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Data obtained during the entry segment of the descent phase of the flights are analyzed. The nominal entry profile is defined and a description is given of the guidance, navigation, and control subsystem. Emphasis is placed on the stability and control problems encountered during STS-1 and to the changes made in response to these anomalies. These are: (1) the first roll maneuver was done manually at a reduced roll rate; (2) the nominal elevator position was changed from one degree up to one degree down for Mach numbers greater than 12 to reduce the heat load on the body flap; (3) the pilot was directed to execute small roll maneuvers at dynamic pressures of 4, 8, and 18 psf to help determine the roll moment from the aft yaw jets; (4) the planned test inputs in the transonic region were reduced in magnitude; and (5) the targeted touchdown point was moved 500 feet closer to the runway threshold.
    Keywords: SPACE TRANSPORTATION
    Type: AAS 82-041 , Guidance and control 1982; Jan 30, 1982 - Feb 03, 1982; Keystone, CO; United States
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  • 93
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    Working in space (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The capabilities of the NASA Neutral Buoyancy Simulator (NBS) water tank test facility are described, with reference to the proving of crew-operated mechanisms incorporated by the Space Telescope (ST). There are 24 Orbital Replaceable Units which are subject to handling in space by suited crewmen of the Space Shuttle, the largest of which is comparable to a telephone booth and weighs over 700 lb. The water volume of the simulator is sufficient to accept a full-size mockup of the Space Shuttle cargo bay, in which all ST operations will be conducted. Early ST simulations tested the mechanisms which astronauts would operate during contingency operations. More recently, the simulation tasks have reflected maintenance objectives of ST orbital life prolongation. With the recent addition of a fully functional Remote Manipulator System and the Manned Maneuvering Unit, the simulator constitutes the most complete training ground for extravehicular activities extant.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-1856 , Technology for Space Astrophysics Conference: The Next 30 Years; Oct 04, 1982 - Oct 06, 1982; Danbury, CT
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  • 94
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    Open Cherry Picker simulation results (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The Open Cherry Picker (OCP) is a manned platform, mounted at the end of the Remote Manipulator System (RMS), which is used to enhance extravehicular activities. The objective of the simulation program described was to reduce the existing complexity of those OCP design features that are mandatory for initial Space Shuttle applications. The OCP development test article consists of a torque box, a rotating foot restraint, a rotating stanchion that houses handholds, and a tool storage section with an interface with payload modules. If the size or complexity of the payload increases, payload handling devices may be added at a later data. The simulations have shown that the crew can control the RMS from the Aft Flight Deck of the Shuttle, using voice commands from the EVA crewman. No need for a stabilizer was evident, and RMS dynamics due to crew-induced workloads were found to be minor.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-1848 , Technology for Space Astrophysics Conference: The Next 30 Years; Oct 04, 1982 - Oct 06, 1982; Danbury, CT
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  • 95
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    Space Shuttle flight results (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: System function aspects of the first Space Shuttle mission are assessed. Almost 90 mission anomalies have been identified by a mission evaluation team, which were variously attributed to instrumentation sensor failures, improper operation, or design deficiencies. The two most significant problems encountered were Solid Rocket Booster ignition wave overpressure, which exceeded maximum expected pressure by a factor of 2:1 over most of the Orbiter and 5:1 at a sensor location on the aft bulkhead, near the engines, and an inoperative tumble valve, which would normally have imparted to the Space Shuttle External Tank a tumbling motion, after Tank separation, that insures disintegration of the large structure during reentry. The first problem has been solved by strengthening six support struts, and the second by ensuring that the tumble valve is moisture-free.
    Keywords: SPACE TRANSPORTATION
    Type: Annual Reliability and Maintainability Symposium; Jan 26, 1982 - Jan 28, 1982; Los Angeles, CA
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  • 96
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    Space Shuttle stability and control test plan (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The development of a completely automatic flight test program to test different aspects of the Shuttle flight capability during reentries is described. Data from each flight to date has been employed to devise a sequence of maneuvers which will be keyboard-punched into the Orbiter control system by the astronauts during entry phases of flight. Details of the interaction and cooperation of the Orbiter elevons and bodyflap to provide the vehicle with latitudinal and longitudinal directional control and trim are outlined. Uncertainties predicted for the control of the Orbiter during wind tunnel testing prior to actual flights have been adjusted to actual flight data, leading to the identification of actual flight regimes which need further investigation. Maneuvers scheduled for flights 5-9 are reviewed.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-1315 , Atmospheric Flight Mechanics Conference; Aug 09, 1982 - Aug 11, 1982; San Diego, CA
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  • 97
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    Stability and control flight test results of the space transportation system's orbiter (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Flight testing of the Space Shuttle Orbiter is in progress and current results of the post-flight aerodynamic analyses are discussed. The purpose of these analyses is to reduce the pre-flight aerodynamic uncertainties, thereby leading to operational certification of the Orbiter flight envelope relative to the integrated airframe and flight control system. Primary data reduction is accomplished with a well documented maximum likelihood system identification techniques.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-1316 , Atmospheric Flight Mechanics Conference; Aug 09, 1982 - Aug 11, 1982; San Diego, CA
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  • 98
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    The simulation of time varying ascent loads on arrays of Shuttle tiles in a large transonic tunnel (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A large variety of tests were made to determine the strength, fatigue and thermal characteristics of the thermal-protection system of the Shuttle orbiter. The present paper describes first-launch-critical tests which were conducted in the Langley 8-Foot Transonic Pressure Tunnel (8'TPT) which simulated the time histories of Shuttle ascent loads on tile arrays bonded to structures which accurately duplicated those of the Shuttle. The time varying free-stream conditions were provided by controlling the deflection angle history of diffuser spoiler flaps in an automated way. Time histories of the critical-load parameters imposed on the tile arrays in the tunnel are compared in the paper to those expected in flight. In addition, the effect of repeated load pulses on the smoothness of the surface and condition of the tiles is discussed briefly.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-0566 , Aerodynamic Testing Conference; Mar 22, 1982 - Mar 24, 1982; Williamsburg, VA
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  • 99
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    Space Shuttle entry longitudinal aerodynamic comparisons of flight 2 with preflight predictions (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An overview of the aerodynamic performance, longitudinal trim, and control surface effectiveness as developed from the second Shuttle flight is presented, along with comparisons with preflight predictions. The Orbiter enters the atmosphere at Mach 29 and descends through all the Mach speeds until touchdown. Control mechanisms for the Orbiter are outlined, noting the lessening of angle of attack as the terminal configuration is reached. Methods of developing the wind tunnel predictions are reviewed, including performance in different altitudes and speed regimes, and the impetus to decouple the flight control system from aerodynamics with respect to uncertainties. Preflight predictions agreed well with the lift/drag ratio above Mach 1, but higher L/D was exhibited than predicted below Mach 1. A deficiency in the wind tunnel environment was concluded for the inaccuracies in the predictions for hypersonic trim characteristics.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-0565 , In: Aerodynamic Testing Conference; Mar 22, 1982 - Mar 24, 1982; Williamsburg, VA
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  • 100
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    A preliminary correlation of the orbiter stability and control aerodynamics from the first two Space Shuttle flights /STS-1 & 2/ with preflight predictions (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A correlation of the stability and control derivatives from flight (STS-1 & 2) with preflight predictions is presented across the Mach range from 0.9 to 25. Flight data obtained from specially designed flight test maneuvers as well as from conventional bank maneuvers generally indicate good agreement with predicted data. However, the vehicle appears to be lateral-directionally more stable than predicted in the transonic regime. Aerodynamic 'reasonableness tests' are employed to test for validity of flight data. The importance of testing multiple models in multiple wind tunnels at the same test conditions is demonstrated.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 82-0564 , In: Aerodynamic Testing Conference; Mar 22, 1982 - Mar 24, 1982; Williamsburg, VA
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