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  • General Chemistry  (1,021)
  • SPACE VEHICLES  (597)
  • Physics  (555)
  • BIOTECHNOLOGY  (305)
  • STRUCTURAL MECHANICS  (281)
  • THERMODYNAMICS AND COMBUSTION
  • 1970-1974  (3,039)
  • 1945-1949
  • 1972  (3,039)
Collection
Keywords
Publisher
Years
  • 1970-1974  (3,039)
  • 1945-1949
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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    Assessment of advances in structural analysis for space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The latest technology for structural analysis in relation to the design tasks that lie ahead for the space shuttle is reviewed. For shell-of-revolution structures, the analysis can be formulated as a one-dimensional problem which is readily solved by using finite-difference or numerical-integration techniques. For more general asymmetric shells, a two-dimensional formulation is required. However, the governing equations are readily formulated and are amenable to solution by finite-difference techniques. For a completely general structural arrangement, such as structural frameworks, recourse is usually made to discretized formulations using finite elements. Of course, the finite-element programs could be used for shell structures, but at a loss in accuracy and increase in computer time compared with the special purpose programs.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA Space Shuttle Technol. Conf.; p 685-725
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  • 25
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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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  • 26
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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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  • 27
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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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  • 28
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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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  • 29
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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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  • 30
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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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  • 31
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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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  • 32
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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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  • 33
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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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  • 34
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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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  • 35
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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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    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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  • 37
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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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  • 38
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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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  • 39
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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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  • 40
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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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  • 41
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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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  • 42
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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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  • 43
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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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  • 44
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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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  • 45
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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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  • 46
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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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  • 47
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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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  • 48
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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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  • 49
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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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  • 50
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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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  • 51
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    Investigation of traveler acceptance factors in short haul air carrier operations (1972)
    In:  CASI
    Details
    Publication Date: 2006-04-26
    Description: The development of a mathematical model for human reaction to variables involved in transportation systems is discussed. The techniques, activities, and results related to defining certain specific inputs to the model are presented. A general schematic diagram of the problem solution is developed. The application of the model to short haul air carrier operations is examined.
    Keywords: BIOTECHNOLOGY
    Type: NASA. Langley Res. Center Symp. on Vehicle Ride Quality; p 211-228
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  • 52
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    Ride quality research activities at NASA Langley Research Center (1972)
    In:  CASI
    Details
    Publication Date: 2006-04-26
    Description: Ride quality research to determine criteria to describe vehicle performance characteristics which will insure passenger comfort is discussed. The manner in which disciplines of vehicle environmental dynamics, structural dynamics, and electromechanical measurements are combined to define passenger environments is described. The activities of many governmental and private agencies in the field of passenger comfort are examined.
    Keywords: BIOTECHNOLOGY
    Type: Symp. on Vehicle Ride Quality; p 229-246
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  • 53
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    Miniature biotelemeter gives multichannel wideband biomedical data (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: A miniature biotelemeter was developed for sensing and transmitting multiple channels of biomedical data over a radio link. The design of this miniature, 10-channel, wideband (5 kHz/channel), pulse amplitude modulation/ frequency modulation biotelemeter takes advantage of modern device technology (e.g., integrated circuit operational amplifiers, complementary symmetry/metal oxide semiconductor logic, and solid state switches) and hybrid packaging techniques. The telemeter is being used to monitor 10 channels of neuron firings from specific regions of the brain in rats implanted with chronic electrodes. Design, fabrication, and testing of an engineering model biotelemeter are described.
    Keywords: BIOTECHNOLOGY
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 152-166
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  • 54
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    Factors influencing public acceptance of STOL noise (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The responses of people to special noise characteristics associated with short takeoff aircraft are discussed. The findings of studies which have yielded data that may be pertinent to community acceptance of short takeoff aircraft noise are presented. A three step program to evaluate public acceptance of short takeoff aircraft noise was conducted. The three steps were: (1) definition of short takeoff aircraft noise characteristics, (2) laboratory tests to evaluate individual responses, and (3) the use of community survey data to extrapolate conventional takeoff aircraft experience.
    Keywords: BIOTECHNOLOGY
    Type: STOL Technol.; p 353-365
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  • 55
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    Comparison of the sensitivity to rotation of pilots and nonpilots. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Thirty-six airline pilots and 56 nonpilots were tested to determine their sensitivity to rotation. A staircase procedure was used to determine oculogyral illusion and perception of rotation thresholds, in a precision rotation device. The results indicated that (1) there were no significant differences between the two groups for either threshold measure, (2) the thresholds for the oculogyral illusion were significantly lower than the perception of rotation thresholds for both groups, and (3) changes in threshold as a function of age were minimal for 91 of the men. The validity and results of the tests are discussed with regard to the pilot's use of motion information in control tasks for aircraft and simulators.
    Keywords: BIOTECHNOLOGY
    Type: Aerospace Medicine; 43; Jan. 197
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  • 56
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    Passenger fluid volumes measured before and after a prolonged commercial jet flight. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Interstitial and intracellular fluid volumes were calculated from measured plasma volume, extracellular volume and total body water of six subjects before and after a 24-hour commercial overseas flight. No change occurred in these spaces or in peripheral hematocrit or total serum protein concentration. The subjective feeling of dehydration and the actual swelling of the lower extremities characteristically found among passengers at the end of a long trip of this type seems to represent a shift in body fluids to the dependent portions of the body rather than water retention or a decrease in the intravascular water volume.
    Keywords: BIOTECHNOLOGY
    Type: Aerospace Medicine; 43; Jan. 197
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  • 57
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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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  • 58
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    Contamination threats to critical surfaces from handling and storage practices. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of the procedures and results of a program designed to remove the threat of sources of molecular and particulate contamination of critical optical, electrical, and mechanical elements in spacecraft. The results of recent contamination-probing thermal-vacuum tests indicate that some of the materials and practices commonly used to protect critical surfaces from molecular or particulate contamination can themselves represent significant threats. These contamination sources include clean-room and clean-tent materials, gloves, tissues, and covering or packaging materials. Mass and infrared spectral analyses of these materials and the environments and instruments exposed to them show that the contaminants are mostly plasticizers, slip or antistatic agents, and binders used in the manufacture of these products. Products of particular threat include vinyl gloves, boots, clean-tent walls, and some polyethylene sheets and bags. Techniques for reducing these threats are discussed.
    Keywords: BIOTECHNOLOGY
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  • 59
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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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  • 60
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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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  • 61
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    Finite elements of nonlinear continua. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The finite element method is extended to a broad class of practical nonlinear problems, treating both theory and applications from a general and unifying point of view. The thermomechanical principles of continuous media and the properties of the finite element method are outlined, and are brought together to produce discrete physical models of nonlinear continua. The mathematical properties of the models are analyzed, and the numerical solution of the equations governing the discrete models is examined. The application of the models to nonlinear problems in finite elasticity, viscoelasticity, heat conduction, and thermoviscoelasticity is discussed. Other specific topics include the topological properties of finite element models, applications to linear and nonlinear boundary value problems, convergence, continuum thermodynamics, finite elasticity, solutions to nonlinear partial differential equations, and discrete models of the nonlinear thermomechanical behavior of dissipative media.
    Keywords: STRUCTURAL MECHANICS
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  • 62
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    Dynamic response analysis of geometrically non-linear structures subjected to high impact. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Description of an efficient digital computer method for the determination of the propagation of elastic stresses and deformations in certain geometrically nonlinear structures subjected to high impact loading. The finite-element matrix displacement approach utilizing curved quadrilateral shell elements in conjunction with a nodewise predictor-corrector method employing Runge-Kutta extrapolation techniques has been adopted for the present solution. The related computer program written in FORTRAN V for the UNIVAC 1108 computer has proved to be effective for the solution of a range of practical problems including rectangular and cylindrical panels. Numerical results are presented for a relevant structure, the cell container, and the negative electrode of an impact-resistant battery subjected to high impact, simulating its free landing on a planetary surface.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal for Numerical Methods in Engineering; 4; Mar
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  • 63
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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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  • 64
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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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    Shuttle ascent guidance and control. (1972)
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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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    Flying automated laboratories to the planets. (1972)
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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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    Buckling of nearly cylindrical shells under lateral pressure. (1972)
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    Publication Date: 2011-08-16
    Description: The effect of slight meridional curvature on the buckling of shells subjected to an external constant directional lateral pressure is examined. A class of nearly cylindrical shells with constant meridional curvature, a central radius-to-thickness ratio of 500, and central rise-to-shell-length ratios varying from plus 5% to minus 5% is considered. A brief study is presented of the dependence of the critical lateral pressure on the meridional curvature and on the length and meridional edge restraint.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Feb. 197
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    Effect of a slot on the buckling load of a cylindrical shell with a circular cutout. (1972)
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    Publication Date: 2011-08-16
    Description: The results are discussed of a study of the effect of slots on the buckling of cylinders with circular holes of systematically varied circularity. The results obtained suggest that the substantial increase in the buckling loads of cylindrical shells resulting from increases in slot length is due to a relief of the bending stress field.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Feb. 197
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  • 69
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    Experimental investigation of strains in fabric under biaxial and shear forces. (1972)
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    Publication Date: 2011-08-16
    Description: The paper defines the experimental phase of an objective to obtain the mechanical characteristics and coefficients required by the generalized form of Hooke's law for nylon-polyurethane-coated fabric. Test specimens were cylindrical fabric sleeves and were loaded in axial tension by an Instron, in hoop tension by pressurizing, and in shear by a torquing fixture. An extensive amount of strain data is included for a wide combination of the three membrane loads. The tests indicate highly nonlinear stress-strain characteristics of the fabric and a strong dependency on all three membrane loads.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Aircraft; 9; Jan. 197
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  • 70
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    Physical examinations of workers exposed to trichlorotrifluoroethane. (1972)
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    Publication Date: 2011-08-16
    Description: A group of 50 workers, exposed for an average of 2.77 years in an environment, samples of which contained from 46 to 4700 ppm of trichlorotrifluoroethane (Freon 113), was examined. There were no subjective complaints, other than one case of dryness of the skin, referable to this occupational exposure. At this time, it is our opinion that there is no evidence of adverse effects from exposure to trichlorotrifluoroethane under the conditions encountered by these personnel. We believe that continued, periodic, follow-up examinations of these workers will be helpful in further evaluating any possible long-range effects of this material.
    Keywords: BIOTECHNOLOGY
    Type: Archives of Environmental Health; 24; Apr. 197
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  • 71
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    Skylab status report. (1972)
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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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  • 72
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    Small-scale wind shear definition for aerospace vehicle design. (1972)
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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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  • 73
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    Biological experiments - The Viking Mars Lander. (1972)
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    Publication Date: 2011-08-16
    Description: From the biological point of view, the Viking 1975 mission might be regarded as a test of the Oparin-Haldane hypothesis concerning the chemical evolution of living systems. Mars is a planet whose early history was probably similar to that of the earth and whose present environmental conditions may be compatible with the maintenance of living organisms. Thus, the biological experiments aboard the Viking I spacecraft are primarily concerned with the question of whether chemical evolution on Mars took place, and, if so, whether the process reached a level of complexity characteristic of replicating systems.
    Keywords: BIOTECHNOLOGY
    Type: Icarus; 16; Feb. 197
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  • 74
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    Stability of plane Poiseuille flow with heat transfer. (1972)
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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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  • 75
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    Effects of n-dominance and group composition on task efficiency in laboratory triads. (1972)
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    Publication Date: 2011-08-16
    Description: Task-oriented triads were formed into various homogeneous and heterogeneous combinations according to their scores on the n-dominance personality trait of the Edwards Personal Preference Schedule. Five group categories were used. The group task required a consensus decision on each trial. High cooperation and interdependence were reinforced by partially restricting the communication network. Results showed heterogeneous groups significantly better at organizing their group communication processes. They consequently performed the task more efficiently than homogeneous triads.
    Keywords: BIOTECHNOLOGY
    Type: Organizational Behavior and Human Performance; 7; Apr. 197
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    Thermal radiation heat transfer. (1972)
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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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  • 77
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    Sonic-boom-induced building structure responses including damage. (1972)
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    Publication Date: 2011-08-16
    Description: Concepts of sonic-boom pressure loading of building structures and the associated responses are reviewed, and results of pertinent theoretical and experimental research programs are summarized. The significance of sonic-boom load time histories, including waveshape effects, are illustrated with the aid of simple structural elements such as beams and plates. Also included are discussions of the significance of such other phenomena as three-dimensional loading effects, air cavity coupling, multimodal responses, and structural nonlinearities. Measured deflection, acceleration, and strain data from laboratory models and full-scale building tests are summarized, and these data are compared, where possible, with predicted values. Damage complaint and claim experience due both to controlled and uncontrolled supersonic flights over communities are summarized with particular reference to residential, commercial, and historic buildings. Sonic-boom-induced building responses are compared with those from other impulsive loadings due to natural and cultural events and from laboratory simulation tests.
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    Shuttle status report. (1972)
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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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    External auditory canal temperature as an estimate of core temperature. (1972)
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    Publication Date: 2011-08-16
    Description: Measurement of rectal (T sub re), auditory canal (T sub ac), positioned 8 to 10 mm from the tympanic membrane, and mean skin temperature (mean T sub sk) in five men during various exercise regimens at an ambient temperature (T sub a) of 25 C (phase one) and in two men during rest and exercise at 5, 15, 25, and 35 C T sub a (phase two). The purpose was to determine if T sub ac can be used as an accurate estimate of core temperature. Previous observations that T sub ac was highly correlated with T sub re but T sub ac was consistently lower than T sub re are confirmed; the mean difference varied from 0.4 C at rest to 1.1 C at the end of exercise. It is concluded that auditory canal temperature cannot be utilized as an estimate of core temperature, but T sub ac may be used to estimate mean body temperature where very accurate measurements are not required.
    Keywords: BIOTECHNOLOGY
    Type: Journal of Applied Physiology; 32; Feb. 197
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  • 80
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    Establishing an upper bound for window response to the sonic boom. (1972)
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    Publication Date: 2011-08-16
    Description: Study of the failure of glass windows, which is probably the most severe problem confronting the SST program outside of the psychological and sociological aspects. The structural configuration most likely to suffer a window failure due to sonic boom excitation is one representable by a single large room, a single large window, and an open door. It is suggested that if the open door were replaced with another window the resultant stresses in both windows would be substantially reduced.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Sound and Vibration; 21; Mar. 22
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  • 81
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    Automatic surface inoculation of agar trays. (1972)
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    Publication Date: 2011-08-16
    Description: Description of a machine and technique for the automatic inoculation of a plastic tray containing agar media with a culture, using either a conventional inoculation loop or a cotton swab. The design of the machine is simple, it is easy to use, and it relieves the operator from the manual task of streaking cultures. The described technique makes possible the visualization of the overall qualitative and, to some extent, quantitative relationships of various bacterial types in a sample tested.
    Keywords: BIOTECHNOLOGY
    Type: Applied Microbiology; 24; Nov. 197
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    Life detection systems. (1972)
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    Publication Date: 2011-08-16
    Description: Some promising newer approaches for detecting microorganisms are discussed, giving particular attention to the integration of different methods into a single instrument. Life detection methods may be divided into biological, chemical, and cytological methods. Biological methods are based on the biological properties of assimilation, metabolism, and growth. Devices for the detection of organic materials are considered, taking into account an instrument which volatilizes, separates, and analyzes a sample sequentially. Other instrumental systems described make use of a microscope and the cytochemical staining principle.
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  • 83
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    Matrix transformations for spacecraft attitude determination. (1972)
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    Publication Date: 2011-08-16
    Keywords: SPACE VEHICLES
    Type: Planetary and Space Science; 20; Oct. 197
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  • 84
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    Plane elastostatic analysis of V-notched plates. (1972)
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    Publication Date: 2011-08-16
    Description: Solutions are given for several plane elastostatic problems of plates having a V-notch on one edge, and subjected to a variety of boundary conditions. The effect of the magnitude of the V-notch angle and specimen geometry on stress intensity factors KI and KII are obtained for unloaded notch surfaces. There is less than one per cent difference in opening model stress intensity factor in going from a zero degree notch angle to a 30 degree notch angle. Notch opening displacements at the plate edge were measured experimentally, and the results obtained were in excellent agreement with the computed results.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal of Fracture Mechanics; 8; Sept
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  • 85
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    An integrated medical system for long-duration space missions. (1972)
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    Publication Date: 2011-08-16
    Description: A description is given of the Integrated Medical and Behavioral Laboratory Measurement System (IMBLMS) being developed for onboard medical support of the crew and for medical research during space missions. The system is suitable for use during early extended space flights and for accommodating measurement and diagnostic apparatus as well as treatment and surgical facilities developed for later missions.
    Keywords: BIOTECHNOLOGY
    Type: Journal of Spacecraft and Rockets; 9; Aug. 197
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    Study of fatigue crack initiation from flaws using fracture mechanics theory. (1972)
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    Publication Date: 2011-08-16
    Keywords: STRUCTURAL MECHANICS
    Type: Engineering Fracture Mechanics; 4; June 197
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  • 87
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    Panel-flutter analysis of a thermal protection-shield concept for the space shuttle. (1972)
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    Publication Date: 2011-08-16
    Description: Analysis of the panel flutter characteristics of a candidate thermal protection system (TPS) for the space shuttle, using piston theory aerodynamics and Lagrange equations. The results show the TPS candidate panel array to be deep in the 'no-flutter' region during launch and, therefore, safe from panel flutter.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Aug. 197
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  • 88
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    Rayleigh wave effects in an elastic half-space. (1972)
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    Publication Date: 2011-08-16
    Description: Consideration of Rayleigh wave effects in a homogeneous isotropic linearly elastic half-space subject to an impulsive uniform disk pressure loading. An approximate formula is obtained for the Rayleigh wave effects. It is shown that the Rayleigh waves near the center of loading arise from the portion of the dilatational and shear waves moving toward the axis, after they originate at the edge of the load disk. A study is made of the vertical displacement due to Rayleigh waves at points on the axis near the surface of the elastic half-space.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Aug. 197
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  • 89
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    Strongly coupled stress waves in heterogeneous plates. (1972)
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    Publication Date: 2011-08-16
    Description: Consideration of coupled stress waves generated by an impulsive load applied at one end of a semiinfinite plate. For the field equations governing the one-dimensional coupled waves a hyperbolic system of equations is obtained in which a strong coupling in the second derivatives exists. The method of characteristics described by Chou and Mortimer (1967) is extended to cover the case of strong coupling, and a study is made of the transient stress waves in a semiinfinite plate subjected to an initial step input. Coupled discontinuity fronts are found to propagate at different velocities. The normal plate stress and the bending moment at different time regimes are illustrated by graphs.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Aug. 197
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    A review of film boiling at cryogenic temperatures. (1972)
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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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    Orbital propellant depot system. (1972)
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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.
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  • 92
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    Minimum weight passive insulation requirements for hypersonic cruise vehicles. (1972)
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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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  • 93
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    A halo-orbit lunar station. (1972)
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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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    Self-contamination and environment of an orbiting satellite. (1972)
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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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  • 95
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    Thin-film light-intensity measurement strain-analysis technique. (1972)
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    Publication Date: 2011-08-16
    Description: The optical response to loading of a thin metallic film deposited on a low-modulus structural substrate is studied theoretically and experimentally. Two types of optical properties called total and central-image transmittance (or reflectance) are shown to be related to the mechanical state of the substrate. Empirical optical-mechanical relationships are proposed between these optical properties and the substrate strain field of a general plane-stress problem. A technique based on wrinkle and microfracture patterns is described for determining principal directions of strain. Experimental results for uniaxially loaded specimens show that it is possible to obtain a nearly linear relationship between transmittance and strain for certain materials combinations.
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  • 96
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    A non-linear dynamic lumped-parameter model of a rectangular plate. (1972)
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    Publication Date: 2011-08-16
    Description: A lumped-parameter model of a rectangular plate is developed by assuming fundamental mode solutions and using Hamilton's Principle and the Euler equations to set up the differential equation of motion for the system. The plate theory used may be described as the dynamic analogue of the von Karman large-deflection theory. Four sets of symmetrical boundary conditions are considered with the restriction of uniform pressure dynamic loads. The model takes the form of a mass on a cubic-hardening spring with each term defined by algebraic expressions of the plate parameters. The results for some specific problems are compared with two previous solutions. This method is less accurate but simpler to develop and apply.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Sound and Vibration; 21; Apr. 8
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    Solution of eigenvalue problems by Sturm sequence method. (1972)
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    Publication Date: 2011-08-16
    Description: A generalized eigenvalue algorithm is presented herein along with the complete listing of the associated computer program, which may be conveniently utilized for the efficient solution of certain broad classes of eigenvalue problems. Extensive applications of the procedure are envisaged in the analysis of many important engineering problems, such as stability and natural frequency analysis of practical discrete structural systems, idealized by the finite element technique. The procedure based on the Sturm sequence method is accurate and fast, possessing several significant advantages over other known methods of such analysis. Numerical results are also presented for two representative structural engineering problems.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal for Numerical Methods in Engineering; 4; May-June
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    Spacecraft sterilization. (1972)
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    Publication Date: 2011-08-16
    Description: Spacecraft sterilization is a vital factor in projects for the successful biological exploration of other planets. The microorganisms of major concern are the fungi and bacteria. Sterilization procedures are oriented toward the destruction of bacterial spores. Gaseous sterilants are examined, giving attention to formaldehyde, beta-propiolactone, ethylene oxide, and the chemistry of the bactericidal action of sterilants. Radiation has been seriously considered as another method for spacecraft sterilization. Dry heat sterilization is discussed together with the effects of ethylene oxide decontamination and dry heat sterilization on materials.
    Keywords: BIOTECHNOLOGY
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  • 99
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    Unknown
    Lateral expansion of a laser-supported detonation wave in a gas. (1972)
    In:  Other Sources
    Details
    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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  • 100
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    Effect of a circular hole on the buckling of cylindrical shells loaded by axial compression. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An experimental and analytical investigation of the effect of a circular hole on the buckling of thin cylindrical shells under axial compression was carried out. The experimental results were obtained from tests performed on seamless electroformed copper shells and Mylar shells with a lap joint seam. These results indicated that the character of the shell buckling was dependent on a parameter which is proportional to the hole radius divided by the square root of the product of the shell radius and thickness. For small values of this parameter, there was no apparent effect of the hole on the buckling load. For slightly larger values of the parameter, the shells still buckled into a general collapse configuration, but the buckling loads were sharply reduced as the parameter increased. For still larger values of the parameter, the buckling loads were further reduced, and the shells buckled into a stable local buckling configuration.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Nov. 197
    Format: text
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