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  • Other Sources  (120)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (68)
  • STRUCTURAL MECHANICS  (49)
  • Nuclear explosion
  • 1985-1989  (120)
  • 1980-1984
  • 1940-1944
  • 1985  (120)
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  • Other Sources  (120)
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  • 1985-1989  (120)
  • 1980-1984
  • 1940-1944
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  • 1
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    Expanding role for autonomy in military space (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The Jet Propulsion Laboratory is currently transferring satellite on-board autonomy technology to the USAF for use in military spacecraft as a means of lowering the ground support requirements. The techniques were proven on the Viking and Voyager spacecraft and permitted on-board fault detection and correction. New military satellites will incorporate an autonomous redundancy and maintenance management subsystem in an on-board computer, while the system will still be subject to ground-based safing commands for situations demanding deeper analyses. A level 5 autonomy will need 256 kb memory, 10 Mb nonvolatile data storage and 50 W power and will weigh 20 kg. Systems will be periodically checked and compared with an ideal in the data base. Deviations detected will result in a rollback and redundant examination by two microprocessors, which can initiate correction commands until operational criteria are met. The development of the expert systems to the point that they satisfy military specifications is expected to take 10 yr.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace America (ISSN 0740-722X); 23; 74-77
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    NASA TECHNICAL REPORTS
  • 2
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    The Galeleo spacecraft magnetometer boom (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Galileo spacecraft utilizes a deployable lattice boom to position three science instruments at remote distances from the spacecraft body. An improved structure and mechanism to precisely control deployment of the boom, and the unique deployment of an outer protective cover are described.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Ames Research Center 19th Aerospace Mech. Symp.; p 1-22
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    NASA TECHNICAL REPORTS
  • 3
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    Relative displacement measurements for two-body problems (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: While high-sensitivity moire interferometry is very effective for displacement measurements in continuous bodies, special difficulties arise with two-body problems. Fringes may become discontinuous at the boundary between the bodies and as a result the relative displacements cannot be extracted from the fringe patterns. In this work, flexible bridges are used between the bodies to provide a continuous path for fringe counting. The bridges are made of relatively low modulus material and have a low stiffness geometry, such that they deform under minimal load. The experimental methods used for obtaining relative displacement measurements in two-body problems are described for the two cases; dovetail joint in turbo-machinery, and thick adherend lap joint.
    Keywords: STRUCTURAL MECHANICS
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    NASA TECHNICAL REPORTS
  • 4
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    Polar orbit electrostatic charging of objects in shuttle wake (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A survey of DMSP data has uncovered several cases where precipitating auroral electron fluxes are both sufficiently intense and energetic to charge spacecraft materials such as teflon to very large potentials in the absence of ambient ion currents. Analytical bounds are provided which show that these measured environments can cause surface potentials in excess of several hundred volts to develop on objects in the orbiter wake for particular vehicle orientations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Environ. Interactions Technol., 1983; p 229-234
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  • 5
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    Vibration characteristics of the HPOTP (High Pressure Oxygen Turbopump) of the SSME (Space Shuttle Main Engine) (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A review is presented of various rotordynamic problems which have been encountered and eliminated in developing the current flight engines, and continuing subsynchronous problems which are being encountered in developing a 109% power level engine. The basic model for the High Pressure Oxygen Turbopump (HPOTP) of the SSME including the structural dynamic model for the rotor and housing and component models for the liquid and gas seals, turbine-clearance excitation forces, and impeller-diffuser forces are discussed. Results from a linear model are used to examine the synchronous response and stability characteristics of the HPOTP, examining bearing load and stability problems associated with the second critical speed. Various seal modifications are examined and shown to have favorable consequences with respect to bearing reactions and stability.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Marshall Space Flight Center Advan. High Pressure O2(H2 Technol; p 452-481
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  • 6
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    Some design characteristics of the AMPTE turn and orbit change maneuvers (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The maneuvers carried out by the Active Magnetospheric Particle Tracer Explorers (AMPTE) including the Charge Composition Explorer (CCE) and the Ion Release Module (IRM) spacecraft are analyzed. Analytic and graphical methods are developed in order to carry out sensitivity analyses that helped design the nominal maneuvers, by taking into account errors in burn initiating time, motor performance, and spin axis pointing. A tradeoff analysis between errors in timing and Delta V magnitude is shown for the IRM orbit transfer, and a technique that allows for the determination of the attitude of spinner spacecraft by way of the observed Doppler shift resulting from an unbalanced turn is investigated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 85-0217
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    SIRTF Telescope Instrument Changeout and Cryogen Replenishment (STICCR) Study (1985)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Space Infrared Telescope Facility (SIRTF) is a long-life cryogenically cooled space-based telescope for infrared astronomy from 2 to 700 micrometers. SIRTF is currently under study by NASA-ARC (Reference AP) and planned for launch in approximately the mid 1990s. SIRTF will operate as a multiuser facility, initially carrying three instruments at the focal plane. It will be cooled to below 2 K by superfluid liquid helium to achieve radiometric sensitivity limited only by the statistical fluctuations in the natural infrared background radiation over most of its spectral range. The lifetime of the mission will be limited by the lifetime of the liquid helium supply, and baseline is currently to be 2 years. The telescope changes required to allow in-space replenishment of the 4,000-L superfluid helium tank was investigated. A preliminary design for the space services equipment was also developed. The impacts of basing the equipment and servicing on the space station were investigated. Space replenishment and changeout of instruments required changes to the telescope design. Preliminary concepts are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-177380 , NAS 1.26:177380 , T-4277
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    NASA TECHNICAL REPORTS
  • 8
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    Stresses and deformations in cross-ply composite tubes subjected to a uniform temperature change: Elasticity and Approximate Solutions (1985)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effects of a uniform temperature change on the stresses and deformations of composite tubes are investigated. The accuracy of an approximate solution based on the principle of complementary virtual work is determined. Interest centers on tube response away from the ends and so a planar elasticity approach is used. For the approximate solution a piecewise linear variation of stresses with the radial coordinate is assumed. The results from the approximate solution are compared with the elasticity solution. The stress predictions agree well, particularly peak interlaminar stresses. Surprisingly, the axial deformations also agree well. This, despite the fact that the deformations predicted by the approximate solution do not satisfy the interface displacement continuity conditions required by the elasticity solution. The study shows that the axial thermal expansion coefficient of tubes with a specific number of axial and circumferential layers depends on the stacking sequence. This is in contrast to classical lamination theory which predicts the expansion to be independent of the stacking arrangement. As expected, the sign and magnitude of the peak interlaminar stresses depends on stacking sequence.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-176147 , NAS 1.26:176147 , COMS-85-06 , VPI-E-85-15 , IR-51
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    NASA TECHNICAL REPORTS
  • 9
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    Shear-strain contours from moire interferometry (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The development of whole-field contour maps of shear strains gamma (xy), derived from displacement fields obtained by moire interferometry with 2400 lines/mm, is described. The use of mechanical differentiation to obtain cross-derivatives of displacements and the use of graphical additive moire to sum the cross-derivatives are explained. Quantitative analysis in the small-strain domain is possible because of the high sensitivity of moire interferometry. The applicability of this technique is shown by the testing of a short epoxy beam under three-point bending.
    Keywords: STRUCTURAL MECHANICS
    Type: Experimental Mechanics (ISSN 0014-4851); 25; 282-287
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  • 10
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    ENVIROSAT-2000 report: Federal agency satellite requirements (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The requirement of Federal agencies, other than NOAA, for the data and services of civil operational environmental satellites (both polar orbiting and geostationary) are summarized. Agency plans for taking advantage of proposed future Earth sensing space systems, domestic and foreign, are cited also. Current data uses and future requirements are addressed as identified by each agency.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-88752 , NAS 1.15:88752
    Format: application/pdf
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