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  • Other Sources  (376)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (207)
  • ASTRONAUTICS (GENERAL)  (169)
  • Geoelektrik
  • Pendel
  • ddc:300
  • 2015-2019
  • 1980-1984
  • 1975-1979  (376)
  • 1976  (376)
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  • Other Sources  (376)
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  • 2015-2019
  • 1980-1984
  • 1975-1979  (376)
Year
  • 1
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    Progress Report on Project Mercury (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Progress on Project Mercury, program for manned orbital space flight, is briefly reviewed. The original aims and concepts of the project are recounted. Various types of launch apparatus are mentioned along with safety factors.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Collected Works of Charles J. Donlan; 6 p
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  • 2
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    Guidelines for advanced manned space vehicle program, June 1960 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: A very broad mission objective was established; i.e., manned circumlunar flight and return to earth. It is implicit that the Saturn will be the primary propulsion system for this mission. The following attempts to: (1) define the objective so as to achieve as much capability in the vehicle as possible; (2) draw on Mercury experience to provide broad guidelines for vehicle performance and safety; (3) provide flexibility in the vehicle capability in the event that the manned lunar mission is proved to be subject to unacceptable risk in the target time period; and (4) indicate problem areas where work appears to be particularly needed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Collected Works of Charles J. Donlan; 66 p
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  • 3
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    Zero-G processing of magnets experiment MA-070 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Solidification of magnetic materials in the low gravity orbital environment was studied. The magnetic compounds under study, manganese bismuth and copper cobalt cerium ((Cu, Co)5Ce), both have the potential for the development of high coercive strength. Preliminary results indicate that static fluid configurations, in the absence of the gravitational body force, differ substantially from the documented terrestrial behavior. Chemical homogeneity is substantially enhanced on a macroscopic and microscopic level. Single crystal matrices have been grown in the coordinated growth regions of the flight samples. Primary crystals one order of magnitude greater than those grown terrestrially have been noted and are limited in size by the ampoule dimensions.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Lyndon B. Johnson Space Center Apollo-Soyuz Test Project; 13 p
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  • 4
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    An application of modern control theory to an elastic spacecraft (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Results are presented to illustrate the application of established procedures of linear, quadratic, Gaussian optimal estimation and control to a spacecraft with dynamically significant elastic appendages. Interpretations are provided in both time domain and frequency domain, and conclusions are drawn for a wide class of problems of flexible spacecraft attitude control.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Dyn. and Control of Non-rigid Space Vehicles; 5 p
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  • 5
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    Cometary nucleus release experiments and ice physics (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Some physical and chemical processes involved in the evaporation and sublimation of mixtures of frozen gases are discussed. Effects of zero gravity, vacuum, and solar radiation are emphasized. Relevant experiments that can be carried out with the aid of the space shuttle are proposed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Proc. of the Shuttle-Based Cometary Sci. Workshop; p 137-141
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  • 6
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    Simulation of a cometary conglomerate of frozen gases and dust in a zero-gravity environment: A critical evaluation of possible space experiments (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: It is proposed to use the Shuttle (OFT experiments) or eventually Spacelab to study, in the absence of gravity the low velocity accretion and the bulk properties of icy conglomerates simulating cometary material and their sedimentation and bulk properties in very small acceleration fields. Their behavior when exposed to the direct solar flux is also under consideration.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Proc. of the Shuttle-Based Cometary Sci. Workshop; p 99-117
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  • 7
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    Space shuttle opportunities for cometary research (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The different modes of cometary investigation offered by the shuttle are reviewed. First, there is a mode in which instrumentation for observations of a natural comet is carried to orbit on Spacelab. Second is a mode in which gaseous or solid material is released from the shuttle to simulate some aspect of cometary physics. Another mode uses the near weightlessness within Spacelab to allow laboratory experiments with materials as they may exist on the surface of a comet nucleus.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Proc. of the Shuttle-Based Cometary Sci. Workshop; p 5-6
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  • 8
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    Solar photochemistry using the space shuttle (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A continuing source of difficulty in cometary astrophysics is understanding the origin of C2, C3, NH and CO(+) species in comets. An experiment is proposed to investigate these problems by continuously releasing suspected parent gases from the space shuttle and using a dye laser to selectively excite fragments produced as a result of solar photochemical decomposition of the molecules. The backscattered fluorescence is gathered by a telescope, spectrally filtered, and measured as a function of time after the laser pulse.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Proc. of the Shuttle-Based Cometary Sci. Workshop; p 118-136
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  • 9
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    Review comments of shuttle-based cometary experiments (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The experiments considered are in two groups: on-board experiments and overboard experiments. The on-board experiments include the determination of bulk properties and processes (within solids) and observations of exposure panels (near surface phenomena) The overboard experiments consist of analysis of gas/dust shells by observation from the shuttle and observation by sub-satellites. Experimental parameters are discussed with emphasis on work that is unique to low gravity and high vacuum environments.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Proc. of the Shuttle-Based Cometary Sci. Workshop; p 160-166
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  • 10
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    Gasdynamics of the cryogenic cooler of the Nimbus F spacecraft (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: This paper presents a theoretical study of the gasdynamic behavior of the system used to vent methane gas from an open-cycle cryogenic cooler carried on the Nimbus F satellite. The flow of this gas from the cryogen tank to the vent-line exit takes place at very low Reynolds number, and is strongly affected by variations in the tube cross-sectional area, substantial heat addition, and important frictional effects. All three of these factors play a role in determining the choking mass flow. Finite-difference calculations are used to establish the mass flow rates for a range of cryogen temperatures. Finite-difference calculations are also used to determine the flowfield in the plume that results when the vented gas exits from the spacecraft. The momentum-flux distributions within the plume are then used to estimate the torques applied to the spacecraft when the plume impinges on several surfaces near the exit point. These torque estimates compare favorably with flight data.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets; 13; Dec. 197
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  • 11
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    Quantitative determination of zero-gravity effects on crystal growth from the melt (experiment MA-060) (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The purpose of experiment MA-060 was to investigate quantitatively the effects of near-zero gravity conditions on crystal growth and dopant segregation during directional solidification from the melt. Gallium-doped germanium single crystals were successfully grown from the melt with simultaneous interface demarcation during the Apollo Soyuz Test Project mission. The analysis of the experimental data indicates striking differences of dopant segregation and growth behavior in the presence and absence of gravity. The results obtained are believed to have far-reaching implications on materials processing under zero-gravity conditions and on the theory of crystal growth and segregation in general.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: ESA Mater. Sci. in Space; p 181-187
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  • 12
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    Space processing payload experiment requirements (1976)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: An overview is given of the definition of research requirements and derivation of engineering design requirements for a group of 77 representative applications of space processing. Representative requirements are documented for applied research in space on biological processes, chemical/fluid phenomena, solidification processes, and glass/ceramics processes. Design requirements for payload equipment to accommodate these research requirements are presented in engineering terms, such as power requirements, schematic diagrams, etc. In addition, a summary of the 77 applied research topics is included.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: ESA Mater. Sci. in Space; p 87-113
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  • 13
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    Future earth orbit transportation systems/technology implications (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Assuming Space Shuttle technology to be state-of-the-art, projected technological advances to improve the capabilities of single-stage-to-orbit (SSTO) derivatives are examined. An increase of about 30% in payload performance can be expected from upgrading the present Shuttle system through weight and drag reductions and improvements in the propellants and engines. The ODINEX (Optimal Design Integration Executive Computer Program) program has been used to explore design options. An advanced technology SSTO baseline system derived from ODINEX analysis has a conventional wing-body configuration using LOX/LH engines, three with two-position nozzles with expansion ratios of 40 and 200 and four with fixed nozzles with an expansion ratio of 40. Two assisted-takeoff approaches are under consideration in addition to a concept in which the orbital vehicle takes off empty using airbreathing propulsion and carries out a rendezvous with two large cryogenic tankers carrying propellant at an altitude of 6100 m. Further approaches under examination for propulsion, aerothermodynamic design, and design integration are described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 14; Sept
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  • 14
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    Prediction and measurement of radiation damage to CMOS devices on board spacecraft (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The CMOS Radiation Effects Measurement (CREM) experiment is presently being flown on the Explorer-55, to evaluate device performance in the actual space radiation environment and to correlate the respective measurements to on-the-ground laboratory irradiation results. The experiment contains an assembly of CMOS and P-MOS devices shielded in front over 2 pi steradian by flat slabs of aluminum of 40, 80, 150, and 300 mils (1.02, 2.04, 3.81, and 7.62 mm) thicknesses, and by a practically infinite shield in the back. Initial results from the CREM experiment are reported. Predictions of radiation damage to CMOS devices are based on standard environment models and computational techniques. Measured space damage is smaller than predicted by about a factor of 2-3 for thin shields but agrees well with predictions for thicker shields. It is not clear at this time how the trapped particle environment models or the computational methods should be modified in order to achieve better agreement between experimental results and predicted damage curves.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 15
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    Crystal growth from the vapour phase (ASTP experiment MA-085) (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The positive effects of microgravity on crystal quality and fundamental properties of the vapor transport reaction were established by analyzing the results of three transport experiments on multi-component systems performed during the Apollo Soyuz Test Project (ASTP) mission. The systems employed were GeSe(0.99)Te(0.01) - GeI4 (A), GeS(0.98)Se(0.02) - GeCl4 (B), and GeS - GeCl4-Ar (C). The crystallographic analysis is based on a direct comparison of space and ground-based (prototype) crystals, employing X-ray diffraction, microprobe, microscopic, and chemical etching techniques. The results demonstrate a considerable improvement of the space-grown crystals in terms of chemical and crystalline homogeneity, surface morphology, and bulk perfection relative to ground specimens. The confirmation of greater mass transport rates than predicted for micro-gravity by present vapor transport models is of basic scientific and practical importance for the improvement of transport models and techniques on earth and for the development of a transport model for space conditions. The internal consistency and agreement between ASTP and Skylab results obtained for different compounds, transport agents, and temperature gradients strongly support the validity of these observations. The combined findings of improved crystal quality and high mass transport rates are of technological significance for space-processing applications.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: ESA Mater. Sci. in Space; p 189-206
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  • 16
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    Summary of the pre-ASTP results (1976)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A general overview of materials experiments done on several Apollo missions and Skylab as well as the ground research that led to these experiments is given. Demonstrations of composite solidification, electrophoresis, and fluid flow were developed for Apollo. Fourteen different experiments in metal processing and single crystal growth were done in the space processing facility on Skylab. Metals were melted and solidified in a variety of configurations using different methods of heating to produce improved alloys and composite materials. Single crystals were grown by directional solidification and vapor transport to achieve uniform crystalline perfection, decreased structural defects, and homogeneity of the dopant material.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: ESA Mater. Sci. in Space; p 19-26
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  • 17
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    The Vikings are coming (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The exploration of Mars with the aid of the two Viking landers is discussed. The probable landing date for Viking Lander 1 will be July 4, 1976, and for Lander 2 September 4, 1976. The criteria used in selecting the landing site are considered along with the procedure to be employed in the final approach of the lander to the planet and the touchdown. A description is given of the studies to be conducted by the lander, taking into account the search for life and the collection of meteorological and seismological data. Attention is also given to technical data concerning the spacecraft, details regarding the software, and the ground facilities on earth which are used for the Viking project.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Spectrum; 13; June 197
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  • 18
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    Molecular shield - An orbiting low-density materials laboratory (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Analysis of a molecular shield orbited at 200 km utilizes the kinetic theory of a drifting Maxwellian gas, applied to a hemispherical shell geometry containing internal sources. The molecular shield provides very low gas density conditions for materials experiments at low gravity, while the hemispherical geometry minimizes the internal surface/volume ratio. Deployment of the shield in orbit is described. Contributions to density by shield outgassing, by experiment outgassing, and by interaction with the orbiter are discussed separately. A jettisonable closure plate sealing the hemisphere minimizes any risk of experiment contamination during deployment.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Journal of Vacuum Science and Technology; 13; May-June
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  • 19
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    Developing space occupancy - Perspectives on NASA future space programme planning (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: NASA planning aspects of potential future manned space flight missions are examined and the necessity of long-range planning is pointed out. A listing of desirable future activities is considered, taking into account the permanent occupancy of near-earth orbit space, the permanent occupancy of earth-moon space, the full self-sufficiency of man in geolunar space, and the permanent occupancy of heliocentric space. The technological requirements for the considered activities are discussed, giving attention to transportation, habitation, engineering technology, life sciences, operations technology, and advanced management concepts. A description of future program phasing and advanced studies requirements is also given.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: British Interplanetary Society; vol. 29
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  • 20
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    Estimates of nitric oxide production for lifting spacecraft reentry (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An approximate analysis to estimate the quantity of nitric oxide that could be formed in the wake of a reentering lifting spacecraft is reported. Three different approaches are undertaken: two simplified analytical models utilizing the sudden-freezing concept named the 'trailing-edge-freezing' and 'wake-freezing' approximations, and a computer calculation involving numerical integration of chemical rate equations. The three methods predict a maximum nitric oxide production equivalent to 6, 9.5 and 8% of the mass of the spacecraft, respectively. Thus, the amount of nitric oxide expected to be produced by future space activities is negligibly small compared with that produced by the natural processes.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Atmospheric Environment; 10; 4, 19; 1976
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  • 21
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    The capture of lunar materials ejected into deep space (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Lunar Science Inst., Abstracts of Papers Presented at a Special Session of the Seventh Annual Lunar Science Conference on Utilization of Lunar Materials and Expertise for Large Scale Operations in Space; p 162-164
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  • 22
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    Free-fall trajectories from the Moon to the Lagrangian equilibrium points (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Lunar Science Inst., Abstracts of Papers Presented at a Special Session of the Seventh Annual Lunar Science Conference on Utilization of Lunar Materials and Expertise for Large Scale Operations in Space; p 158-159
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  • 23
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    Testing the Shuttle heat-protection armor (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The article deals with the thermal protection system (TPS) designed to keep Space Shuttle structures at 350 F ratings over a wide range of temperatures encountered in orbit, but also during prelaunch, launch, deorbit and re-entry, landing and turnaround. The structure, function, fabrication, and bonding of various types of reusable surface insulation and composite materials are described. Test programs are developed for insulation, seals, and adhesion bonds; leak tests and acoustic fatigue tests are mentioned. Test facilities include arc jets, radiant heaters, furnaces, and heated tunnels. The certification tests to demonstrate TPS reusability, structural integrity, thermal performance, and endurance will include full-scale assembly tests and initial orbital flight tests.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 14; Jan. 197
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  • 24
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    Shuttle-based observations (1976)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Progress in science in relation to the space shuttle is reported. Several studies on the uses of the space shuttle and Spacelab are highlighted. A review of the activities of the Shuttle Spacelab Payloads Project Office are presented. The activities cover such fields as solar physics, astronomy with optical instruments, high energy astrophysics, atmospheric research and magnetospheric physics, and Earth observational studies.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Proc. of the Shuttle-Based Cometary Sci. Workshop; p 193-197
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  • 25
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    Spectroscopy of small cometary particles (1976)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Knowledge of chemical composition derived from the spectroscopy of small cometary meteoroids when they enter the Earth's atmosphere at high velocity and become visible as meteors is briefly summarized. For statistically reliable results it is necessary to have a large number of observations and this requires the photography of relatively faint meteors, which are considerably more numerous than the bright fireballs. The improvement in observational techniques and cameras has made it possible to extend the range of spectrographic data from cometary particles of mass between a kilogram and a gram down to those of only 0.01 or 0.001 grams in mass. The corresponding increase in the number-value of the statistics was from less than 100 data points to several 1000.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Proc. of the Shuttle-Based Cometary Sci. Workshop; p 150-159
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  • 26
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    A scheme for transport of lunar materials to utilization sites in Earth orbit (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Lunar Science Inst., Abstracts of Papers Presented at a Special Session of the Seventh Annual Lunar Science Conference on Utilization of Lunar Materials and Expertise for Large Scale Operations in Space; p 165-172
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  • 27
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    A way to compare costs of building rotating structures in space (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Lunar Science Inst., Abstracts of Papers Presented at a Special Session of the Seventh Annual Lunar Science Conference on Utilization of Lunar Materials and Expertise for Large Scale Operations in Space; p 116-119
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  • 28
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    Space shuttle digital flight control system (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The space shuttle digital, fly by wire, flight control system presents an interesting challenge in avionics system design. In residence in each of four redundant general purpose computers at lift off are the guidance, navigation, and control algorithms for the entire flight. The mission is divided into several flight segments: first stage ascent, second stage ascent; abort to launch site, abort once around; on orbit operations, entry, terminal area energy management; and approach and landing. The FCS is complicated in that it must perform the functions to fly the shuttle as a boost vehicle, as a spacecraft, as a reentry vehicle, and as a conventional aircraft. The crew is provided with both manual and automatic modes of operations in all flight phases including touchdown and rollout.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Advanced Control Technol. and its Potential for Future Transport Aircraft; p 271-294
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  • 29
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    Viking GC/MS mechanisms design and performance (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Viking Lander gas chromatograph/mass spectrometer will analyze pyrolyzed samples of the Martian surface for organic content. The surface-sample loader and pyrolyzer assembly (SSPLA) is described, along with the major problems encountered during design and testing. Three mechanisms were developed to implement the required SSLPA functions: (1) a soil loader that forces soil from a filled rotating funnel into each of three ovens located on a carriage, (2) a Geneva drive for rotating and precisely indexing the ovens to receive sample, and (3) a toggle-clamp mechanism for sealing the ovens by forcing circular double knife edges into gold sealing surfaces.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL 10th Aerospace Mech. Symp.; p 208-217
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  • 30
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    High stability deployable boom (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Meaningful magnetic field vector measurements in space require accurate placement of a magnetometer beyond the magnetic fields of a spacecraft. The design and development of a deployable boom is described which ensures accurate deployment of an instrument package and maintains high stability after extension.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL 10th Aerospace Mech. Symp.; p 143-154
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  • 31
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    The Helios experiment 5 antenna mechanism (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Experiment 5 Antenna deployment problem onboard Helios A, the failure analysis, and changes in design, test, and operation which led to a successful deployment of both antennas during the early Helios B mission phase are described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL 10th Aerospace Mech. Symp.; p 133-142
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  • 32
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    Caging Mechanism for a drag-free satellite position sensor (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A disturbance compensation system for satellites based on the drag-free concept was mechanized and flown, using a spherical proof mass and a cam-guided caging mechanism. The caging mechanism controls the location of the proof mass for testing and constrains it during launch. Design requirements, design details, and hardware are described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL 10th Aerospace Mech. Symp.; p 125-132
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  • 33
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    Pin puller impact shock attenuation (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Design of a pin arresting mechanism for a pyrotechnically actuated pin puller is reviewed. The investigative approach is discussed and the impact shock test results for various candidate designs are presented. The selected pin arresting design reduced the peak value of the shock response spectrum by five to one.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL 10th Aerospace Mech. Symp.; p 71-79
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  • 34
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    The Helios mechanical despin drive assembly for the high-gain antenna reflector (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Helios is the German-American solar probe which comes within 0.31 Astronomical Units of the sun. A special thermal design and a dry lubrication system have resulted in successful operation up to now, with Helios having finished its first orbit around the sun.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL 10th Aerospace Mech. Symp.; p 80-89
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  • 35
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    Apollo-Soyuz test project docking system (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The United States and Soviet Union in July 1975 successfully completed a joint space mission utilizing each country's spacecraft and the compatible docking system designed and fabricated by each country. The compatible docking system is described, along with the extensive research, development, and testing leading up to the successful mission. It also describes the formulation and implementation of methods for breaking the language barrier, bridging the extensive distances for communication and travel, and adjusting to each country's different culture during the three-year development program.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL 10th Aerospace Mech. Symp.; p 26-37
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  • 36
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    Life Science Payloads Planning Study Integration Facility Survey: Executive Summary (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analyses of proposed life science shuttle era payload operations are discussed. A summary of results from a survey conducted to: (1) examine facility and equipment resources needed for life science payload integration, checkout, test and mission support activities; (2) identify presently available resources; and (3) determine methods by which operational era status may be implemented based on currently available resources, is presented.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-160391 , MDC-G6579
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  • 37
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    Life science payloads planning study integration facility survey results (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The integration facility survey effort described is structured to examine the facility resources needed to conduct life science payload (LSP) integration checkout activities at NASA-JSC. The LSP integration facility operations and functions are defined along with the LSP requirements for facility design. A description of available JSC life science facilities is presented and a comparison of accommodations versus requirements is reported.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-160390 , MDC-G6275
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  • 38
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    Dust content and particle release experiments (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Since dust particles are carried away from a comet nucleus by sublimating ices the effects from the ambient Earth's atmosphere on shuttle-based simulation experiments at lower altitudes are of the same concern to the studies of the dust behavior as they are to the investigation of the volatile component. Also, since the experimental modeling could realistically be performed on a linear scale that is at least three orders of magnitude smaller than required by the true conditions in comets, severe problems of extrapolation may arise in the interpretation of some of the simulation results. Subject to these limitations, future dust-release experiments made on artificial comets could prove fruitful, as they would test the correctness of the understanding of the fundamental properties of the dust emission mechanism in comets, and at the same time insight into the behavior of dust particles after expulsion would be gained.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Proc. of the Shuttle-Based Cometary Sci. Workshop; p 142-149
    Format: text
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  • 39
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    Abort Region Determinator (ARD) module feasibility report. Mission planning, mission analysis and software formulation (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A detailed performance evaluation of the Abort Region Determinator (ARD) module design was provided in support of OFT-1 ascent and OFT-1 intact launch aborts. The evaluation method used compared ARD results against results obtained using the full-up Space Vehicle Dynamic Simulations program under the same conditions. Results were presented for each of the three major ARD math models: (1) the ascent numerical integrator; (2) the mass model, and (3) the second stage predictor as well as the total ARD module. These results demonstrate that the baselined ARD module meets all design objectives for mission control center orbital flight test launch/abort support.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-151580 , HAD-1.4-274 , REPT-1.4-4-33
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  • 40
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    Laser driven light sails: An examination of the possibilities for interstellar probes and other missions (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical discussion of high energy laser propelled light sails is presented. Selection of sail materials, interstellar drag forces, beam pointing, flight velocity, probe mass, and radiation shielding are among the factors discussed. Interstellar probe missions and colonization of the solar system via the light sail are considered.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-157362 , WJSA-76-26
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  • 41
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    Space station systems analysis study, program review (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Mission selection, operational solar power, and public service platform of the space station systems analysis study program are included.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-150764
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  • 42
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    Low fluxes of X-rays (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytic and experimental investigations of the interactions of high-energy protons with spacecraft materials and light nucleus atoms were conducted. Irradiation of typical materials for scintillation detectors using accelerator-produced energetic protons and associated theoretical calculations indicate activity within detectors produced by this mechanism is significant to detection of low-level cosmic gamma radiation. Samples of several materials were flown aboard Skylab to obtain measures of the neutron and proton flux environment. Extremely weak activity was produced in the samples. Calculations of interactions of intermediate-energy protons with light nuclei were performed and a more complete theoretical model programmed for digital computation. Preliminary results appear promising for calculating products of such interactions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-149984 , MS-MSFC-1975
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  • 43
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    Advanced space system concepts and their orbital support needs (1980 - 2000). Volume 3: Detailed data. Part 1: Catalog of initiatives, functional options, and future environments and goals (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The following areas were discussed in relation to a study of the commonality of space vehicle applications to future national needs: (1) index of initiatives (civilian observation, communication, support), brief illustrated description of each initiative, time periods (from 1980 to 2000+) for implementation of these initiatives; (2) data bank of functional system options, presented in the form of data sheets, one for each of the major functions, with the system option for near-term, midterm, and far-term space projects applicable to each subcategory of functions to be fulfilled; (3) table relating initiatives and desired goals (public service and humanistic, materialistic, scientific and intellectual); and (4) data on size, weight and cost estimations.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-148710 , ATR-76(7365)-1-VOL-3-PT-1
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  • 44
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    Advanced space system concepts and their orbital support needs (1980 - 2000). Volume 4: Detailed data. Part 2: Program plans and common support needs (a study of the commonality of space vehicle applications to future national needs (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The methodology of alternate world future scenarios is utilized for selecting a plausible, though not advocated, set of future scenarios each of which results in a program plan appropriate for the respective environment. Each such program plan gives rise to different building block and technology requirements, which are analyzed for common need between the NASA and the DoD for each of the alternate world scenarios. An essentially invariant set of system, building block, and technology development plans is presented at the conclusion, intended to allow protection of most of the options for system concepts regardless of what the actual future world environment turns out to be. Thus, building block and technology needs are derived which support: (1) each specific world scenario; (2) all the world scenarios identified in this study; or (3) generalized scenarios applicable to almost any future environment. The output included in this volume consists of the building blocks, i.e.: transportation vehicles, orbital support vehicles, and orbital support facilities; the technology required to support the program plans; identification of their features which could support the DoD and NASA in common; and a complete discussion of the planning methodology.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-148708 , ATR-76(7365)-1-VOL-4-PT-2
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  • 45
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    Atmospheric cloud physics laboratory project study (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Engineering studies were performed for the Zero-G Cloud Physics Experiment liquid cooling and air pressure control systems. A total of four concepts for the liquid cooling system was evaluated, two of which were found to closely approach the systems requirements. Thermal insulation requirements, system hardware, and control sensor locations were established. The reservoir sizes and initial temperatures were defined as well as system power requirements. In the study of the pressure control system, fluid analyses by the Atmospheric Cloud Physics Laboratory were performed to determine flow characteristics of various orifice sizes, vacuum pump adequacy, and control systems performance. System parameters predicted in these analyses as a function of time include the following for various orifice sizes: (1) chamber and vacuum pump mass flow rates, (2) the number of valve openings or closures, (3) the maximum cloud chamber pressure deviation from the allowable, and (4) cloud chamber and accumulator pressure.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-149956
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  • 46
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    A Nestable Tapered Column Concept for Large Space Structures (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A structural element concept is described which permits achievement of weight critical payloads for space shuttle. These columns are highly efficient structural members which could be the basic building elements for very large, space truss structures. Parametric results are presented which show that untapered cylindrical columns result in volume limited payloads on the space shuttle and that nestable, tapered columns easily eliminate this problem. It is recognized that the tapered column concept belongs to a class of structures which must be assembled in orbit. However, analytical results are presented which indicate that the gain in the amount of structure placed in orbit per launch, is great enough that such a concept should be considered in future systems studies of very large space structures.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-73927
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  • 47
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    Failure rate analysis of Goddard Space Flight Center spacecraft performance during orbital life (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Space life performance data on 57 Goddard Space Flight Center spacecraft are analyzed from the standpoint of determining an appropriate reliability model and the associated reliability parameters. Data from published NASA reports, which cover the space performance of GSFC spacecraft launched in the 1960-1970 decade, form the basis of the analyses. The results of the analyses show that the time distribution of 449 malfunctions, of which 248 were classified as failures (not necessarily catastrophic), follow a reliability growth pattern that can be described with either the Duane model or a Weibull distribution. The advantages of both mathematical models are used in order to: identify space failure rates, observe chronological trends, and compare failure rates with those experienced during the prelaunch environmental tests of the flight model spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TN-D-8272 , G-7681
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  • 48
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    An investigation to determine the pressure distribution on the 0.0137 scale solid rocket booster forebody (MSFC model 467) at angles of attack at or near 90 deg and high Reynolds numbers in the MSFC High Reynolds Number Wind Tunnel (SA29F) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An aerodynamic investigation was conducted in the MSFC High Reynolds Number Wind Tunnel to determine the pressure distribution over the foresection of the current 146 inch diameter shuttle SRB. The test model consisted of a 0.0137 scale version of the SRB nose cone and a forward portion of the cylindrical body which was approximately 2.7 calibers in length. The pressure distributions are plotted as a function of longitudinal station ratioed to body diameter and circumferential location for each angle of attack and Mach number. A Reynolds number variation study was made for Mach numbers of 0.4 and 0.6 at an angle of attack of 270 deg and roll angle of 180 deg.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147608 , DMS-DR-2207
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  • 49
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    Transonic-supersonic high Reynolds number stability and control characteristics of a 0.015-scale (remotely controlled elevon) model 44-0 of the space shuttle orbiter tested in the VSD high speed wind tunnel (LA67) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A detailed aerodynamic data base which can be used to substantiate the aerodynamic design data book for the current shuttle orbiter configuration was generated. Special attention was directed to definition of non-linear aerodynamic characteristics by taking data at small increments in the angle of attack, angle of sideslip, Mach number, and elevon position. Six-component aerodynamic force and moment and elevon position data were recorded over an angle-of-attack range from -2 deg to as high as 32 deg at angles of sideslip of 0 deg, 1 deg, and +2 deg. The test Mach numbers were 0.60, 0.80, 0.90, 1.2, 1.5, 2.0, 3.0, and 4.6. The effects of Reynolds number were investigated and covered a range from 5.0 to 16.0 million per foot.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144607 , DMS-DR-2266
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  • 50
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    Force test of a 0.88 percent scale 142-inch diameter solid rocket booster (MSFC model number 461) in the NASA/MSFC high Reynolds number wind tunnel (SA13F) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented of a force test of a .88 percent scale model of the 142 inch solid rocket booster without protuberances, conducted in the MSFC high Reynolds number wind tunnel. The objective of this test was to obtain aerodynamic force data over a large range of Reynolds numbers. The test was conducted over a Mach number range from 0.4 to 3.5. Reynolds numbers based on model diameter (1.25 inches) ranged from .75 million to 13.5 million. The angle of attack range was from 35 to 145 degrees.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144617 , DMS-DR-2277
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  • 51
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    Centaur D-1A nose fairing jettison test (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted to verify the functional and structural capability of the Centaur D-1A nose fairing. A full-scale flight-type nose fairing was jettisoned at the Lewis Research Center Space Power Chamber at simulated altitude. Two complete jettisons of the nose fairing were performed, one without aft helper springs and one with aft helper springs. A ''static'' rotation test was also performed to verify capability of the helper springs and to allow clearance measurements between the nose fairing and spacecraft envelope mock-up at certain discrete nose fairing rotation angles. Nose fairing trajectories, structural deflections, clearances, and hinge forces during jettison are presented. Data from subsequent Centaur D-1A flights, relative to nose fairing jettisons, are compared with the experimental results.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-73450 , E-8808
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  • 52
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    High supersonic stability and control characteristics of a 0.015-scale (remotely controlled elevon) model 49-0 of the space shuttle orbiter tested in the NASA/LaRC 4-foot UPWT (LEG 2) (LA63B) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The model tested was a Langley-built 0.015-scale SSV Orbiter model with remote independently operated left and right elevon surfaces. The objective of the test was to generate a detailed aerodynamic data base for the current Shuttle Orbiter Configuration. Special attention was directed to definition of nonlinear aerodynamic characteristics by taking data at small increments, angle of attack, angle of sideslip, and elevon position. Six-component aerodynamic force and moment and elevon position data were recorded over an angle-of-attack range from -4 deg to 45 deg, at angles of sideslip of 0 deg, + or - 2 deg, and + or - 4 deg. Additional tests were made over an angle of sideslip range from -6 deg to 8 deg at selected angles of attack. The test Mach numbers were 2.86, 3.90, and 4.60 with Reynolds number held at a constant two million per foot.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144606 , DMS-DR-2279
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  • 53
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    Magnetic bearing reaction wheel (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a program for the development, fabrication and functional test of an engineering model magnetically suspended reaction wheel are described. The reaction wheel develops an angular momentum of + or - 0.5 foot-pound-second and is intended for eventual application in the attitude control of long-life interplanetary and orbiting spacecraft. A description of the wheel design and its major performance characteristics is presented. Recommendations for flight prototype development are made.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-148315 , PUBL-71-0853-00-00
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  • 54
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    Aeroheating (pressure) characteristics on a 0.010-scale version of the vehicle 3 space shuttle configuration (26-OTS) in the Langley Research Center 4-foot wind tunnel (IH4) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-27333.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144611 , DMS-DR-2138-VOL-4
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  • 55
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    Aeroheating (pressure) characteristics on a 0.010-scale version of the vehicle 3 space shuttle configuration (26-OTS) in Langley Research Center 4-foot wind tunnel (IH4) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-27333.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144610 , DMS-DR-2138-VOL-3
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  • 56
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    Aeroheating (pressure) characteristics on a 0.10-scale version of the vehicle 3 space shuttle configuration (26-OTS) in the Langley Research Center 4-foot wind tunnel (IH4) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of wind tunnel tests, conducted at the Langley Research Center Unitary Plan Wind Tunnel, are presented. The model tested was an 0.010-scale version of the Vehicle 3 Space Shuttle Configuration. Pressure measurements were made on the launch configuration, Orbiter alone, external tank alone, and solid rocket booster alone, to provide heat transfer pressure data. The tests were conducted for a Mach number range from 2.36 to 4.6 and Reynolds number range from 1.2 to 5 million per foot. The model was tested at angles of attack from -10 to 20 deg for a sideslip angle range from -5 to +5 deg, and at sideslip angles from -5 to 48 deg for 0 deg angle of attack. Tabulated data are given and photographs of the test configuration are shown.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144609 , DMS-DR-2138-VOL-2
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  • 57
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    Results of test MA22 in the NASA/LaRC 31-inch CFHT on an 0.010-scale model (32-0) of the space shuttle configuration 3 to determine RCS jet flow field interaction, volume 4 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-27329.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147607 , DMS-DR-2267-VOL-4
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  • 58
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    Results of test MA22 in the NASA/LaRC 31-inch CFHT on an 0.010-scale model (32-0) of the space shuttle configuration 3 to determine RCS jet flow field interaction, volume 3 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-27329.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147606 , DMS-DR-2267-VOL-3
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  • 59
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    Results of test MA22 in the NASA/LaRC 31-inch CFHT on an 0.010-scale model (32-0) of the space shuttle configuration 3 to determine RCS jet flow field interaction, volume 2 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-27329.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147605 , DMS-DR-2267-VOL-2
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  • 60
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    Results of test MA22 in the NASA/LaRC 31-inch CFHT on an 0.010-scale model (32-0) of the space shuttle configuration 3 to determine RCS jet flow field interaction, volume 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind tunnel test was conducted in the Langley Research Center 31-inch Continuous Flow Hypersonic Wind Tunnel from May 6, 1975 through June 3, 1975. The primary objectives of this test were the following: (1) to study the ability of the wind tunnel to repeat, on a run-to-run basis, data taken for identical configurations to determine if errors in repeatability could have a significant effect on jet interaction data, (2) to determine the effect of aerodynamic heating of the scale model on jet interaction, (3) to investigate the effects of elevon and body flap deflections on jet interaction, (4) to determine if the effects from jets fired separately along different axes can be added to equal the effects of the jets fired simultaneously (super position effects), (5) to study multiple jet effects, and (6) to investigate area ratio effects, i.e., the effect on jet interaction measurements of using wind tunnel nozzles with different area ratios in the same location. The model used in the test was a .010-scale model of the Space Shuttle Orbiter Configuration 3. The test was conducted at Mach 10.3 and a dynamic pressure of 150 psf. RCS chamber pressure was varied to simulate free flight dynamic pressures of 5, 7.5, 10, and 20 psf.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147604 , DMS-DR-2267-VOL-1
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  • 61
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    Thermal and convection analyses of the dendrite remelting rocket experiment; Experiment 74-21 in the space processing rocket program (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Dendrite Remelting Rocket Experiment was performed aboard a Black Brant VC Sounding Rocket during a period which gravity levels of approximately 0.00001 g prevailed. The experiment consisted of cooling an aqueous ammonium chloride solution in a manner such that crystallization of ammonium chloride crystals proceeded throughout a three minute period of zero-g. The crystallization process during flight was recorded on 35 mm panatomic-x film. A number of ground crystallizations were similarly recorded for comparison purposes. The convective and thermal conditions in aqueous and metallic liquid systems were assessed under conditions of the flight experiment to help establish the relevance of the rocket experiment to metals casting phenomena. The results indicate that aqueous or metallic convective velocities in the Dendrite Remelting Rocket Experiment cell are of insignificant magnitudes at the 0.0001 to 0.00001 g levels of the experiment. The crystallization phenomena observed in the Rocket Experiment, therefore, may be indicative of how metals will solidify in low-g.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-149920 , LMSC-HREC-TR-D496847
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  • 62
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    Multi-star processing and gyro filtering for the video inertial pointing system (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The video inertial pointing (VIP) system is being developed to satisfy the acquisition and pointing requirements of astronomical telescopes. The VIP system uses a single video sensor to provide star position information that can be used to generate three-axis pointing error signals (multi-star processing) and for input to a cathode ray tube (CRT) display of the star field. The pointing error signals are used to update the telescope's gyro stabilization system (gyro filtering). The CRT display facilitates target acquisition and positioning of the telescope by a remote operator. Linearized small angle equations are used for the multistar processing and a consideration of error performance and singularities lead to star pair location restrictions and equation selection criteria. A discrete steady-state Kalman filter which uses the integration of the gyros is developed and analyzed. The filter includes unit time delays representing asynchronous operations of the VIP microprocessor and video sensor. A digital simulation of a typical gyro stabilized gimbal is developed and used to validate the approach to the gyro filtering.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-73130 , A-6595
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  • 63
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    Environmental charging of spacecraft-tests of thermal control materials for use on the global positioning system flight space vehicle. Part 2: Specimen 6 to 9 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The NASA/USAF program on the Environmental Charging of Spacecraft Surfaces consists, in part, of experimental efforts directed toward evaluating the response of materials to the environmental charged particle flux. Samples of thermal blankets of the type to be used on the Global Positioning System Flight Space Vehicles were tested to determine their response to electron flux. The primary result observed was that no discharges were obtained with the quartz-fiber-fabric-covered multilayer insulation specimen. The taped aluminized polyester grounding system used on all specimens did not appear to grossly deteriorate with time; however, the specimens require specific external pressure to maintain constant grounding system resistance.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-73436 , E-8789
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  • 64
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    Apollo experience report environmental acceptance testing (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Environmental acceptance testing was used extensively to screen selected spacecraft hardware for workmanship defects and manufacturing flaws. The minimum acceptance levels and durations and methods for their establishment are described. Component selection and test monitoring, as well as test implementation requirements, are included. Apollo spacecraft environmental acceptance test results are summarized, and recommendations for future programs are presented.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-TN-D-8271 , JSC-S-458
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  • 65
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    Apollo experience report guidance and control systems (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Apollo guidance and control systems for both the command module and the lunar module are described in a summary report. General functional requirements are discussed, and general functional descriptions of the various subsystems and their interfaces are provided. The differences between the original in-flight maintenance concept and the final lunar-orbital-rendezvous concept are discussed, and the background in philosophy, the system development, and the reasons for the change in concept are chronologically presented. Block diagrams showing the command module guidance and control system under each concept are included. Significant conclusions and recommendations contained in more detailed reports on specific areas of the guidance and control systems are included.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-TN-D-8249 , JSC-S-418
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  • 66
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    Phase B: Final definition and preliminary design study for the initial Atmospheric Cloud Physics Laboratory (ACPL): A Spacelab mission payload (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A program outline is presented. Emphasis is placed on the definition and preliminary design of the laboratory to provide a firm basis for subsequent hardware development, production, and operation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144170
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  • 67
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    Results of an experimental investigation to determine separation characteristics for the Orbiter/747 using a 0.0125-scale model (48-0 AX1318I-1 747) in the Ames Research Center 14-foot wind tunnel (CA23B) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aerodynamic separation data obtained from a wind tunnel test of an 0.0125-scale SSV Orbiter model of a VC70-000002 Configuration and a 0.0125-scale 747 model was presented. Separation data was obtained at a Mach number of 0.6 and three incidence angles of 4, 6, and 8 degrees. The orbiter angle of attack was varied from 0 to 14 degrees. Longitudinal, lateral and normal separation increments were obtained for fixed 747 angles of attack of 0, 2, and 4 degrees while varying the orbiter angle of attack. Control surface settings on the 747 carrier included rudder deflections of 0 and 10 degrees and horizontal stabilizer deflections of -1 and +5 degrees.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144604 , DMS-DR-2275-VOL-2
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  • 68
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    Results of an experimental investigation to determine separation characteristics for the Orbiter/747 using a 0.0125-scale model (48-0 AX1318I-1 747) in the Ames Research center 14-foot wind tunnel (CA23B), volume 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Separation data were obtained at a Mach number of 0.6 and three incidence angles of 4 deg, 6 deg, and 9 deg. The orbiter angle of attack was varied from 0 to 14 degrees. Longitudinal, lateral and normal separation increments were obtained for fixed 747 angles of attack of 0 deg, 2 deg, and 4 deg while varying orbiter angle of attack. Control surface settings on the 747 carrier included rudder deflections of 0 deg and 10 deg and horizontal stabilizer deflections of -1 deg and +5 deg. Photographs of tested configurations are shown.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144603 , DMS-DR-2275-VOL-1
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  • 69
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    Unsteady aerodynamic flow field analysis of the space shuttle configuration. Part 4: 747/orbiter aeroelastic stability (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A quasi-steady analysis of the aeroelastic stability of the lateral (antisymmetric) modes of the 747/orbiter vehicle was accomplished. The interference effect of the orbiter wake on the 747 tail furnishes an aerodynamic undamping contribution to the elastic modes. Likewise, the upstream influence of the 747 tail and aft fuselage on the orbiter beaver-tail rail fairing also is undamping. Fortunately these undamping effects cannot overpower the large damping contribution of the 747 tail and the modes are damped for the configurations analyzed. However, significant interference effects of the orbiter on the 747 tail have been observed in the pitch plane. The high response of the 747 vertical tail in the orbiter wave was also considered. Wind tunnel data points to flapping of the OMS pod wakes as the source of the wake resonance phenomenon.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144335 , LMSC-D057194-PT-4
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  • 70
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    Unsteady aerodynamic flow field analysis of the space shuttle configuration. Part 3: Unsteady aerodynamics of bodies with concave nose geometries (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis of the unsteady aerodynamics of bodies with concave nose geometries was performed. The results show that the experimentally observed pulsating flow on spiked bodies and in forward facing cavities can be described by the developed simple mathematical model of the phenomenon. Static experimental data is used as a basis for determination of the oscillatory frequency of spike-induced flow pulsations. The agreement between predicted and measured reduced frequencies is generally very good. The spiked-body mathematical model is extended to describe the pulsations observed in forward facing cavities and it is shown that not only the frequency but also the pressure time history can be described with the accuracy needed to predict the experimentally observed time average effects. This implies that it should be possible to determine analytically the impact of the flow pulsation on the structural integrity of the nozzles for the jettisoned empty SRM-shells.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144334 , LMSC-D057194-PT-3
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  • 71
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    Unsteady aerodynamic flow field analysis of the space shuttle configuration. Part 2: Launch vehicle aeroelastic analysis (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An exploratory analysis has been made of the aeroelastic stability of the Space Shuttle Launch Configuration, with the objective of defining critical flow phenomena with adverse aeroelastic effects and developing simple analytic means of describing the time-dependent flow-interference effects so that they can be incorporated into a computer program to predict the aeroelastic stability of all free-free modes of the shuttle launch configuration. Three critical flow phenomana have been identified: (1) discontinuous jump of orbiter wing shock, (2) inlet flow between orbiter and booster, and (3) H.O. tank base flow. All involve highly nonlinear and often discontinuous aerodynamics which cause limit cycle oscillations of certain critical modes. Given the appropriate static data, the dynamic effects of the wing shock jump and the HO tank bulbous base effect can be analyzed using the developed quasi-steady techniques. However, further analytic and experimental efforts are required before the dynamic effects of the inlet flow phenomenon can be predicted for the shuttle launch configuration.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144333 , LMSC-D057194-PT-2
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  • 72
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    Response of space shuttle insulation panels to acoustic noise pressure (1976)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The response of reusable space shuttle insulation panels to random acoustic pressure fields are studied. The basic analytical approach in formulating the governing equations of motion uses a Rayleigh-Ritz technique. The input pressure field is modeled as a stationary Gaussian random process for which the cross-spectral density function is known empirically from experimental measurements. The response calculations are performed in both frequency and time domain.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-148201 , FR-2
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  • 73
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    Unsteady aerodynamic flow field analysis of the space shuttle configuration. Part 1: Orbiter aerodynamics (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis of the steady and unsteady aerodynamics of the space shuttle orbiter has been performed. It is shown that slender wing theory can be modified to account for the effect of Mach number and leading edge roundness on both attached and separated flow loads. The orbiter unsteady aerodynamics can be computed by defining two equivalent slender wings, one for attached flow loads and another for the vortex-induced loads. It is found that the orbiter is in the transonic speed region subject to vortex-shock-boundary layer interactions that cause highly nonlinear or discontinuous load changes which can endanger the structural integrity of the orbiter wing and possibly cause snap roll problems. It is presently impossible to simulate these interactions in a wind tunnel test even in the static case. Thus, a well planned combined analytic and experimental approach is needed to solve the problem.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144332 , LMSC-D057194-PT-1
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  • 74
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    Results of an aerodynamic investigation of a space shuttle orbiter/747 carrier flight test configuration to determine separation characteristics utilizing 0.0125-scale models (48-0/AX1318I-1) in the LTV 4 x 4 foot high speed wind tunnel (CA26), volume 5 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see Vol. 1 .
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144616 , DMS-DR-2273-VOL-5
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  • 75
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    Results of an aerodynamic investigation of a space shuttle orbiter/747 carrier flight test configuration to determine separation characteristics utilizing 0.0125-scale models (48-0/AX1318I-1) in the LTV 4 x 4 foot high speed wind tunnel (CA26), volume 4 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see Vol. 1 .
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144615 , DMS-DR-2273-VOL-4
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  • 76
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    Results of an Aerodynamic Investigation of a Space Shuttle Orbiter/747 Carrier Flight Test Configuration to Determine Separation Characteristics Utilizing 0.0125-Scale Models (48-0/AX1318I-1) in the LTV 4 X 4 Foot High Speed Wind Tunnel (CA26), Volume 2 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see Vol. 1 .
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144613 , DMS-DR-2273-VOL-2
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  • 77
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    Results of an aerodynamic investigation of a space shuttle orbiter/747 carrier flight test configuration to determine separation characteristics utilizing 0.0125-scale models (48-0/AX1318I-1) in the LTV 4 x 4-foot high speed wind tunnel (CA26), volume 3 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see Vol. 1 .
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144614 , DMS-DR-2273-VOL-3
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  • 78
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    Results of an aerodynamic investigation of a space shuttle orbiter/747 carrier flight test configuration to determine separation characteristics utilizing 0.0125-scale models (48-0/AX1318I-1) in the LTV 4 x 4 foot high speed wind tunnel (CA26), volume 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of tests conducted on a 0.0125-scale model of the Space Shuttle Orbiter and a 0.0125-scale model of the 747 CAM configuration in a 4 x 4-foot High Speed Wind Tunnel were presented. Force and moment data were obtained for each vehicle separately at a Mach number of 0.6 and for each vehicle in proximity to the other at Mach numbers of 0.3, 0.5, 0.6 and 0.7. The proximity effects of each vehicle on the other at separation distances (from the mated configuration) ranging from 1.5 feet to 75 feet were presented; 747 Carrier angles of attack from 0 deg to 6 deg and angles of sideslip of 0 deg and -5 deg were tested. Model variables included orbiter elevon, aileron and body flap deflections, orbiter tailcone on and off, and 747 stabilizer and rudder deflections.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144612 , DMS-DR-2273-VOL-1
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  • 79
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    Aeroheating (pressure) characteristics on a 0.010-scale version of the vehicle 3 space shuttle configuration (26-OTS) in the Langley Research Center 4-foot wind tunnel (IH4), volume 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of wind tunnel tests conducted on a 0.010-scale version of the Vehicle 3 Space Shuttle Configuration were presented. Pressure measurements were made on the launch configuration, orbiter alone, external tank alone, and solid rocket booster alone, to provide heat transfer pressure data. The tests were conducted for a Mach number range from 2.36 to 4.6 and Reynolds number range from 1.2 to 5 million per foot. The model was tested at angles of attack from -10 deg to 20 deg for a sideslip angle range from -5 deg to +5 deg and at sideslip angles from -5 deg to 48 deg for 0 deg angle of attack.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144608 , DMS-DR-2138-VOL-1
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  • 80
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    Some anomalies observed in wind-tunnel tests of a blunt body at transonic and supersonic speeds (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation of anomalies observed in wind tunnel force tests of a blunt body configuration was conducted at Mach numbers from 0.20 to 1.35 in the Langley 8-foot transonic pressure tunnel and at Mach numbers of 1.50, 1,80, and 2.16 in the Langley Unitary Plan wind tunnel. At a Mach number of 1.35, large variations occurred in axial force coefficient at a given angle of attack. At transonic and low supersonic speeds, the total drag measured in the wind tunnel was much lower than that measured during earlier ballistic range tests. Accurate measurements of total drag for blunt bodies will require the use of models smaller than those tested thus far; however, it appears that accurate forebody drag results can be obtained by using relatively large models. Shock standoff distance is presented from experimental data over the Mach number range from 1.05 to 4.34. Theory accurately predicts the shock standoff distance at Mach numbers up to 1.75.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TN-D-8237 , L-10784
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  • 81
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    Results of an investigation of jet plume effects on an 0.010-scale model (75-OTS) of the space shuttle integrated vehicle in the 9 x 7-foot leg of the NASA/Ames unitary wind tunnel (IA82B), volume 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The base pressure environment was investigated for the first and second stage mated vehicle in a supersonic flow field from Mach 1.55 through 2.20 with simulated rocket engine exhaust plumes. The pressure environment was investigated for the orbiter at various vent port locations at these same freestream conditions. The Mach number environment around the base of the model with rocket plumes simulated was examined. Data were obtained at angles of attack from -4 deg through +4 deg at zero yaw, and at yaw angles from -4 deg through +4 deg at zero angle of attack, with rocket plume sizes varying from smaller than nominal to much greater than nominal. Failed orbiter engine data were also obtained. Elevon hinge moments and wing panel load data were obtained during all runs. Photographs of the tested configurations are shown.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144601 , DMS-DR-2231-VOL-1
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  • 82
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    Zero-gravity growth of NaF-NaCl eutectics in the NASA Skylab program (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Continuous and discontinuous NaF fibers, embedded in a NaCl matrix, were produced in space and on earth. The production of continuous fibers in a eutectic mixture is attributed to the absence of convection current in the liquid during solidification in space. Image transmission and optical transmittance measurements of transverse sections of the space-grown and earth-grown ingots were made with a light microscope and a spectrometer. It is shown that better optical properties were obtained from samples grown in space. This was attributed to a better alignment of NaF fibers along the ingot axis. A new concept is advanced to explain the phenomenon of transmittance versus far infrared wavelength of the directionally solidified NaCl-NaF eutectic in terms of the two-dimensional Bragg Scattering and the polarization effect of Rayleigh scattering. This concept can be applied to other eutectic systems as long as the index of refraction of the matrix over a range of wavelengths is known. Experimental data are in agreement with the theoretical prediction.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-144311 , UCLA-ENG-7609
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  • 83
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    Results of tests in the AEDC VKF Tunnel B using the phase change paint technique on 0.04 scale 50 percent forebody models (82-0) of the Rockwell space shuttle orbiter (OH50A) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Model information and data from wind tunnel tests conducted on 0.04 scale 50 percent forebody models of the Space Shuttle Orbiter were presented. These tests were conducted using the phase change paint technique to determine aerodynamic heating rates due to various proturberances and recessions. Angles of attack from 20 deg through 45 deg were investigated at Mach 8.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144595 , DMS-DR-2285
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  • 84
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    Analysis of structural dynamic data from Skylab. Volume 2: Skylab analytical and test model data (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The orbital configuration test modal data, analytical test correlation modal data, and analytical flight configuration modal data are presented. Tables showing the generalized mass contributions (GMCs) for each of the thirty tests modes are given along with the two dimensional mode shape plots and tables of GMCs for the test correlated analytical modes. The two dimensional mode shape plots for the analytical modes and uncoupled and coupled modes of the orbital flight configuration at three development phases of the model are included.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144286 , MCR-76-179-VOL-2
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  • 85
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    Shuttle payload interface verification equipment study. Volume 3: Specification data (1976)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A complete description is given of the IVE physical and performance design requirements as evolved in this study. The data are presented in a format to facilitate the development of an item specification. Data were used to support the development of the project plan data (schedules, cost, etc.) contained in Volume 4 of this report.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147668 , SD76-SH-0092-VOL-3
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  • 86
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    Shuttle payload interface verification equipment study. Volume 1: Executive summary (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary design analysis of a stand alone payload integration device (IVE) is provided that is capable of verifying payload compatibility in form, fit and function with the shuttle orbiter prior to on-line payload/orbiter operations. The IVE is a high fidelity replica of the orbiter payload accommodations capable of supporting payload functional checkout and mission simulation. A top level payload integration analysis developed detailed functional flow block diagrams of the payload integration process for the broad spectrum of P/L's and identified degree of orbiter data required by the payload user and potential applications of the IVE.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147665 , SD76-SH-0092-VOL-1
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  • 87
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    Results of an investigation of jet plume effects on a 0.010-scale model (75-OTS) of the space shuttle integrated vehicle in the 8 x 7-foot leg of the NASA/Ames unitary wind tunnel (IA82C), volume 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The primary test objective was to define the base pressure environment of the first and second stage mated vehicle in a supersonic flow field from Mach 2.60 through 3.50 with simulated rocket engine exhaust plumes. The secondary objective was to obtain the pressure environment of the Orbiter at various vent port locations at these same freestream conditions. Data were obtained at angles of attack from -4 deg through +4 deg at zero yaw, and at yaw angles from -4 deg through +4 deg at zero angle of attack, with rocket plume sizes varying from smaller than nominal to much greater than nominal. Failed Orbiter engine data were also obtained. Elevon hinge moments and wing panel load data were obtained during all runs. Photographs of test equipment and tested configurations are shown.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144597 , DMS-DR-2219-VOL-1
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  • 88
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    Set covering algorithm, a subprogram of the scheduling algorithm for mission planning and logistic evaluation (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program using Lemke, Salkin and Spielberg's Set Covering Algorithm (SCA) to optimize a traffic model problem in the Scheduling Algorithm for Mission Planning and Logistics Evaluation (SAMPLE) was documented. SCA forms a submodule of SAMPLE and provides for input and output, subroutines, and an interactive feature for performing the optimization and arranging the results in a readily understandable form for output.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-147551 , LEC-6842 , JSC-09950
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  • 89
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    Aerodynamic results of a separation effects test on a 0.010-scale model (52-OTS) of the integrated SSV in the AEDC/VKF 40-by-40 inch supersonic wind tunnel A (IA111), volume 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Graphical data obtained during experimental wind tunnel aerodynamic investigations of a 0.010 scale model (52-OTS) of the integrated space shuttle vehicle was presented. The purpose of this investigation was to obtain data with the solid rocket booster (SRB) in proximity to the orbiter/external tank (O/ET), over a large O/ET initial angle of attack and sideslip range, as well as data on the SRB alone (greatly separated from the O/ET). A captive trajectory system, which supported the SRB, was used with the tunnel primary sector (supporting the O/ET) to obtain grid type separation effects data. One symmetrical SRB model was used interchangeably to obtain right-hand and left-hand SRB data. The entire investigation was conducted at a free-stream Mach number of 4.5 at unit Reynolds number of 3.95 and 5.9 million per foot.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141831 , DMS-DR-2242-VOL-1
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  • 90
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    Thermal support for scale support (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The thermal design work completed for the Thermal Protection System (TPS) of the Space Shuttle System (TPS) of the space shuttle vehicle was documented. This work was divided into three phases, the first two of which reported in previous documents. About 22 separate tasks were completed in phase III, such as: hot gas facility (HGF) support, guarded tank support, shuttle external tank (ET) thermal design handbook support, etc.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144185 , LMSC-HREC-TR-D496704
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  • 91
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    Upper wing surface boundary layer measurements and static aerodynamic data obtained on a 0.015-scale model (42-0) or the SSV orbiter configuration 140A/B in the LTV HSWT at a Mach number of 4.6 (LA58) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The purpose of the test was to investigate the nature of the Orbiter boundary layer characteristics at angles of attack from -4 to 32 degrees at a Mach number of 4.6. The effect of large grit, employed as transition strips, on both the nature of the boundary layer and the force and moment characteristics were investigated along with the effects of large negative elevon deflection on lee side separation. In addition, laminar and turbulent boundary layer separation phenomena which could cause asymmetric flow separation were investigated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144592 , DMS-DR-2215
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  • 92
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    Aerodynamic results of wind tunnel tests on a 0.010-scale model (32-QTS) space shuttle integrated vehicle in the AEDC VKF-40-inch supersonic wind tunnel (IA61) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Plotted and tabulated aerodynamic coefficient data from a wind tunnel test of the integrated space shuttle vehicle are presented. The primary test objective was to determine proximity force and moment data for the orbiter/external tank and solid rocket booster (SRB) with and without separation rockets firing for both single and dual booster runs. Data were obtained at three points (t = 0, 1.25, and 2.0 seconds) on the nominal SRB separation trajectory.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144587 , DMS-DR-2143
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  • 93
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    Preliminary input to the space shuttle reaction control subsystem failure detection and identification software requirements (uncontrolled) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The current baseline method and software implementation of the space shuttle reaction control subsystem failure detection and identification (RCS FDI) system is presented. This algorithm is recommended for conclusion in the redundancy management (RM) module of the space shuttle guidance, navigation, and control system. Supporting software is presented, and recommended for inclusion in the system management (SM) and display and control (D&C) systems. RCS FDI uses data from sensors in the jets, in the manifold isolation valves, and in the RCS fuel and oxidizer storage tanks. A list of jet failures and fuel imbalance warnings is generated for use by the jet selection algorithm of the on-orbit and entry flight control systems, and to inform the crew and ground controllers of RCS failure status. Manifold isolation valve close commands are generated in the event of failed on or leaking jets to prevent loss of large quantities of RCS fuel.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147461 , C-4576
    Format: application/pdf
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  • 94
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    An Evaluation of Reaction Wheel Emitted Vibrations for Large Space Telescope (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Emitted force and torque vibration were measured in three axes for three Sperry reaction wheels. Data were taken for both hard and soft mounts; tests were conducted at constant speeds and during runup-rundown over a 0 to 5000 rpm range. A FSC, 7 ft-lb-sec and HEAO, 30 ft-lb-sec ball bearing reaction wheel and a model magnetic bearing were tested. Data analysis was conducted to identify the principal resonances in the 10 to 120 Hz region. Although some particular phenomena remain unexplained, in general good agreement is attained between the analytical predictions and test data. Predictions were also made of the expected emitted vibrations for an LST sized ball bearing and magnetic bearing reaction wheel using engineering judgment and the test data obtained. Additional tests were also run on the 101H duplex bearing pairs used in the reaction wheel suspension to determine bearing stiffness characteristics in the pre-breakaway zero speed region.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144190 , PUBL-71-0824-00-00
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  • 95
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    Space processing of crystalline materials: A study of known methods of electrical characterization of semiconductors: Bibliography (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A selective bibliography is given on electrical characterization techniques for semiconductors. Emphasis is placed on noncontacting techniques for the standard electrical parameters for monitoring crystal growth in space, preferably in real time with high resolution.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-144187
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  • 96
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    Requirements and capabilities for planetary missions. Venus orbiter imaging radar 1983, volume 3 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two spacecraft will be launched in mid-1983 and inserted into a circular polar orbit around Venus about 6 months later. Elliptical orbits are also under consideration. The objective of the mission is imagery of the planet, at about the 200-m resolution level, with continuous altimetry and topographical studies. Science investigations will determine surface characteristics of the planet, study the surface/atmosphere interactions, and determine Venus' mass distribution. A plausible vehicle is based on a Mariner Jupiter/Saturn derivative; others being considered include a Lunar Polar Orbiter derivative and a Pioneer Venus Orbiter derivative.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-148734 , JPL-SP-43-27-VOL-3
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  • 97
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    Transition heating rates determined on a 0.006 scale space shuttle orbiter model (no. 50-0) in the NASA/LaRC Mach 8 variable density wind tunnel test (OH14) (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Data obtained from wind tunnel tests of an .006-scale space shuttle orbiter model in the 18 in. Variable Density Wind Tunnel are presented. The tests, denoted as OH14, were performed to determine transition heating rates using thin skin thermocouples located at various locations on the space shuttle orbiter. The model was tested at M = 8.0 for a range of Reynolds numbers per foot varying from 1.0 to 10.0 million with angles-of-attack from 20 to 35 degrees incremented by 5 degrees.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147617 , DMS-DR-2117
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  • 98
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    Shuttle model tailcone pressure distribution at low subsonic speeds of a 0.03614-scale model in the NASA/LaRC low-turbulence pressure tunnel (LA81), volume 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted in the NASA/LaRC Low-Turbulence Pressure Tunnel on a 0.03614-scale orbiter model of a 089B configuration with a 139B configuration nose forward of F.S. 500. The tailcone was the TC sub 4 design and was instrumented with eighty-nine pressure orifices. Control surfaces were deflected and three wind tunnel mounting techniques were investigated over an angle-of-attack range from -2 deg to a maximum of 18 deg. In order to determine the sensitivity of the tailcone to changes in Reynolds number, most of the test was made at a Mach number of 0.20 over a Reynolds number range of 2.0 to 10 million per foot. A few runs were made at a Mach number of 0.30 at Reynolds numbers of 4.0, 6.0, and 8 million per foot.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147609 , DMS-DR-2296-VOL-1
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  • 99
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    Extended analysis of Skylab experiment M558 data (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A careful review of the data from Skylab M558 was made in an effort to explain the apparent anomaly of the existence of radial concentration gradients whereas none should bave been observed. The very close modelling of the experimental axial concentration profiles by the unsteady-state one-dimensional solution of Fick's Law of self-diffusion in liquid zinc, and the condition of initial uniform concentration in the radioactive pellet portion of the experimental specimens would have precluded the appearance of such radial concentration gradients. Statistical analyses were used to test the significance of the observed deviation from radial-concentration homogeneity. A student t-distribution test of significance showed that, at 90% or even at 80% level of significance, there were no significant deviations from uniformity in radial concentrations. It was also concluded that the two likely causes of any deviation that existed were the zinc to zinc-65 bonding procedure and surface phenomena such as surface tension and capillary action.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-CR-149958
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  • 100
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    Optimal control of spin stabilized spacecraft with telescoping appendages (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The control of a spin-stabilized spacecraft consisting of a rigid central hub and one or two movable offset telescoping booms (with end masses) is considered. The equations of rotational motion are linearized about either of two desired final states. A control law for the boom and mass position is sought such that a quadratic cost functional involving the weighted components of angular velocity plus the control is minimized when the final time is unspecified and involves the solution of the matrix Riccati algebraic equation. For three-axis control more than one offset boom (orthogonal to each other) is required. For two-axis control with a single boom offset from a symmetrical hub, an analytic solution is obtained; when this system is used for nutation decay the time constant is one order of magnitude smaller than previously achieved using non-optimal control logic. For the general case results are obtained numerically.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Dyn. and Control of Non-rigid Space Vehicles; 12 p
    Format: text
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