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  • SPACE VEHICLES  (1,190)
  • THERMODYNAMICS AND COMBUSTION  (624)
  • 1970-1974  (1,814)
  • 1965-1969
  • 1972  (877)
  • 1971  (937)
Collection
Keywords
Years
  • 1970-1974  (1,814)
  • 1965-1969
Year
  • 1
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    Composite systems utilization for space shuttle structures (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Research and development of composite material systems to show applicability of these materials to shuttle structures and to demonstrate availability through a hardware development program is reported. The various configurations studied and potential areas of composite structures use are described and an outline of ongoing composite programs, complementing the indicated feasible applications, including a typical cost study, is shown. The following composite systems are investigated: Boron filaments with epoxy, polyimide, or aluminum matrix, and graphite filaments with epoxy or polyimide matrix.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 605-644
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  • 2
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    Flight loads and control (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The prediction of flight loads and their potential reduction, using various control logics for the space shuttle vehicles, is very complex. Some factors, not found on previous launch vehicles, that increase the complexity are large lifting surfaces, unsymmetrical structure, unsymmetrical aerodynamics, trajectory control system coupling, and large aeroelastic effects. Discussed are these load producing factors and load reducing techniques. Identification of potential technology areas is included.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 175-203
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  • 3
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    New considerations for pogo prevention on space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Recommendations for improving the methodology of pogo suppression for the space shuttle include: Consideration of inter-pump location for accumulator or active device, inclusion of tank outflow effects in dynamic structural analysis, the use of simplified transfer functions in systems studies, three phase dynamic testing program for turbopump with development of dynamic flowmeters, and the use of a linearized mathematical model for engine physics studies.
    Keywords: SPACE VEHICLES
    Type: NASA, Washington NASA Space Shuttle Technol. Conf.; p 97-116
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  • 4
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    Development of methods for fracture control of space shuttle structures (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The technology with respect to fracture control requirements of the shuttle is considered. The current state-of-the-art does permit an approach based on linear elastic fracture mechanics concepts. Development and implementation of a fracture control plan should recognize deficiencies and provide adequate resources for the extensive empirical test data which are required. With respect to the cost impact of such tests, recent experiences involving advanced aircraft systems have seen unit cost increases of from 200 to 500 percent.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 727-770
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  • 5
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    Ablator manufacturing (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Studies are being conducted to determine how manufacturing-induced defects affect the performance of ablative heat shields. If commonly occurring defects do not affect material performance, simpler manufacturing techniques can be used, quality control requirements can be relaxed, repair and rework operations can be held to a minimum, and thus the total manufacturing cost can be reduced.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 475-504
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  • 6
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    Docking devices for Soyuz-type spacecraft (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Two docking device designs for Soyuz-type spacecraft are compared. The first was flight tested successfully; the second achieves rigid and exact joining of two spacecraft, while incorporating changes to allow for the intravehicular transfer of crew members. The main functions of the docking device are considered, with the means by which they are accomplished, and measures for increasing its reliability and flexibility in service are noted.
    Keywords: SPACE VEHICLES
    Type: 6th Aerospace Mech. Symp.; p 143-150
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  • 7
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    Aerospace transporter and lifting body activities in Europe and potential participation in the development of the space shuttle orbiter (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The course of European aerospace research regarding reentry problems is briefly reviewed for the period from 1966 up to the present. The considerable experience gained by Europe, and particularly Germany, is shown to have led to their involvement and participation in the U.S. space shuttle program. The areas of investigation and expected contributions by European cooperation in the shuttle program are outlined.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 969-995
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  • 8
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    Rocket combustion instability suppression with cavity resonators (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Properly tuned Helmholtz resonator damping devices are an effective method for eliminating high frequency combustion instability in rocket engine thrust chambers. A program was implemented with the objective of extending Helmholtz resonator theory to thrust chamber conditions to establish a standard design procedure. By using systematic cold-flow testing and hot firings, empirical design equations were formulated. An effort is currently underway to extend the design theory to other types of acoustical damping devices such as quarter-wave tubes and slots.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Res. Achievements Rev., Vol. 4, No. 6; p 53-59
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  • 9
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    Status of reusable surface insulation thermal protection system technology programs (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of three low-density rigidized insulation materials for the shuttle TPS application is reported. These materials consist of one high purity silica system and two systems based on mullite, an aluminum silicate. Both systems consist of fibers joined together with appropriate binders to obtain a rigidized insulation composite. Both material systems require the application of a glassy coating to provide a wear resistant, high emittance surface and to prevent the absorption of water by the fiber matrix. The technology program has addressed the development of water impervious coatings, methods of assembling the materials in design concepts while minimizing the thermal stress in the insulation, achieving compatibility between the RSI material and the structural system, and test evaluations to demonstrate the feasibility of the surface insulation concept.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 435-474
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  • 10
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    Reusable surface insulation materials research and development (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Reusable surface insulation is considered a prime candidate for heat shielding large areas of the space shuttle vehicle. The composition and fabrication of RSI materials are discussed, followed by evolution of RSI and current problems, physical and thermal properties, arc plasma test data and results, and material improvement research. Finally, a summary of RSI technology status is presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 373-433
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  • 11
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    Overview of technology relative to the pogo instability on space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The prediction of pogo contains a major source of uncertainty in the difficulty of defining the dynamic characteristics of certain components. An overview of the space shuttle technology with respect to each the following pogo problem areas is presented: structure, tank-liquid interaction, feedline, engine (pump), pogo-loop/control-loop interaction, and stability analysis.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 117-138
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  • 12
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    Materials and design for ablative heat shields (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The goal of the ablation technology program is to bring ablation research and development to a high state of readiness for application to space shuttle vehicles. Some recent results and current work in the areas of materials, designs, and refurbishment for ablative TPS are reported. Future research and development needs are also presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 505-536
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  • 13
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    Assessment of potential buffet problems on the space shuttle vehicle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Buffet of the space shuttle launch and reentry configuration is an area requiring continued evaluation to produce a safe reliable vehicle of minimum weight. Buffet forces result from flow separation and therefore can not be predicted accurately. Buffet loads are highly sensitive to configuration, angle of attack, and Mach number and can be reliably determined only by wind tunnel tests of elastically scaled models.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 25-43
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  • 14
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    Thermal protection system trade studies on ablators and reuseable surface insulation (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Analytical trade studies are presented that consider passive TPS configurations using the following material categories: (1) reuseable surface insulation - surface-coated rigidized ceramic fiber; (2) low density charring ablators; and (3) carbon-carbon and high density ablators for leading edge areas. Emphasized are effects on TPS weight by variations in entry trajectories and material thermal characteristics.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 303-334
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  • 15
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    An assessment of radiative metallic thermal protection systems for space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The metallic thermal protection system technology program for the space shuttle is reviewed for the areas of environmental uncertainties, materials data base, TPS design concepts and heat-shield panel configurations, testing and evaluation of materials, panels, and complete systems.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 267-302
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  • 16
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    Dynamic analysis for shuttle design verification (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Two approaches that are used for determining the modes and frequencies of space shuttle structures are discussed. The first method, direct numerical analysis, involves finite element mathematical modeling of the space shuttle structure in order to use computer programs for dynamic structural analysis. The second method utilizes modal-coupling techniques of experimental verification made by vibrating only spacecraft components and by deducing modes and frequencies of the complete vehicle from results obtained in the component tests.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 205-230
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  • 17
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    Surface studies on Surveyor 3 tubing sections (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Sections C and E of the unpainted, polished aluminum tubing from the strut of the radar altimeter and Doppler velocity sensor were examined in a transmission electron microscope for micrometeorite damage and ion bombardment. Both sections were contaminated and eroded on one side; it is suggested that these conditions were caused by sandblasting by lunar dust and retrorocket plume contamination during Surveyor 3 landing. Microcraters of different configurations were found on the bright sides of the tubes. Several degrees of violence were involved in the formation of the craters, and the particle size could be responsible for some differences. All micropits found were on the bright areas and data indicate 0.2 hypervelocity impact/sq cm and 2/sq cm for other types of craters. The greatest degree of damage resulted from particle impact and was limited to a maximum depth of 2 microns.
    Keywords: SPACE VEHICLES
    Type: NASA, Washington Analysis of Surveyor 3 Mater. and Phot. Returned by Apollo 12; p 154-158
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  • 18
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    Development of a silicone ablator for high-heat-flux and high-shear-rate condition (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A silicone material was developed which gives suitable ablative protection in the high heat flux, high shear environments encountered in severe reentry applications, such as nose cones for ballistic vehicles and protection of leading edges or other critical areas of a vehicle. In addition, the ease of handling, low application cost, and room temperature cure make such a silicon material suitable nozzles for the large rockets necessary for vehicle launching. The development of this product is traced from the selection of suitable polymers through the choice of fillers and the finalization of filler loadings.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Goddard Space Flight Center Space Simulation; p 725-748
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  • 19
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    Aerodynamic studies of delta-wing shuttle orbiters. Part 2: Hypersonics (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An early version of an external hydrogen-oxygen tank orbiter was used as a baseline vehicle to experimentally evaluate: (1) nose shape and canopy effects on longitudinal, lateral, and directional stability and trim, and (2) yaw due to aerodynamic roll control at hypersonic speeds. Nose alterations were examined since that part of the vehicle may be subject to modifications because of internal packaging requirements, alleviation of potential high heating areas, and/or possible improvements in aerodynamic stability and control. There was also some concern about the effect of the rather high profile canopy on the aerodynamics; therefore its removal was examined. In addition, roll-yaw coupling was investigated because of its impact on the RCS fuel requirements for entry maneuvers.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 803-830
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  • 20
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    Space simulation and rate dependent radiation testing (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An environmental test facility is described which allows in-situ measurements for evaluation of near real time sinergistic effects of combined space environments.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Goddard Space Flight Center Space Simulation; p 453-460
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  • 21
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    Impact of subsonic aerodynamic considerations on a space shuttle booster configuration (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Considerations of cruise-back efficiency and subsonic flying qualities are shown to have resulted in a configuration with an aft high wing of moderate aspect ratio and with vertical tails located at the wing tips. The need to protect the air breathing engines during ascent and reentry and the desire for a low trim penalty longitudinal control surface led to consideration of a jet-flap canard. The advantages of this application of STOL technology to a space system are examined and the results of both wind tunnel tests and flight simulations are discussed. Since the use of the jet-flap canard concept offers the potential for a minimum weight vehicle, a proposed technology development program is outlined in order that the full benefit of this concept may be realized.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol.3; p 737-784
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  • 22
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    Nozzle exhaust plume backscatter experiment using the JPL Molsink facility (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Qualitative tests were made by injecting water through a rocket nozzle wall, and the droplet trajectories were observed photographically. These tests were conducted for nozzles in which boundary layer flow is significant. The tests indicated that both gases and particulate matter will be found in the region outside of the plume boundaries, and can be calculated using current analytical techniques. A test program is being conducted to measure the distribution of exhaust gases from small nozzles using an electron beam/photomultiplier system and a matrix of quartz crystal microbalances. Calibration tests, using simulated hydrazine exhaust product gas mixtures, were also conducted. The test program and results of the pumping calibration tests with hydrazine (simulated hydrazine exhaust products) are reported.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 89-96
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  • 23
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    On the possibility of Earth reentry simulation of shallow angle Jupiter entry (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Possible Earth reentry simulation of shallow-angle (3 to 30 deg) Jupiter entry was investigated in terms of four parameters of the bow shock layer ahead of a blunt vehicle: peak (equilibrium) temperature, peak pressure, peak inward radiative flux, and time-integrated radiative flux. It is shown that simulation ranging from fair to good can be achieved. Reentry is easiest (lowest Earth reentry speed) at steep Earth reentry, in the Earth entry speed range of 15 to 22 km/sec, for both the Jupiter nominal and cool atmospheres. Increased Earth speed is required, generally, for increasing Jupiter entry angle, and for increasing temperature, radiative flux, time-integrated flux and pressure, in that order.
    Keywords: SPACE VEHICLES
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 19-29
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  • 24
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    Application of composite materials to space shuttle tanks (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Tanks are broken down into two categories: pressure vessels that carry primarily pressure loads, and structural tanks that carry structural loads such as thrust or bending in addition to pressure. A significant portion of the shuttle orbiter structure are tanks and in order to minimize both weight and cost growth on these shuttle tank structures, composite material tanks of both types are considered.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 573-603
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  • 25
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    Advanced design concepts for shuttle airframe structure (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of weight-saving advanced design concepts for shuttle airframe structure is presented. Design concepts under investigation employ selective composite reinforcement and/or efficient geometric arrangements. An effort to develop metallic panel designs which exploit the relaxation of smooth external-surface requirements for skin structure is reviewed. Available highlights from research and development studies which investigate the application of composite reinforcement to the design of two types of fuselage panels, a shear web, a large fuselage frame, and a landing-gear-door assembly are presented. Preliminary results from these studies suggest weight savings of 25 percent can be obtained.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 537-572
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  • 26
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    Oxidation protected carbon-carbon (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Pyrolized carbon-carbon has one unique advantage over other materials that makes its application to the space shuttle thermal protection system very attractive. This unique characteristic is the increase in material strength and modulus with increase in temperature up to about 2500 K (4040 F). Offsetting this unique advantage are disadvantages which include brittleness, high cost, and the tendency of the material to react with oxygen, particularly at high temperatures. The development of an oxidation inhibitor for the material and the definition of fabrication processes for selected full-scale components are considered.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 335-372
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  • 27
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    Flutter technology for space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of analytical and experimental techniques needed to predict space shuttle flutter boundaries and insure adequate flutter margins and anticipated problems associated with aeroelastic-model and full-scale testing to validate flutter clearance are considered. Results illustrating the best available tools for subsonic and supersonic flutter prediction are presented. Programs currently underway which will help overcome the difficult problems envisioned for the transonic wind-tunnel and flight flutter test program are also discussed.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 1-24
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  • 28
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    Gas-powered reentry body erection mechanism (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The design, analysis, testing, and flight of the supersonic planetary entry decelerator 2 spacecraft are described. The vehicle was launched in a folded condition and deployed to its required configuration following exit from the atmosphere. This concept was selected primarily because it allows utilization of existing launch vehicle systems in the most economical manner possible.
    Keywords: SPACE VEHICLES
    Type: 6th Aerospace Mech. Symp.; p 101-107
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  • 29
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    Satellite temperature correlation of predicted, test, and flight data (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: This study compares satellite temperature predictions with thermal vacuum test results and shows the improvement from testing. Orbital data were compared with prediction/test results to determine quantitatively an expected error criteria.
    Keywords: SPACE VEHICLES
    Type: NASA. Goddard Space Flight Center Space Simulation; p 425-443
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  • 30
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    Experiments on the dynamic stability of the space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Some dynamic stability experiments on the space shuttle using a half-model oscillatory technique are discussed. Resulting information from the experiments is presented and includes: (1) dynamic pitching characteristics of both the orbiter and the booster alone as well as of the two models mated into a single launch configuration; (2) the static and dynamic interference effects during an abort separation maneuver; and (3) the dynamic plume interference effect.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 933-968
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  • 31
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    Dynamic testing for shuttle design verification (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Space shuttle design verification requires dynamic data from full scale structural component and assembly tests. Wind tunnel and other scaled model tests are also required early in the development program to support the analytical models used in design verification. Presented is a design philosophy based on mathematical modeling of the structural system strongly supported by a comprehensive test program; some of the types of required tests are outlined.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 231-265
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  • 32
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    Heat pipes for spacecraft temperature control: Their usefulness and limitations (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Heat pipes are used in spacecraft to equalize the temperature of structures and maintain temperature control of electronic components. Information is provided for a designer on: (1) a typical mounting technique, (2) choices available in wick geometries and fluids, (3) tests involved in flight-qualifying the design, and (4) heat pipe limitations. An evaluation of several heat pipe designs showed that the behavior of heat pipes at room temperature does not necessarily correlate with the classic equations used to predict their performance. They are sensitive to such parameters as temperature, fluid inventory, orientation, and noncondensable gases.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: 6th Aerospace Mech. Symp.; p 33-41
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  • 33
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    Neuter docking mechanism study (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Neuter (or androgynous) docking systems that allow space vehicles with similar or identical docking hardware to dock are discussed. Basic requirements applicable to docking mechanism design, four neuter concepts that were studied, and the concept selected by the NASA Manned Spacecraft Center for detailed investigation are presented.
    Keywords: SPACE VEHICLES
    Type: 6th Aerospace Mech. Symp.; p 43-49
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  • 34
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    Aerodynamic studies of delta-wing shuttle orbiters. Part 1: Low speed (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Numerous wind tunnel tests conducted on the evolving delta-wing orbiters have generated a fairly large aerodynamic data base over the entire entry operation range of these vehicles. A limited assessment is made of some of the aerodynamics of the current HO type orbiters, and several specific problem areas selected from the broad data base are discussed. These include, from a subsonic viewpoint, discussions of trim drag effect; effects of the installation of main rocket engine nozzles, OMS and RCS packages, Reynolds number effects, lateral-directional stability characteristics, and landing characteristics.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 785-802
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  • 35
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    Wing optimization for space shuttle orbiter vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The results were presented of a parametric study performed to determine the optimum wing geometry for a proposed space shuttle orbiter. The results of the study establish the minimum weight wing for a series of wing-fuselage combinations subject to constraints on aerodynamic heating, wing trailing edge sweep, and wing over-hang. The study consists of a generalized design evaluation which has the flexibility of arbitrarily varying those wing parameters which influence the vehicle system design and its performance. The study is structured to allow inputs of aerodynamic, weight, aerothermal, structural and material data in a general form so that the influence of these parameters on the design optimization process can be isolated and identified. This procedure displays the sensitivity of the system design of variations in wing geometry. The parameters of interest are varied in a prescribed fashion on a selected fuselage and the effect on the total vehicle weight is determined. The primary variables investigated are: wing loading, aspect ratio, leading edge sweep, thickness ratio, and taper ratio.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 831-860
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  • 36
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    Status of Langley studies of aerodynamics and interference effects of tandem launch vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Some of the aerodynamic and interference effects measured from wind-tunnel tests of three fully reusable space shuttle configurations at transonic and low-supersonic speeds are presented, and the status is given of an assessment of the analytical approach to date. The three configurations tested were a low-fineness-ratio booster combined in tandem with a delta-wing orbiter, designated the "low-fineness-ratio configuration,' and a phase B shuttle configuration consisting of the delta-wing orbiter and high-fineness-ratio booster, designated the "stage-arrangement configuration,' arranged in tandem and in parallel. The force measurements obtained at a Mach number of 1.5 for the low-fineness-ratio configuration were representative of the transonic and low-supersonic speed ranges where the interference effects are predominant and were used for comparison with values calculated at the same Mach number. This comparison is the basis for a preliminary assessment of the initial application of the analytical approach.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 707-736
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  • 37
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    A review of the Grumman orbiter wind tunnel heat transfer tests (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Tests were conducted in the NASA Langley continuous flow, variable density and Mach 20 helium tunnels. The orbiter was tested alone and with various side and tandem mounted tanks. Test conditions spanned a Reynolds number range which resulted in both laminar and turbulent flows. Experimental studies also examined the heat transfer problems associated with integration of the auxiliary propulsion system into the orbiter. Tests in the hypersonic shock tunnel investigated heating to cavities and heating from single and multiple hydrogen-oxygen plumes while tests, run as part of the configuration evaluation, examined the heating to wing pods.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 297-345
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  • 38
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    Some contamination problems in the European TD satellite (1972)
    In:  CASI
    Details
    Publication Date: 2009-11-16
    Description: Materials were selected for the European TD satellite with a view to avoiding contamination of its stellar ultraviolet telescopes. Materiels were selected using the micro-VCM technique, and some typical cases of materials evaluation are described. The cleanliness of the satellite was monitored during integration and test phases, and in particular during long duration thermal vacuum tests.
    Keywords: SPACE VEHICLES
    Type: NASA. Goddard Space Flight Center Space Simulation; p 613-627
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  • 39
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    Heat-transfer testing procedures in phase B shuttle studies with emphasis on phase change data improvement (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The procedures used in the application of the phase change technique to the phase B shuttle configuration are discussed along with factors which may affect data accuracy. These factors include variation of thermal properties of phase change model material, sensitivity of measured heat transfer coefficients to the assumed value of the adiabatic to total temperature ratio, and wall temperature effects. These sensitivities are illustrated in sample calculations for a shuttle geometry. Factors which may affect the visual clarity and interpretation of phase change data are discussed, and a method of improving photographic data quality through the use of polarized light is presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 661-682
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  • 40
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    An analysis of the booster plume impingement environment during the space shuttle nominal staging maneuver (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: An experimental study of the plume impingement heating on the space shuttle booster afterbody resulting from the space shuttle orbiter engine plumes was conducted. The 1/100-scale model tests consisted of one and two orbiter engine firings on a flat plate, a flat plate with a fin, and a cylinder model. The plume impingement heating rates on these surfaces were measured using thin film heat transfer gages. Results indicate the engine simulation is a reasonable approximation to the two engine configuration, but more tests are needed to verify the plume model of the main engine configuration. For impingment, results show models experienced laminar boundary layer convective heating. Therefore, tests at higher Reynolds numbers are needed to determine impingment heating.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 607-644
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  • 41
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    Determination of aerothermodynamic environment uncertainties with application to space shuttle vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: In an effort to minimize the cost of the thermal protection system (TPS) for space shuttles, an analysis is made of environmental uncertainties. The basic categories of these uncertainties include aerodynamic heating, trajectory dispersions, atmospheric variations, and vehicle attitude variations. Also discussed are TPS design sensitivity to environmental uncertainties, and uncertainty profiles. Preliminary results indicate moderate TPS cost for a high confidence level environment may be obtained.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 503-518
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  • 42
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    Aerothermodynamic measurements for space shuttle configuration in hypersonic wind tunnels (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The effect of shuttle configuration geometry, angle of attack, and free stream flow conditions on the heat-transfer distribution as influenced by three-dimensional effects, the wing-fuselage shock-interaction, and resultant wing-impingement phenomena are examined. In addition, the data provided information regarding the flow field in the vicinity of the nose and boundary layer transition in the plane of symmetry of the fuselage. The data included measurements of the surface pressure, the heat transfer rate distributions, (using models instrumented with thermocouples and models painted with thermographic phosphor) and schlieren and shadowgraph photographs. Posttest photographs of the painted models supplemented the heat transfer data.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 469-501
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  • 43
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    Lee-side flow phenomena on space shuttle configurations at hypersonic speeds. Part 2: Studies of lee-surface heating at hypersonic Mach numbers (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: Lee surface heating data, obtained at relatively low unit Reynolds numbers at Mach 6 and 19, are discussed with emphasis on the peak heating behavior. Surface pressures measured along the lee meridian of the delta-wing orbiter are presented and analyzed in conjunction with the heating. The effects of nose bluntness and lee surface geometry on the heating are discussed and general guidelines are presented for modifying the lee surface geometry of the shuttle to reduce vortex-induced heating. The application of the wind tunnel results to realistic shuttle flight conditions is discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 451-467
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  • 44
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    Effects of roughness on heating and boundary-layer transition. Part 2: effects of discrete roughness on heating (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: A preliminary investigation on the effects of roughness on heating in delta wing orbiters was conducted on the windward surface of the vehicle. The purpose of the experiment was to determine the feasibility of using parametric relationships obtained from discrete roughness effects on heating in flat plates and cones, to complex shuttle configurations. An attempt was also made to characterize what parameters were needed to influence roughness. Experimental results show that effective roughness Reynolds numbers are less than or equal to those of flat plates at the same edge Mach number, but, the roughness correlations for plates and cones cannot be applied to the shuttle configuration.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 395-411
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  • 45
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    Lee-side flow phenomena on space shuttle configurations at hypersonic speeds. Part 1: Flow separation and flow field viscous phenomena of a delta-wing shuttle orbiter configuration (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: Results of a pitot pressure investigation of the flow field on the lee side of a delta wing shuttle orbiter are presented. The results delineate the extent of the lee side separated flow and give a tentative cross sectional definition to the shock wave structure for angles of attack of 15 deg and 30 deg. It is shown that while, in general, the effects of Reynolds number on the flow field are not large, detailed effects are observed that may have significant bearing on the heating estimate. Two examples are cited for an angle of attack of 15 deg; these are: (1) The scope of the vertical tail exposed to the unseparated flow increases with increasing Reynolds number and (2) the depth of the separated flow adjacent ot where the bow wave crosses the wing appears to decrease with increasing Reynolds number. In addition, it is shown that at a spanwise station outboard of the wing-fuselage juncture, increasing Reynolds number decreased the pitot pressure in the unseparated flow. This defect of pitot pressure appears associated with the flow over the wing-fillet-fuselage juncture.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 413-449
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  • 46
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    Effects of roughness on heating and boundary-layer transition. Part 1: Effects of simulated panel joints on boundary-layer transition (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The effects of distributed roughness, arising from space shuttle orbiter panel joints, on boundary layer transition are investigated. The North American Rockwell 134B delta wing shuttle configuration was used for the study. Results show: (1) Premature boundary layer transition occurred in models having simulated heat shield panels with rased joints. (2) Laminar flow was maintained with slot type panel joint models to a Reynolds number twice that at which transition occurred in raised joints. (3) Significant increases in peak surface temperature and the time during which turbulent flow occurs may result from distributed roughness of heat shield panel joints. (4) Laminar and turbulent heating levels were predicted within available theories. (5) A complex interference between the wing and fuselage flow was observed in the delta wing model.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 375-394
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  • 47
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    High Reynolds number turbulent heating to two simplified shuttle configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: Turbulent heating and transition data, taken from three test facilities, for two space shuttle configurations are presented. Major efforts were on: (1) the effect of the two geometries having different amounts of cross flow and how the different cross flows affect heating and transition, (2) the experimental level of turbulent heating and the ability to predict the level of turbulent heating, and (3) a comparison of the transitional and turbulent heating in three facilities with two model scale sizes to investigate the facility effects and scale-size effect on transition and turbulent heating. The three facilities in which the configurations were tested are the Langley Mach 8 variable-density hypersonic tunnel and the Arnold Engineering Development Center tunnel B and tunnel F at Mach numbers of 8 and 10.5, respectively.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 347-373
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  • 48
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    Experimental and theoretical aerodynamic heating and flow field analysis of a space shuttle orbiter (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The results of work on the McDonnell Douglas delta wing orbiter are summarized and compared to other data and theories where applicable. The tests were conducted in the continuous hypersonic Tunnel B at Mach 8 and in the hypervelocity hotshot Tunnel F at Mach 10.5. Photographic data are used to illustrate the regions of peak heating on the lee-side and to show the vortical nature of the flow. Windward centerline data include measurements of shock angle, surface pressure, flow field pitot pressure and total temperature, and heat transfer rate coefficient distributions. Shock angles, surface pressures, and local Mach number distributions are compared with tangent cone theory over an angle of attack range from 10 to 60 deg. The measured heat transfer rate coefficient distributions are compared to both laminar and turbulent theories and boundary layer transition data are compared to the McDonnell Douglas criteria.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 261-296
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  • 49
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    Small rocket exhaust plume data (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: During recent cryodeposit tests with an 0.18-N thruster, the mass flux in the plume back field was measured for the first time for nitrogen, carbon dioxide, and a mixture of nitrogen, hydrogen, and ammonia at various inlet pressures. This mixture simulated gases that would be generated by a hydrazine plenum attitude propulsion system. The measurements furnish a base upon which to build a mathematical model of plume back flow that will be used in predicting the mass distribution in the boundary region of other plumes. The results are analyzed and compared with existing analytical predictions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: JPL Quart. Tech. Rev., Vol. 2, No. 2; p 90-99
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  • 50
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    Statistical distribution of spacecraft maximum structural response. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Under nonstationary random excitations resulting from booster engine shutdown, a direct statistical analysis of spacecraft maximum response is performed, and the spacecraft structural reliability is obtained. It is found that the Gumbel (1958) Type I asymptotic distribution of maximum values provides a reasonably good statistical model for spacecraft maximum responses. This approach makes it possible to perform the reliability-based optimum design of spacecraft structures.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 9; Jan. 197
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  • 51
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    Thermal design verification testing for the ATS-F and -G spacecraft. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: There is a wide fluctuation in the internal power dissipation from the components within the earth viewing module (EVM). The electronic component functional reliability required for a two-to-five year mission is the most significant factor for the thermal design criteria. A mathematical thermal model of the EVM and the orbital environment is used to predict the performance of the thermal control system. Comparisons of the results obtained in chamber thermal balance tests with the data computed on the basis of the theoretical model provide the means for validating the thermal design.
    Keywords: SPACE VEHICLES
    Type: Journal of Environmental Sciences; 15; Mar
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  • 52
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    Lambda-point measurements of eta rho sub n for pure He 4 and for three He 3-He 4 mixtures. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Results of torsional crystal measurements of eta rho sub n for pure He 4 and for three He 3-He 4 mixtures over temperature intervals which included their respective lambda points. The precision of the measurements for the mixtures was greater than that of any previous lambda-point eta rho sub n measurements. Doubly reduced plots of eta rho sub n versus T showed a slight but definite tendency for such curves to rotate clockwise about the (1,1) point with increasing x sub 3 up to about 0.05. Values of eta were derived from the measurements by computing rho sub n as a function of T*. For each mixture, both eta and d eta/dT were continuous across T sub lambda (x sub 3). No tendency was manifest for such curves to develop discontinuities as x sub 3 decreased. It was therefore inferred that both eta and d eta/dT of pure He 4 are continuous across T sub lambda (0).
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physical Review A - General Physics; vol. 5
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  • 53
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    The space shuttle and its uses. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The development of reusable space-shuttle vehicles has been made practical by the availability of improved staged-combustion engines and durable thermal protection systems. A two-state launch configuration with fully reusable booster and orbiter elements is considered to be the best design solution, and size specifications for such a vehicle are examined as a function of launch costs. Significant vehicle characteristics are explained in terms of cargo bay dimensions, cross-range maneuvering capability, mission duration requirements, engine characteristics, and acceleration constraints. Shuttle flight activities include satellite deployment and repair, sortie missions for short-duration research purposes, and space station support operations. Phases of the development program are outlined, and structural details of several candidate space shuttle concepts are illustrated.
    Keywords: SPACE VEHICLES
    Type: Aeronautical Journal; 76; Jan. 197
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  • 54
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    Radiative cooling of shock-heated air in an explosively driven shock tube. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Results are presented of an experimental program to measure the effect of radiative cooling on the enthalpy distribution behind incident shock waves traveling in air. The shock velocity was nominally 16 km/sec and the preshock ambient pressure was varied from 0.4 to 1.6 torr. Shock-tube diameters of 4.7 and 9.4 cm were used to investigate the effects of varying optical depths. Radiative cooling rates were determined from spatially resolved measurements of the profile of the H sub alpha line and from absolute measurements of the continuum radiation. The measured enthalpy profiles are in good agreement with the theoretical predictions of Chien and Compton which account for both nongrey and multidimensional aspects of the radiative transport in the shock tube.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physics of Fluids; 15; Jan. 197
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  • 55
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    Shuttle ascent guidance and control. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The requirements of a unified optimal guidance scheme are discussed, giving attention to a general formulation, aspects of self-targeting, problems of optimum guidance within the atmosphere, and a unified concept for all flight phases. Since no previous guidance scheme meets these requirements, the shuttle demands a fundamentally new approach. A new unified optimal guidance scheme, called Mascot, was developed. The capabilities of Mascot include the real-time solution of general trajectory-optimization problems and the unification of guidance for all flight phases.
    Keywords: SPACE VEHICLES
    Type: Astronautics and Aeronautics; 10; Feb. 197
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  • 56
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    Flying automated laboratories to the planets. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of results obtained by instrumented spacecraft in investigation of the planets, mainly Mars. It appears that Mars is a world of varying topographical structure, some of which must have been created by the same processes that sculptured the moon and by others thus far unique in the solar system. The atmosphere is too thin to shield the surface, and there are no traces of liquid water. The very large recent dust storm is discussed. Mariner 9 has revealed definite indication of probable volcanic activity on Mars in recent geologic times.-
    Keywords: SPACE VEHICLES
    Type: Teledyne Ryan Aeronautical Reporter; 33; Spring 1
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  • 57
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    Skylab status report. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The laboratory will be launched on Apr. 30, 1973, aboard a Saturn V vehicle. Approximately twenty-three and a half hours later the first crew will be launched in a command and service module aboard a Saturn IB launch vehicle. The laboratory will consist of modules. The orbital workshop (OWS) is made from the liquid oxygen and liquid hydrogen tanks of a Saturn S-IVB third stage. The OWS contains the living quarters and two experiments areas. The airlock sits on top of the OWS and contains the controls and hatch for the extra-vehicular activity.
    Keywords: SPACE VEHICLES
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  • 58
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    Small-scale wind shear definition for aerospace vehicle design. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Rawinsonde wind profile data provide adequate wind shear information for vertical height intervals greater than 1 km. To specify wind shears for intervals below 1 km for space vehicle design, detailed wind-profile information like that provided by the FPS-16 Radar/Jimsphere system or an extrapolation procedure is required. This paper is concerned with the latter alternative. It is assumed that any realization from an ensemble of wind profiles can be represented in terms of a Fourier integral. This permits the calculation of the ensemble standard deviation and mean of the corresponding shear ensemble for any altitude and shear interval in terms of the power spectrum of the ensemble of wind profiles. The results of these calculations show that the mean and standard deviation of the wind shear ensemble, as well as the wind shear for any percentile, asymptotically behave like the vertical interval to the 0.7 power. This result is in excellent agreement with shear data from Cape Kennedy, Fla.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 9; Feb. 197
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  • 59
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    Stability of plane Poiseuille flow with heat transfer. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Investigation of the influence of heat transfer on the stability of a plane Poiseuille flow iahnnl. The liquid flow is affected by the heat transfer through the variation in viscosity with temperature. Additional viscosity gradient terms are included in a modified Orr-Sommerfeld equation, and it is the presence of these terms which leads to a prediction of more unstable flows, for without the inclusion of these extra terms, the flow is stabilized. The results show that a temperature difference between the walls is always destabilizing and, in particular, a temperature difference between the walls of 100 F leads to a reduction in the critical Reynolds number from 7800 to 4600.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physics of Fluids; 15; Mar. 197
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  • 60
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    Thermal radiation heat transfer. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A comprehensive discussion of heat transfer by thermal radiation is presented, including the radiative behavior of materials, radiation between surfaces, and gas radiation. Among the topics considered are property prediction by electromagnetic theory, the observed properties of solid materials, radiation in the presence of other modes of energy transfer, the equations of transfer for an absorbing-emitting gas, and radiative transfer in scattering and absorbing media. Also considered are radiation exchange between black isothermal surfaces, radiation exchange in enclosures composed of diffuse gray surfaces and in enclosures having some specularly reflecting surfaces, and radiation exchange between nondiffuse nongray surfaces. The use of the Monte Carlo technique in solving radiant-exchange problems and problems of radiative transfer through absorbing-emitting media is explained.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 61
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    Shuttle status report. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The Space Shuttle Program is still in Phase B, a phase consisting predominantly of paper analyses and trade studies leading to the selection of a single design. A brief history of the program up to Phase B is discussed together with the results of the original year-long Phase B effort, and the objectives of the Phase B extension currently in work. A Lockheed study is discussed together with a Grumman/Boeing study, Phase B contractor results, displays and controls, simulations, and the flight test.
    Keywords: SPACE VEHICLES
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  • 62
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    Matrix transformations for spacecraft attitude determination. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: SPACE VEHICLES
    Type: Planetary and Space Science; 20; Oct. 197
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  • 63
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    A review of film boiling at cryogenic temperatures. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Film boiling occurs in the quenching of metals, the chilling of biological species, the regenerative cooling of rockets, and the cooling down of a cryogenic fuel tank. Occasionally film boiling is also found in a nuclear reactor or in a cryomagnet. Aspects of film boiling involving an unconstrained liquid mass are considered, giving attention to the evaporation time, the Leidenfrost temperature, solid-liquid contacts, the thermal properties of the solid, effects of coating or scale, wettability, the metastable condition, and the velocity effect on drops. Developments discussed with regard to pool boiling are related to vertical surfaces, film boiling from horizontal surfaces, film boiling from a horizontal cylinder, film boiling from a sphere, and film boiling of helium. Processes of film boiling in a channel are also analyzed.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 64
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    Orbital propellant depot system. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of some of the problems involved in the design of a long-term propellant storage depot in earth orbit to act as a resupply station for cargo/personnel shuttles between earth orbit and lunar orbit, between low earth orbit and synchronous orbit, and possibly for use with interplanetary probes. The problems discussed pertain essentially to the long-term storage and propellant transfer capabilities.
    Keywords: SPACE VEHICLES
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  • 65
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    Minimum weight passive insulation requirements for hypersonic cruise vehicles. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Analytical solutions are derived for two representative cases of the transient heat conduction equation to determine the minimum weight requirements for passive insulation systems of hypersonic cruise vehicles. The cases discussed are the wet wall case with the interior wall temperature held to that of the boiling point of the fuel throughout the flight, and the dry wall case where the heat transferred through the insulation is absorbed by the interior structure whose temperature is allowed to rise.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 10; July 197
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    A halo-orbit lunar station. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A relay satellite following a halo trajectory will always maintain line-of-sight contact with the earth and the moon's far side. The Integrated Program Plan for lunar exploration in the 1980s and beyond calls for a fully reusable earth-moon transportation system. The principal elements of the system are a Translunar Shuttle, a Lunar-Orbit Space Station or Halo-Orbit Space Station, and a Lunar Space Tug. It is shown that a halo-orbit space station could offer important operational and performance advantages compared to a lunar-orbit station in a second-generation lunar program.
    Keywords: SPACE VEHICLES
    Type: Astronautics and Aeronautics; 10; June 197
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  • 67
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    Self-contamination and environment of an orbiting satellite. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The flux of molecules emitted by the satellite and subsequently returning to its surface is investigated. The reflection occurs upon collision of these with ambient molecules. The evaluation of this flux is carried out from a knowledge of the outgassing rate of the satellite, its dimensions, and the orbit parameters. Condensation rates and adsorption layers on critical surfaces are calculated from the knowledge of this flux, and from the natures and temperatures of the gas and the surface. The calculation of these parameters, based on estimated and in some cases measured emission rates, has been carried out for a number of satellites. These developed relationships and graphs allow the estimation of several important parameters for an orbiting satellite. This report presents the pressures and densities at various distances from the satellite as produced by the surrounding ambient molecules and by the outgassing of the satellite.
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  • 68
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    Lateral expansion of a laser-supported detonation wave in a gas. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A model satisfying the conditions in the burnt (ionized) and ambient undisturbed gases is presented for the two-dimensional case of the absorption wave resulting from the interaction of a laser beam with the plasma it generates in the gas through which the beam propagates. The flowfield of the rarefaction wave resulting from the laser-supported detonation is discussed, along with the computed shock and flow deflection angles.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 10; Dec. 197
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  • 69
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    Computed total radiation properties of compressed oxygen between 100 and 1000 K. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Journal of Heat and Mass Transfer; 15; Nov. 197
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  • 70
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    An experimental investigation of radiative properties of aluminum oxide particles. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The radiative properties of aluminum oxide at high temperatures were determined at various wavelengths. Absorption cross-sections of aluminum oxide particles averaged over a particle size distribution were determined by measuring the radiative emission from the particles in a flame and by determining the particle number density and size distribution from measurements of the scattering of laser light incident on the particles in this flame. From these values of average absorption cross-section, the imaginary part of the refractive index was deduced. Results indicate that the absorption cross-section and the imaginary part of the refractive index increase as the temperature increases in the range from 1920 to 2610 K, and that these properties decrease with increasing wavelength in the interval from 0.35 to 1.2 micron, indicating a nongray-body behavior.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer; 12; Nov. 197
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  • 71
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    Parameters influencing dynamic stability characteristics of Viking-type entry configurations at Mach 1.76. (1972)
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    Publication Date: 2011-08-16
    Description: Free-oscillation tests of three Viking-type blunt conical configurations were conducted in a wind tunnel to determine the important variables influencing their dynamic stability characteristics at Mach 1.76. The effects of sting geometry are shown to be significant at low angles of attack, while the effects of cross plane motions and tunnel vibration characteristics appear to be negligible. Variation of the reduced-frequency parameter and model base geometry caused significant effects in the data. An approximate technique was developed for converting effective data from either forced-oscillation or free-oscillation tests to values based on the instantaneous angle of attack.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 9; July 197
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  • 72
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    Air film cooling in a nonadiabatic wall conical nozzle. (1972)
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    Publication Date: 2011-08-16
    Description: Experimental data for an air-film cooled conical nozzle operating with a heated-air main stream and a water-cooled wall confirm the validity of Lieu's (1964) method for correlating film cooling data in the accelerated flow of a nonadiabatic-wall nozzle. The film cooling effectiveness modified for nonadiabatic walls by Lieu can be used to correlate film cooling under the condition that the main-stream to coolant velocity ratio at the slot is about 1. Such a ratio provides the optimum cooling effectiveness.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 9; July 197
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  • 73
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    Space-Shuttle applications. (1972)
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    Publication Date: 2011-08-16
    Description: Discussion of the performance potential of the Space Shuttle and the high-energy transportation system to be derived from it. It is shown that, in addition to its cost effectiveness in earth-orbital missions, the Shuttle promises to be of major significance for future solar-system exploration. Eventually, the Shuttle will make possible the use of large interplanetary payloads launched at high velocities to the far reaches of the solar system.
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  • 74
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    The Skylab orbital laboratory. (1972)
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    Publication Date: 2011-08-16
    Description: The Skylab orbital laboratory is described in terms of spacecraft design features, the experiment programs, and the schedule of planned missions. Attention is given to flight and crew operations, rescue measures, the Multiple Docking Adapter, the Airlock Module, the Workshop, the Apollo Telescope Mount, Saturn V booster, Command and Service Modules, the life support system, thermal and environmental control, electrical power, attitude and pointing control, instrumentation and communications, crew equipment, provisions, and stowage.
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  • 75
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    Second virial coefficients for the polar species in steam. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The potential function parameters to fit the data obtained by Kell et al. (1968) are determined. The data of Kell et al. cover the temperature range from 150 to 450 C. Data for the temperature range from 500 to 1000 C are from Sugaware et al. (1964). These calculations have been extended to include OH-OH and OH-H2O pairwise interactions. For the latter interaction the formalism was extended to the case of unequal dipole quadrupole moments in the potential function for the interacting species.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Physical Chemistry; 76; Sept. 28
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  • 76
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    Fundamentals of spacecraft thermal design. (1972)
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    Publication Date: 2011-08-16
    Description: The papers deal with and are grouped according to four major issues. These are: surface radiation properties, including synthesis and measurement, space flight effect, and contamination effects; thermal analysis, including reentry vehicle analysis, radiant heat transfer between surfaces, and thermal contact conductance of surfaces; heat pipes, including possible applications, operating characteristics, and design, fabrication and testing of heat pipes; and thermal design, including radiative, ablative, and active cooling thermal protection of the leading edge of a space-shuttle wing, and space station environmental thermal control. Individual items were previously announced in issues 06 and 11, 1971.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 77
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    Inhibition of the ablation rate of graphite by gaseous chlorine. (1972)
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    Publication Date: 2011-08-16
    Description: Investigation of the inhibiting effect of gaseous chlorine on the ablation rate of graphite. It is shown that small amounts of chlorine gas, when present in a supersonic high-temperature air environment, can inhibit the ablation rate of graphite and depress its surface temperature below that measured in pure air. The ablation inhibition performance of chlorine is presented in graphs in terms of mass loss rate and surface temperature depression as a function of chlorine concentration.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 10; May 1972
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  • 78
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    Silica reinforcement and char reactions in the Apollo heat shield. (1972)
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    Publication Date: 2011-08-16
    Description: Reactions of the silica reinforcement fiber and ablation char of the Apollo heat shield have been investigated by laboratory tests in an arc image furnace (at temperature levels up to 5000 R, pressures up to 0.7 atm, and heat flux similar to reentry) and by an actual reentry test. Microchemical analyses and X-ray diffraction studies have been made to determine the presence of SiC formation in the char. Experimental data and analytical predictions of thermal and density profiles have been compared for the ablation of virgin heat shield and precharred materials to determine the effects of SiC formation on ablation performance. In all analyses, general agreement was found between chemical composition and the thermal predictions for laboratory tests and reentry materials. In all ablated materials, SiC was formed in the front surface of the char. The highest SiC content found was 58% by weight and found in a high-pressure environment. The SiC formed was found to act as a heat sink in the ablation process and can lower the front surface temperature by 300 R.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 9; May 1972
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  • 79
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    Thermal Control of the Scientific Instrument Package in the Large Space Telescope (1972)
    In:  CASI
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    Publication Date: 2014-09-09
    Description: The general thermal control system philosophy was to utilize passive control where feasible and to utilize active methods only where required for more accurate thermal control of the SIP components with narrow temperature tolerances. A thermal model of the SIP and a concept for cooling the SIP cameras are presented. The model and cooling concept have established a rationale for determining a Phase A baseline for SIP thermal control.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Auburn Univ. The NASA-ASEE Summer Fac. Fellowship Program; p 203-228
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  • 80
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    Satellite Aerodynamics and Density Determination from Satellite Dynamic Response (1972)
    In:  CASI
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    Publication Date: 2014-09-09
    Description: The aerodynamic drag and lift properties of a satellite are first expressed as a function of two parameters associated with gas-surface interaction at the satellite surface. The dynamic response of the satellite as it passes through the atmosphere is then expressed as a function of the two gas-surface interaction parameters, the atmospheric density, the satellite velocity, and the satellite orientation to the high speed flow. By proper correlation of the observed dynamic response with the changing angle of attack of the satellite, it is found that the two unknown gas-surface interaction parameters can be determined. Once the gas-surface interaction parameters are known, the aerodynamic properties of the satellite at all angles of attack are also determined.
    Keywords: SPACE VEHICLES
    Type: Auburn Univ. The NASA-ASEE Summer Fac. Fellowship Program; p 345-364
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  • 81
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    Part B: Heat Transfer to Slush Hydrogen (1972)
    In:  CASI
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    Publication Date: 2014-09-04
    Description: Heat transfer to slush hydrogen was measured at one atmosphere and at triple-point pressure. The data were compared with those for heat transfer to liquid hydrogen, and to classical heat transfer correlations for nucleate boiling. The slush data fit convective heat transfer correlations quite well. In general, the data show that for a given heat flux, the temperature difference between the wall and the bulk liquid is not as highly influenced by pressure as predicted by the core correlation for nucleate boiling.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Mixing and Heat Transfer Characteristics of Slush Hydrogen; p 27-50
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  • 82
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    Oscillation effects upon film boiling from a sphere. (1972)
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    Publication Date: 2011-08-16
    Description: Heat transfer rates from a silver-plated copper sphere, 0.75 in. in diameter, were studied by high speed photography during oscillations of the sphere in saturated liquid nitrogen and Freon-11. The oscillation frequencies ranged from zero to 13 Hz, and the amplitude-to-diameter ratio varied from zero to 2.67. The sphere was supported by a thin-walled stainless steel tube and carried a thermocouple attached near the lower stagnation point. A Fastax WF-3 16mm movie camera was used at about 2000 frames/sec. The differences in the vapor removal process at lower and higher oscillation frequencies are discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 83
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    The Large Space Telescope program. (1972)
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    Publication Date: 2011-08-16
    Description: The 1980's should see the establishment of the first major observatory in space. This observatory will contain a long-lifetime reflecting telescope of about 120 inches clear aperture. Advantages of an orbiting telescope include the elimination of astronomical seeing effects and improvements in resolving power. The small images and darker sky will permit low-dispersion spectrographs to avoid more of the contaminating background. The crispness of the images also has potential for very efficient high-dispersion spectroscopy. A further advantage lies in the accessibility of all the sky and nearly around-the-clock observing.
    Keywords: SPACE VEHICLES
    Type: Sky and Telescope; 44; Dec. 197
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  • 84
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    Response of convectively controlled burning to nonlinear disturbances. (1972)
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    Publication Date: 2011-08-16
    Description: A process where energy release rate is proportional to the square root of the Reynolds number of a burning particle or surface is used to demonstrate some distinctive dynamic properties of a disturbed convectively controlled burning process. The instantaneous energy release rates caused by assumed periodic flow field disturbances are numerically evaluated and examined. Correlation coefficients which express the energy released in-phase with the pressure disturbance are evaluated and analytical solutions for these coefficients are derived. The response of the process is shown to be highly sensitive to the harmonic distortion of the disturbance. For some disturbances the energy released in-phase with the pressure disturbance is an order of magnitude larger than that for linear (sinusoidal) disturbances. The results show that harmonic distortion increases the coupling between the burning process and the flow field. This amplifying effect of harmonic distortion is suppressed when a disturbance becomes steep-fronted; therefore, steepening can act to limit the equilibrium amplitudes in disturbed systems. Amplification is also suppressed when the velocity disturbance is phase shifted with respect to the pressure disturbance or when the process is exposed to a high steady velocity.
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  • 85
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    Automated techniques for spacecraft monitoring (1972)
    In:  CASI
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    Publication Date: 2012-05-23
    Description: The feasibility of implementing automated spacecraft monitoring depends on four factors: sufficient computer resources, suitable monitoring function definitions, adequate spacecraft data, and effective and economical test systems. The advantages of automated monitoring lie in the decision-making speed of the computer and the continuous monitoring coverage provided by an automated monitoring program. Use of these advantages introduces a new concept of spacecraft monitoring in which system specialists, ground based or onboard, freed from routine and tedious monitoring, could devote their expertise to unprogrammed or contingency situations.
    Keywords: SPACE VEHICLES
    Type: AGARD Automation in Manned Aerospace Systems; 12 p
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  • 86
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    Mechanism problems (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: It is pointed out that too frequently during the design and development of mechanisms, problems occur that could have been avoided if the right question had been asked before, rather than after, the fact. Several typical problems, drawn from actual experience, are discussed and analyzed. The lessons learned are used to generate various suggestions for minimizing mistakes in mechanism design.
    Keywords: SPACE VEHICLES
    Type: NASA. Lyndon B. Johnson Space Center The 7th Aerospace Mech. Symp.; p 3-13
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    Apollo Lunar Module Landing Gear (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The Apollo lunar module landing-gear flight-performance results and three principal gear development problems are discussed. In evaluating the lunar module touchdown performance, strut stroking and toppling stability are the prime factors and are governed primarily by touchdown velocity and surface slope at the touchdown point. Flight results are shown to be well within design values, and the landing-gear has performed successfully in all landings.
    Keywords: SPACE VEHICLES
    Type: The 7th Aerospace Mech. Symp.; p 123-133
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  • 88
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    Dynamic analysis of Apollo-Salyut/Soyuz docking (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of a docking-system computer program in analyzing the dynamic environment produced by two impacting spacecraft and the attitude control systems is discussed. Performance studies were conducted to determine the mechanism load and capture sensitivity to parametric changes in the initial impact conditions. As indicated by the studies, capture latching is most sensitive to vehicle angular-alinement errors and is least sensitive to lateral-miss error. As proved by load-sensitivity studies, peak loads acting on the Apollo spacecraft are considerably lower than the Apollo design-limit loads.
    Keywords: SPACE VEHICLES
    Type: The 7th Aerospace Mech. Symp.; p 47-57
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  • 89
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    The Apollo 15 deployable boom anomaly (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: During the Apollo 15 mission, a boom with an attached mass spectrometer was required to retract periodically so that the instrument would not be in the field of view of other experiments. The boom did not fully retract on five of 12 occasions. Data analysis indicated that the boom probably retracted to within approximately 2.54 centimeters (1 inch) of full retraction. The pertinent boom-design details, the events in the mission related to the anomaly, a discussion of the inflight and postflight investigation of the problem, a discussion of the design changes to the boom mechanism as a result of the investigation, and subsequent flight performance are presented.
    Keywords: SPACE VEHICLES
    Type: the 7th Aerospace Mech. Symp.; p 15-26
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  • 90
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    Skylab (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The Skylab program is presented to show the construction of the space vehicle and the facilities provided. The projects to be conducted during Skylab missions are described. The cost of the program is discussed and plans for future Skylab vehicles and missions are analyzed. Photographs of the interior of Skylab simulators are included to clarify the report.
    Keywords: SPACE VEHICLES
    Type: NASA. Marshall Space Flight Center Space for Mankind's Benefit; p 41-56
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  • 91
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    Unmanned spacecraft for research (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The applications of unmanned spacecraft for research purposes are discussed. Specific applications of the Communication and Navigation satellites and the Earth Observations satellites are described. Diagrams of communications on world-wide basis using synchronous satellites are developed. Photographs of earth resources and geology obtained from space vehicles are included.
    Keywords: SPACE VEHICLES
    Type: NASA. Marshall Space Flight Center Space for Mankind's Benefit; p 23-39
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  • 92
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    The potential impact of the space shuttle on space benefits to mankind (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The potential impact of the space shuttle on space benefits to mankind is discussed. The space shuttle mission profile is presented and the capabilities of the spacecraft to perform various maneuvers and operations are described. The cost effectiveness of the space shuttle operation is analyzed. The effects upon technological superiority and national economics are examined. Line drawings and artist concepts of space shuttle configurations are included to clarify the discussion.
    Keywords: SPACE VEHICLES
    Type: NASA. Marshall Space Flight Center Space for Mankind's Benefit; p 57-76
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  • 93
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    NASTRAN thermal analyzer: A general purpose finite element heat transfer computer program (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The program not only can render temperature distributions in solids subjected to various thermal boundary conditions, including effects of diffuse-gray thermal radiation, but is fully compatible in capacity and in the finite-element model representation with that of its structural counterpart in the NASTRAN system. The development history of the finite-element approach for determining temperatures is summarized. The scope of analysis capability, program structure, features, and limitations are given with the objective of providing NASTRAN users with an overall veiw of the NASTRAN thermal analyzer.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASTRAN: Users' Experiences; p 443-454
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  • 94
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    Experimental thermal mechanics of deployable boom structures (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: An apparatus was developed for thermal distortion measurements on deployable boom structures. The calibration procedure and thermal static bending plus twist measurements are considered. The thermal mechanics test facility is described. A table is presented for several examples of spacecraft applications of thermal static distortion measurements on 3-m deployable booms.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 140-144
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  • 95
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    Two-dimensional finite-element temperature variance analysis (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The finite element method is extended to thermal analysis by forming a variance analysis of temperature results so that the sensitivity of predicted temperatures to uncertainties in input variables is determined. The temperature fields within a finite number of elements are described in terms of the temperatures of vertices and the variational principle is used to minimize the integral equation describing thermal potential energy. A computer calculation yields the desired solution matrix of predicted temperatures and provides information about initial thermal parameters and their associated errors. Sample calculations show that all predicted temperatures are most effected by temperature values along fixed boundaries; more accurate specifications of these temperatures reduce errors in thermal calculations.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 41-44
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  • 96
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    In-orbit flexible spacecraft dynamics program (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A continuous flexible body nonlinear dynamics computer program is used for simulating the spinning mode performance of a spacecraft under applied control torques. The program takes into account the continuous flexible nature of the antennas by representing deflections in terms of shape functions and integrated the spatial dependence in the formulation of the equations of motion. Comparison of RAE flight data on roll, pitch, and yaw with predictions of the computer program in the gravity gradient mode show fair to good agreement in roll and pitch and excellent agreement in the yaw angle.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 30-35
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    Dynamical in-orbit behavior of the Radio Astronomy Explorer satellite (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Onboard sensors and associated ground based processing systems are used to maintain a well stabilized attitude for the RAE 1 in its near circular earth orbit despite the satellite's four extremely long and flexible antenna booms. Boom tip deflection pictures and central hub orientation measurements show that large boom vibrations and major attitude stability problems anticipated prior to launch have not materialized.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 18-22
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  • 98
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    Comparison of satellite theories (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The accuracy of five mathematical models in computing a nominal orbit for the Vanguard 2 satellite by using a position velocity vector is considered. Either numerical integration or analytical theories are used in all models as well as the same force model that corresponds to a potential with the zonal harmonics to order four. The amounts of spread in the values of the total energy and the z-component of the angular momentum for a set of times are considered as measures of accuracy.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 10-13
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    An analysis of the expected eccentricity perturbations for the second Radio Astronomy Explorer (RAE B) (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Analytical prediction of expected eccentricity perturbations for the RAE 2 lunar orbit shows that the eccentricity will grow linearly in time. Parametric inclination studies and analysis of perturbation equations establish a critical retrograde inclination of 116.565 at which the positive perturbation slope vanishes for a circular orbit about 1100 m above the lunar surface with an eccentricity constraint of less than 0.005 during a period of about one year.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 14-17
    Format: application/pdf
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  • 100
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    Space shuttle orbiter handling quality criteria applicable to terminal area, approach, and landing (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An analytical pilot-vehicle study was made to determine the performance criteria for the space shuttle vehicle. Specifications for the flying qualities of piloted aircraft were used for appropriate portions of the space shuttle mission. The handling qualities during the terminal phases of the space shuttle flight were simulated to develop the necessary criteria. Additional criteria required for conditions during the unpowered approach and landing trajectory portion of the flight are explained.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Tech. Conf., vol. 4; p 1239-1263
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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