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  • General Chemistry  (921)
  • SPACE VEHICLES  (556)
  • PROPULSION SYSTEMS  (295)
  • Cell & Developmental Biology
  • 1970-1974  (1,971)
  • 1910-1914
  • 1973  (1,971)
Collection
Keywords
Publisher
Years
  • 1970-1974  (1,971)
  • 1910-1914
Year
  • 1
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    Investigation of the possibility of use of vibroacoustical signals for purposes of diagnostics in aeronautical engineering (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The application of vibroacoustic techniques for diagnosing aircraft engine malfunctions is discussed. An experiment was conducted to determine the defects introduced by the nature of change in the amplitude-frequency characteristics of the noises and vibrations of an aircraft jet engine. The manner in which the defects were simulated is explained. The test equipment used during the experiment is identified. The results of the amplitude-frequency characteristics investigation are summarized to show optimum location of the microphone pick-up to record the acoustic data.
    Keywords: PROPULSION SYSTEMS
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 317-319
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  • 2
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    The problem of carrying out a diagnosis of an internal combustion engine by vibroacoustical parameters (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The physics of noise formation in an internal combustion engine is discussed. A dependence of the acoustical radiation on the engine operating process, its construction, and operational parameters, as well as on the degree of wear on its parts, has been established. An example of tests conducted on an internal combustion engine is provided. A system for cybernetic diagnostics for internal combustion engines by vibroacoustical parameters is diagrammed.
    Keywords: PROPULSION SYSTEMS
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 247-249
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  • 3
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    Development of propulsion for high atmospheric pressure or dense environments (1973)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: The development of a propulsion system that employs a detonating propellant is described, and the need for such a system and its use in certain planetary atmospheres are demonstrated. A theoretical formulation of the relevant gas-dynamic processes was developed, and a related series of experimental tests were pursued.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 45-52
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  • 4
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    Miscellaneous losses (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The boundary-layer losses associated with the flow process in the blade channel are discussed. To determine the overall design point efficiency of a turbine, other losses must also be considered; these include tip clearance loss and disk friction loss. The sum of these losses normally comprises all the losses that are considered in the design of a full admission axial flow turbine. If, however, a partial admission turbine is being considered, there are additional losses that must be included. The partial admission losses usually considered are the pumping loss in the inactive blade channels and the filling-and-emptying loss in the blade passages as they pass through the admission arc. Finally, a loss that occurs at off-design operation of any turbine is the incidence loss.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 2; p 125-148
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  • 5
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    Channel flow analysis (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The design of a proper blade profile requires calculation of the blade row flow field in order to determine the velocities on the blade surfaces. An analysis theory is presented for several methods used for this calculation and associated computer programs that were developed are discussed.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 2; p 27-56
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  • 6
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    Blade design (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The design of turbine blading is considered that will produce the flow angles and velocities required by velocity diagrams consistent with the desired efficiency and/or number of stages. The determination of the size, shape, and spacing of the blades is fundamental.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl. Vol. 2; p 1-25
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  • 7
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    Operation of small rocket engines in the JPL high-vacuum molecular space simulator (Molsink) (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-10
    Description: The feasibility of operating small rocket engines in the Molsink facility was demonstrated. A 0.44-N (0.1-lbf) hydrazine engine and a 0.18-N (0.04-lbf) thruster using cold gas from a hydrazine plenum system were operated for both flight duty cycles and off-nominal conditions. The exhaust gases from these thrusters contain NH3, N2, and H2. The chamber was also calibrated for larger bipropellant engines using nitrogen tetroxide/monomethyl hydrazine (NTO/MMH). The exhaust products of these engines contain CO2, CO, H2, H2O, and H2. A mixture of cold gases simulating the engine exhaust was injected through a nozzle under conditions simulating thrust levels up to 26.7-N (6 lbf). Pulsing and continuous operations were investigated. The chamber background pressure traces were compared with the traces obtained for the same thrusters operated with pure nitrogen at approximately equivalent thrust. Satisfactory recuperation times were encountered in all the pulsing modes. Test times greater than 20s were obtained in steady state operation before the vacuum chamber back pressure climbed to prohibitive values.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quart. Tech. Rev., Vol. 3, No. 1; p 1-13
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  • 8
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    Chemical propulsion - The old and the new challenges (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The historical background concerning the application of liquid propellant rockets is considered. Progress to date in chemical liquid propellant rocket engines can be summarized as an increase in performance through the use of more energetic propellant combinations and increased combustion pressure. New advances regarding liquid propellant rocket engines are related to the requirement for reusability in connection with the development of the Space Shuttle.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Student Journal; 11; Dec. 197
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  • 9
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    Attitude control of a spinning flexible spacecraft (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The dynamics of rotational motion of a spinning orbiting spacecraft consisting of two rigid bodies connected by a flexible joint and arbitrary number of flexible appendages (two of which are flexible massless booms having masses on their tips) is analyzed. Active attitude control is provided by momentum exchange devices (e.g. control moment gyroscopes) or a mass expulsion system. The linearized equations of motion describing the vehicle are presented, and a large scale digital simulation that has been developed at the Marshall Space Flight Center is presented. A simplified model of the geometrically complex vehicle is selected to make it analytically tractable. The simplified model consists of a single rigid core body with two attached flexible massless booms having tip masses. The states of the vehicle are defined as small perturbations about its steady-state spin. An analysis is performed to determine the domain of stability.
    Keywords: SPACE VEHICLES
    Type: Computer and Electrical Engineering; 1; Dec. 197
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  • 10
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    Technology for low noise aircraft - The NASA Quiet Engines (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of the major goals, procedures, and results of the Quiet Engine Program that was initiated four years ago and is now nearing completion. This program has developed and demonstrated, in full-scale, experimental engine tests, technology advances which, if applied to the design of future aircraft, will help produce equipment with noise levels considerably lower than the older narrow-body aircraft and significantly lower than the new wide-body aircraft flying at present. However, the application of this noise reduction technology will result in increases in aircraft operating costs. Future aircraft noise reduction research should, therefore, consider improvements in the economics associated with noise reduction technology.
    Keywords: PROPULSION SYSTEMS
    Type: Noise Control Engineering; 1; Autumn 1
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  • 11
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    New horizons in chemical propulsion (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: After a review of the work of the late-Fifties on free radicals for propulsion, it is concluded that atomic hydrogen would provide a potentially large increase in specific impulse. Work conducted to find an approach for isolating atomic hydrogen is considered. Other possibilities for obtaining propellants of greatly increased capability might be connected with the technology for the generation of activated states of gases, metallic hydrogen, fuels obtained from other planets, and laser transfer of energy.
    Keywords: PROPULSION SYSTEMS
    Type: Astronautics and Aeronautics; 11; Dec. 197
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  • 12
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    Effect of shear on duct wall impedance. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The solution to the equation governing the propagation of sound in a uniform shear layer is expressed in terms of parabolic cylinder functions. This result is used to develop a closed-form solution for acoustic wall impedance which accounts for both the duct liner and the presence of a boundary layer in the duct. The effective wall impedance can then be used as the boundary condition for the much simpler problem of sound propagation in uniform flow.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Sound and Vibration; 30; Sept. 8
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  • 13
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    SSS-A spacecraft and experiment description. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The scientific objectives of the Explorer-45 mission are discussed. The primary objective is the study of the ring current responsible for the main phase of magnetic storms. Closely associated with this objective is the determination of the relationship between magnetic storms, substorms, and the acceleration of charged particles in the magnetosphere. Further objectives are the measurement of a wide range of proton, electron and alpha-particle energies, and studies of wave-particle interactions responsible for particle transport and loss in the inner magnetosphere. The orbital parameters, the spacecraft itself, and some of its unique features, such as the data handling system, which is programmable from the ground, are described.
    Keywords: SPACE VEHICLES
    Type: Journal of Geophysical Research; 78; Aug. 1
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  • 14
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    Mach number and Reynolds number effect on orbiter/tank interference heating. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Analysis of the variations in orbiter/tank interference heating rates in the Space Shuttle configuration at M numbers up to 19 and Re numbers down to 250,000. Experimental data on heat transfer rate distribution in the tank and on orbiter-induced interference heat transfer factors in the tank are included in diagrams. The data suggest that the primary effect of interference can be a fully developed turbulent boundary layer.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 10; Aug. 197
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  • 15
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    Fuel-optimal angular momentum vector control for spinning and dual-spin spacecraft. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The problem of fuel-optimal small-angle reorientation of the spin axis of a spinning or dual-spin spacecraft is examined. The results obtained show significant improvements over previously published optimization studies by virtue of the introduction of two innovations: (1) mass-explusion active control is utilized for angular momentum vector pointing only, with passive damping relied upon for stable vehicles to attenuate vehicle coning about the angular momentum vector, so that the task of the active controller changes from spin axis control to angular momentum vector control, and (2) several options are considered for type, number, and location of attitude control jets. The first of these considerations introduces a target set which is a smooth, two-dimensional linear manifold in the four-dimensional state space, whereas previous studies have adopted the origin as the target set. The second innovation amounts to consideration of a spectrum of control restraint sets.
    Keywords: SPACE VEHICLES
    Type: Astronautica Acta; 18; June 197
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  • 16
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    Lower payload costs through refurbishment and module replacement. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Payload benefits to be derived from refurbishment can be related to individual spacecraft programs directly and for planning purposes to the entire shuttle mission model. In the case of the large space telescope program, cost savings obtained through the use of the shuttle for maintenance operations have been estimated to be in the range from 30 to 40%. This saving is realized over an operational lifetime of 15 years by reducing, through refurbishment on orbit, the number of flight units along with 'optimized' reliability goals commensurate with periodic maintenance revisits at one-year intervals. Shuttle-era payload implications are discussed together with a pressurized on-orbit maintenance configuration, an earth observation satellite, and some typical teleoperator-serviced spacecraft.
    Keywords: SPACE VEHICLES
    Type: Astronautics and Aeronautics; 11; May 1973
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  • 17
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    The cylindrical electrostatic probes for Atmosphere Explorer -C, -D, and -E. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: This paper briefly describes the cylindrical electrostatic probes to be used on the new Atmosphere Explorer-C, -D, and -E, and outlines the methods to be employed to analyze the experimental data in terms of electron temperature and ion and electron concentration. Two independent cylindrical sensors and partially redundant electronic systems permit greater reliability in measurements. Measurements are made at 1-sec and 2-sec intervals along the orbit. The sensors themselves have been modified from previous applications to cope with the lower electron temperature expected in these low-altitude orbits and to counter possible surface contamination caused by the hydrazine engines used for orbit adjustments.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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  • 18
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    A neutral-atmosphere composition experiment for the Atmosphere Explorer-C, -D, and -E. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The neutral-atmosphere composition experiment instrumentation is designed to obtain in-situ measurements of neutral thermosphere composition from Atmosphere Explorer-C, -D, and -E. The system is based on previously flown OGO-6 and San Marco-3 composition instruments. The mass-spectrometer sensor includes a gold-plated thermalizing chamber and ion source, a hyperbolic rod quadrupole analyzer, and an off-axis electron multiplier. Automatic ion-source sensitivity control and pulse-counting techniques provide density measurement capability from approximately 125 to 1000 km altitude. The normal operating mode includes measurement at all masses in the range of 1 to 44 amu, with emphasis on hydrogen, helium, oxygen, nitrogen, and argon.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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  • 19
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    Space science plans for the shuttle era. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Three separate and distinct modes of using the space shuttle system have been identified. These modes include the boost of a spacecraft plus one or more propulsion stages into earth orbit or parking orbit, the establishment and maintenance of automated observatories in space, and the support of exploratory research and instrument development. Studies show that approximately 60% of all planned NASA missions require a shuttle third stage. Illustrations are presented to show how the largest spacecraft, Viking, and its propulsion system, Centaur, and a communications satellite, with an Agena stage to place it into a geostationary orbit, would fit into the shuttle. Results of the NASA Shuttle Sortie Workshop studies are discussed together with prospects of European cooperation in future workshop experiments.
    Keywords: SPACE VEHICLES
    Type: Astronautics and Aeronautics; 11; May 1973
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  • 20
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    Airborne-science techniques aid Shuttle planning. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: In the sortie mode the Shuttle bay becomes a laboratory for a wide variety of space experiments and observations. Scientists and engineers can man this laboratory for investigations conducted in a space environment. A special program, called ASSESS (Airborne Science/Shuttle Experiment System Simulation) has been instituted to conduct exhaustive studies of the airborne-science concept as it may apply to Shuttle planning. The ASSESS program is described in detail together with the airborne-science operation pertinent to the Shuttle. Similarities of airborne science aircraft to the Shuttle are considered along with the results of a simulation mission, flown in October 1972.
    Keywords: SPACE VEHICLES
    Type: Astronautics and Aeronautics; 11; May 1973
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  • 21
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    An extreme UV photometer for solar observations from Atmosphere Explorer. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A broadband photometer experiment is being prepared for the Atmosphere Explorer-C, -D, and -E missions to record the solar irradiance in seven wavelength bands in the range from 40 to 1250 A. The experiment contains four spiral electron multipliers located behind a moving eight-position filter wheel. Six of the eight sections of this wheel contain metallic filters used to spectrally isolate the solar irradiance. In addition, three Al2O3 diodes, two with filters, are being used to record the solar irradiance over the full range of orbital altitudes including those at which operation of multipliers with high voltages on open structures would be unsafe. A principal goal of the experiment will be to measure time dependence of the solar irradiance.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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  • 22
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    The Bennett ion-mass spectrometer on Atmosphere Explorer-C and -E. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The Bennett spectrometer to be flown on Atmosphere Explorer-C and -E (AE-C and AE-E) is designed to measure, throughout the 120 to 4000-km orbit, the concentrations of all thermal positive ions in the mass range 1 to 72 amu and number density range 5 to 5,000,000 ions per cu cm. To reduce the buildup of ram pressure and facilitate measurements at low altitude, the analyzer is vented, and a multigrid ion-current collector is employed. An extensive command capability permits optimization of instrument parameters for particular measurement objectives; commandable functions include mass-scan range and period, the sensitivity-resolution characteristic of the analyzer, orifice potential, and in-flight calibration.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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  • 23
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    Advances in modeling aerodynamic decelerator dynamics. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The Viking entry vehicle uses a lines-first type of deployment in which the parachute, packed in a deployment bag, gets ejected rearward from the vehicle by a mortar. As the bag moves rearward, first the lines are unfurled and then the canopy. An analysis of the unfurling process is conducted, giving attention to longitudinal and rotational dynamics. It is shown that analytical modeling of aerodynamic systems provides significant information for a better understanding of the physics of the deployment process.
    Keywords: SPACE VEHICLES
    Type: Astronautics and Aeronautics; 11; Apr. 197
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  • 24
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    A Geopause satellite system concept. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The Geopause satellite system concept offers promising approaches in connection with four different problem areas. A typical Geopause satellite orbit has a 14-hour period, a mean height of about 4.6 earth radii, and is nearly circular, polar, and normal to the ecliptic. At this height only a relatively few gravity terms have uncertainties corresponding to orbital perturbations above the decimeter level. The Geopause satellite system also provides the tracking geometery and coverage needed for determining the orbit, the tracking system biases, and the station locations. Studies indicate that the Geopause satellite, tracked with a 2-cm ranging system from nine NASA affiliated sites, can yield decimeter station location accuracies. Five or more fundamental stations well distributed in longitude can view Geopause over the North Pole. This means not only that redundant data are available for determining tracking system biases, but also that both components of the polar motion can be observed frequently. When tracking Geopause, the NASA sites become a two-hemisphere configuration which is ideal for a number of earth physics applications such as the observation of the polar motion with a time resolution of a fraction of a day.
    Keywords: SPACE VEHICLES
    Type: Space Science Reviews; 14; Feb. 197
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  • 25
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    Joint US/Soviet docking mission. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The purpose and objectives of the joint Apollo/Soyuz experimental test flight, the technical requirements and anticipated solutions necessary to meet the objectives, the mission plan, the flight vehicles, the schedule, and the expected results of successfully completing such a project are discussed. The androgynous feature of the docking system is provided by a symmetrical distribution of all elements which are directly connected during docking, relative to the axis of reverse symmetry. Both the American and Russian systems are designed to serve as either the active or passive system for docking and undocking.
    Keywords: SPACE VEHICLES
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  • 26
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    Status report on shuttle program. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Following a brief summary of previous work, major attention is given to Phase-B extension, the Request for Proposal (RFP), the selected configuration and associated activities, and the future. NASA extended Phase-B contracts to examine other options that might lower peak annual funding and decrease program risk. Most of the discussion deals with the shuttle and orbiter systems. The efforts of the shuttle program in the past year have seen the completion of numerous trade studies and the selection of a prime shuttle contractor.
    Keywords: SPACE VEHICLES
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  • 27
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    Status report on Skylab project. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The major objectives of the Skylab project are to examine the medical aspects of what happens to man in long duration space flight, to make long-duration studies of the active and the quiet sun, and to gather data in the study of the ocean and the land masses of the earth. Corollary experiments use either the fact that they are to be performed in a complete vacuum, or the fact that the stars and the ultraviolet can be much more extensively studied. Some experiments in metal processing will make use of the zero force field.
    Keywords: SPACE VEHICLES
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  • 28
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    Results of Apollo 16. (1973)
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    Publication Date: 2011-08-16
    Description: The results of the Apollo 16 mission are summarized, and the present level of hardware and procedures maturity is illustrated. The primary objective was to obtain a sample of the lunar highlands. It appears that the moon and its history are too complex to be explained by any of the models currently available. Contingency plans fell into three categories: (1) emergency recovery from a hazardous situation, (2) alternate plans to maximize the mission return following a hardware malfunction, and (3) alternate procedures to work around specific problems. Operational experience indicates that it is better to execute a plan with some known disadvantages than to replace it with one which has some apparent advantages but is not thoroughly understood.
    Keywords: SPACE VEHICLES
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  • 29
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    Performance of a modified downstream-cathode MPD thruster. (1973)
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    Publication Date: 2011-08-16
    Description: Discussion of the improvements incorporated since 1969 in a low-power MPD thruster design which is considered a potential candidate for satellite station keeping and attitude control. The improvements include a new cathode design, and changes in thruster geometry, with xenon used as the propellant. A better thermal design is found to be necessary for further improvement of the thruster.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Spacecraft and Rockets; 10; Jan. 197
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  • 30
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    Low-energy electron experiment for Atmosphere Explorer-C and -D. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The low-energy electron experiment will provide differential measurements of the energy influx and angular distributions of electrons and protons on the Atmosphere Explorer-C and -D missions. The detectors consist of cylindrical electrostatic analyzers for species and energy selection and Spiraltron electron multipliers as particle sensors. The C version will contain three detectors, two measuring electrons and protons from 0.2 to 25 keV in 16 logarithmically spaced steps and one measuring 5 keV electrons continuously. Angular distributions will be acquired utilizing the spin of the spacecraft. The D version will contain 19 detectors, one proton-stepped energy analyzer, and two electron-stepped energy analyzers at two different angles, again over the energy range 0.2 to 25 keV.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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  • 31
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    The Atmosphere Explorer spacecraft system. (1973)
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    Publication Date: 2011-08-16
    Description: Brief description of the design goals, spacecraft, data system, and data analysis concept for the Atmosphere Explorer (AE) mission. The AE mission is shown to have been conceived and to be implemented for making possible a variety of studies of the lower thermosphere. The spacecraft support system, including an onboard propulsion system, will enable investigations to be carried out deep in the thermosphere and at all points of aeronomic significance about the earth.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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  • 32
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    The neutral-atmosphere temperature instrument. (1973)
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    Details
    Publication Date: 2011-08-16
    Description: The determination of the temperature of the neutral gas at the location of the satellite is based on measurement of the velocity distribution of the molecular nitrogen. Measurement of the thermal-velocity component in the presence of the free-stream velocity will be obtained through application of the velocity-scan technique and, independently, through use of a baffle technique. A 3-cm diameter spherical sampling chamber with a 0.5-cm diameter precisely knife-edged orifice is located at the satellite equator to permit free diffusion of atmosphere gases between the chamber interior and the atmosphere. The spherical chamber is connected through a high-conductance tube to a quadrupole mass-spectrometer sensor to permit accurate quantitative evaluation of the density of the gas.
    Keywords: SPACE VEHICLES
    Type: Radio Science; 8; Apr. 197
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    A Quiet Engine for stilling complaints. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Two experimental Quiet Engines using derated CF6 cores are discussed. One engine has a low-speed fan running at a tip speed of 1160 fps; the other engine has a fan running at the high speed of 1550 fps. The two engines are expected to show the relative advantages of fans operating at low tip speeds with high lift coefficients in comparison with fans operating at high tip speeds with low lift coefficients. Test results obtained with full-scale (6-ft diameter) fans are examined.
    Keywords: PROPULSION SYSTEMS
    Type: Astronautics and Aeronautics; 11; Jan. 197
    Format: text
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    Design and evaluation of combustors for reducing aircraft engine pollution (1973)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: Various techniques and test results are briefly described and referenced for detail. The effort arises from the increasing concern for the measurement and control of emissions from gas turbine engines. The greater part of this research is focused on reducing the oxides of nitrogen formed during takeoff and cruise in both advanced CTOL, high pressure ratio engines, and advanced supersonic aircraft engines. The experimental approaches taken to reduce oxides of nitrogen emissions include the use of: multizone combustors incorporating reduced dwell time, fuel-air premixing, air atomization, fuel prevaporization, water injection, and gaseous fuels. In the experiments conducted to date, some of these techniques were more successful than others in reducing oxides of nitrogen emissions. Tests are being conducted on full-annular combustors at pressures up to 6 atmospheres and on combustor segments at pressures up to 30 atmospheres.
    Keywords: PROPULSION SYSTEMS
    Type: AGARD Atmospheric Pollution by Aircraft Engine; 8 p
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  • 35
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    Engine selection for transport and combat aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: The procedures for selecting engines for transport and combat aircraft during the design process are presented. The types of aircraft considered are: (1) a long haul conventional takeoff and landing transport, (2) a short haul vertical takeoff and landing transport, (3) a long range supersonic transport, and (4) a fighter aircraft. The influence of aircraft noise considerations on engine selection is examined. The aerodynamic characteristics of supercritical wings and their effect on engine selection are reported.
    Keywords: PROPULSION SYSTEMS
    Type: AGARD Aircraft Performance: Prediction Methods and Optimization; 55 p
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    Systems performance monitoring for advanced manned spacecraft (1973)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: Optimum system mechanizations for advanced manned spacecraft are considered. Several studies have proposed automation of the onboard system management task, with functions such as system status monitoring, configuration management, and redundancy management being accomplished under computer control. An experimental system was used in the laboratory to investigate hardware and software requirements for accomplishing these onboard system management functions. A performance monitor system is proposed for the space shuttle. This system provides support to the flight crew in the management of all onboard systems but does not perform critical switching functions during the flight phase.
    Keywords: SPACE VEHICLES
    Type: AGARD Automation in Manned Aerospace Systems; 16 p
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    Spectroscopy of Project Fire 1, April 14, 1964 (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Fire 1 test was designed to study the heating of an Apollo-type reentry vehicle. The total reentry complex weighed approximately 230 kg and entered the upper atmosphere at a velocity of 11.5 km/s. The spectrum of the reentry complex has been studied in the wavelength range 3700 to 8800 A, where 102 multiplets of 21 atoms and the band systems of 5 diatomic molecules have been identified. Comparisons with meteor spectra are made.
    Keywords: SPACE VEHICLES
    Type: NASA, Washington Evolutionary and Phys. Properties of Meteoroids; p 161-167
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  • 38
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    Optical module for the integrated real-time contamination monitor (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The concept of a real time contamination monitor is studied and the evolution of the optical module component from laboratory model through the engineering evaluation model is reported. Mechanisms employed and problems experienced are described. Current efforts are directed toward a major simplification of design in a unit intended for flight.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center The 8th Aerospace Mech. Symp.; p 271-281
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  • 39
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    Spacecraft separation systems mechanisms: Characteristics/performance during high altitude flight test from NASA Wallops Station, Va. (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The applications of various separation mechanisms to meet flight mission goals within the physical and environmental constraints of a single stage rocket test vehicle are considered. Each separation concept was selected from the numerous choices available on the basis of its unique requirement and the flight test vehicle incorporated several different concepts. Attention to specific requirements and thoroughness in design and testing were essential to success since there is no specific single answer to separation problems.
    Keywords: SPACE VEHICLES
    Type: The 8th Aerospace Mech. Symp. te; p 165-178
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  • 40
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    The requirement for designing analyzable space deployable structures (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The applied technology satellite parabolic reflector subsystem is one of the first systems designed for space environment with limited terrestrial environmental ability. As a result, the complete performance of the system could not be demonstrated in a terrestrial environment without unacceptable design compromises. This problem was circumvented by developing a test philosophy which relied heavily on analysis to qualify and accept the flight hardware. The test program was successfully concluded and an optimized, low cost structure resulted. It is felt that this test and analysis philosophy can be applied to future space systems, resulting in substantial cost and schedule savings and a mission optimized system.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center The 8th Aerospace Mech. Symp.; p 351-362
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  • 41
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    Secondary mirror support (LST) (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Large structural mirror supports which meet the stiff requirements for launch and orbit operations in particular, dimensionally stable structures made of titanium alloy, can be manufactured with present day technology and at reasonable cost. With continuing research and development in this area, designs of astronomical telescopes and related earth observatory satellites should benefit from this knowledge.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., 1972; p 45-48
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  • 42
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    Results of Mariner Mars tracking calibration experiment (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Ground station network S-band tracking in three-way Doppler modes of Mariner 9 in deep space provided geodetic parameters with an accuracy of 15 meters for use in Apollo 16 and Apollo 17 programs. It was concluded that unified S-band Doppler data provide geodetic results with accuracies comparable to laser ranging data.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., 1972; p 121-124
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    The International Ultraviolet Explorer (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The International Ultraviolet Explorer is a new astronomical satellite still in the design stage. It is a Delta launched satellite, weighing approximately 365 kilograms, with an intended lifetime of three to five years, and it will serve as a precursor to the large space telescope. The essential features of the satellite are its geosynchronous orbit, a 45-centimeter aperture telescope, and a high performance UV spectrograph using television tubes as detectors.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., 1972; p 86-88
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  • 44
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    The GSFC cosmic radiation experiment for the Pioneer F/G Jupiter mission (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The extremely lightweight, low power design of the cosmic radiation experiment is obtained by using less than 10 percent of the total weight for the mechanical system. Both the baseplate and the top plate are aluminum honeycomb, the side panels are magnesium trusswork, and the inside circuitry is stacked like a sandwich and interleaved with polyester urethane foam for vibration damping. The flight performance of the experimental hardware is excellent.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., 1972; p 82-85
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  • 45
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    Gravity-gradient dynamics experiments performed in orbit utilizing the Radio Astronomy Explorer (RAE-1) spacecraft (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Six dynamic experiments were performed in earth orbit utilizing the RAE spacecraft in order to test the accuracy of the mathematical model of RAE dynamics. The spacecraft consisted of four flexible antenna booms, mounted on a rigid cylindrical spacecraft hub at center, for measuring radio emissions from extraterrestrial sources. Attitude control of the gravity stabilized spacecraft was tested by using damper clamping, single lower leading boom operations, and double lower boom operations. Results and conclusions of the in-orbit dynamic experiments proved the accuracy of the analytic techniques used to model RAE dynamical behavior.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., 1972; p 32-36
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  • 46
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    Delta vehicle improvements (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Delta vehicle performance increases associated with 14 major configuration changes are outlined in terms of spacecraft weight into synchronous transfer orbit. Also discussed is the per-mission cost history, except range cost and amortization of development.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., 1972; p 11-13
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  • 47
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    The OSO-7 mission (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Addition of a gyro and star sensor to the wheel section of OSO-G provided nighttime pointing capability and functional redundancy in correcting an anomaly that put the combined OSO spacecraft and launch vehicle into a flat spin.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., 1972; p 7-10
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  • 48
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    Velocity control propulsion subsystem of the Radio Astronomy Explorer satellite for Goddard Space Flight Center (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Velocity Control Propulsion Subsystem (VCPS) was designed the propulsion required for trajectory and lunar orbit corrections of the spacecraft. A GFE clamp assembly physically attaches the VCPS to the spacecraft and the unit is ejected after completing the required corrections. The VCPS is physically and functionally separated from the spacecraft except for the electrical and telemetry interfaces. A GFE transtage provides the superstructure on which the VCPS is assembled. The subsystem consists of two 5 foot pound rocket engine assemblies, 4 propellant tanks, 2 latching valves, 2 fill and drain valves, a system filter, pressure transducer, gas and propellant manifolds and electrical heaters and thermostats. The RAE-B VCPS program covered the design, manufacture and qualification of one subsystem. This subsystem was to be manufactured, subjected to qualification tests; and refurbished, if necessary, prior to flight. The VCPS design and test program precluded the need for refurbishing the subsystem and the unit was delivered to GSFC at the conclusion of the program.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-132905 , SVHSER-6226
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    Advanced space engine preliminary design (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary design was completed for an O2/H2, 89 kN (20,000 lb) thrust staged combustion rocket engine that has a single-bell nozzle with an overall expansion ratio of 400:1. The engine has a best estimate vacuum specific impulse of 4623.8 N-s/kg (471.5 sec) at full thrust and mixture ratio = 6.0. The engine employs gear-driven, low pressure pumps to provide low NPSH capability while individual turbine-driven, high-speed main pumps provide the system pressures required for high-chamber pressure operation. The engine design dry weight for the fixed-nozzle configuration is 206.9 kg (456.3 lb). Engine overall length is 234 cm (92.1 in.). The extendible nozzle version has a stowed length of 141.5 cm (55.7 in.). Critical technology items in the development of the engine were defined. Development program plans and their costs for development, production, operation, and flight support of the ASE were established for minimum cost and minimum time programs.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-121237 , PWA-FR-5654
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    Unsteady aerodynamic analysis of space shuttle vehicles. Part 3: Booster interference effects (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation of the interference flow field on the space-shuttle boost configuration has been made. The results show that the interference effects can dominate the shuttle aerodynamics. Vortices shed from shock-induced flow separations on the forward portion of the vehicle affect the aerodynamic loads on the aft portion of the booster. Thus, the forebody and aft-body flow fields are coupled. This coupling and the associated time lag due to the finite convection speed of the vortices furnish a mechanism whereby the unsteady aerodynamics can cause undamping of certain low frequency elastic modes of the booster. A preliminary order-of-magnitude analysis of the aeroelastic stability of the shuttle booster indicates that negative aerodynamic damping could occur for at least one bending mode and be of sufficient magnitude to dominate the structural damping. The implication of these results, (with the possibility of undamped oscillations leading to structural failure), is serious enough to warrant further, more detailed analysis.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120124 , LMSC-D352320-PT-3
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    The space shuttle payload planning working groups: Executive summaries (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The findings of a space shuttle payload planning group session are presented. The purpose of the workshop is: (1) to provide guidance for the design and development of the space shuttle and the spacelab and (2) to plan a space science and applications program for the 1980 time period. Individual groups were organized to cover the various space sciences, applications, technologies, and life sciences. Summaries of the reports submitted by the working groups are provided.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-69464
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    The space shuttle payload planning working groups. Volume 1: Astronomy (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The space astronomy missions to be accomplished by the space shuttle are discussed. The principal instrument is the Large Space Telescope optimized for the ultraviolet and visible regions of the spectrum, but usable also in the infrared. Two infrared telescopes are also proposed and their characteristics are described. Other instruments considered for the astronomical observations are: (1) a very wide angle ultraviolet camera, (2) a grazing incidence telescope, (3) Explorer-class free flyers to measure the cosmic microwave background, and (4) rocket-class instruments which can fly frequently on a variety of missions. The stability requirements of the space shuttle for accomplishing the astronomy mission are defined.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-69409
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    Solid motor diagnostic instrumentation (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A review of typical surveillance and monitoring practices followed during the flight phases of representative solid-propellant upper stages and apogee motors was conducted to evaluate the need for improved flight diagnostic instrumentation on future spacecraft. The capabilities of the flight instrumentation package were limited to the detection of whether or not the solid motor was the cause of failure and to the identification of probable primary failure modes. Conceptual designs of self-contained flight instrumentation packages capable of meeting these reqirements were generated and their performance, typical cost, and unit characteristics determined. Comparisons of a continuous real time and a thresholded hybrid design were made on the basis of performance, mass, power, cost, and expected life. The results of this analysis substantiated the feasibility of a self-contained independent flight instrumentation module as well as the existence of performance margins by which to exploit growth option applications.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-136561 , JPL-TM-33-656
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    Balloon launched Viking decelerator test program (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Four BLDT flights were conducted during the summer of 1972. The purpose of these tests was to qualify the Viking parachute system behind the full-scale Viking entry vehicle over the maximum range of entry conditions anticipated in the Viking '75 soft landing on Mars. A summary of the test series is presented. Test conditions ranged from a Mach number of 2.0 to 0.5 and dynamic pressure from 11.7 to 4.4 psf. This range of conditions covers the uncertainty in entry conditions at Mars due to atmospheric and entry performance uncertainties. Emphasis is placed on parachute performance and simulated Mars entry vehicle motions as influenced by the parachute performance. Conclusions are presented regarding the ability of the parachute to perform within the operational parameters required for a successful soft Martian landing. A list of references which covers all reports in the qualification test program is included.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-112288 , TR-3720359
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    Space shuttle atmospheric revitalization subsystem/active thermal control subsystem computer program (users manual) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A shuttle (ARS) atmosphere revitalization subsystem active thermal control subsystem (ATCS) performance routine was developed. This computer program is adapted from the Shuttle EC/LSS Design Computer Program. The program was upgraded in three noteworthy areas: (1) The functional ARS/ATCS schematic has been revised to accurately synthesize the shuttle baseline system definition. (2) The program logic has been improved to provide a more accurate prediction of the integrated ARS/ATCS system performance. Additionally, the logic has been expanded to model all components and thermal loads in the ARS/ATCS system. (3) The program is designed to be used on the NASA JSC crew system division's programmable calculator system. As written the new computer routine has an average running time of five minutes. The use of desk top type calculation equipment, and the rapid response of the program provides the NASA with an analytical tool for trade studies to refine the system definition, and for test support of the RSECS or integrated Shuttle ARS/ATCS test programs.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134164 , SP02T73
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    Space tug point design study. Volume 4: Program requirements (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was conducted to determine the configuration of a space tug and to predict the performance parameters. The program plans and planning data generated in support of the tug development program are presented. The preliminary plans and supporting planning data emphasize the following requirements: (1) maintenance and refurbishment, (2) technology development, (3) production, (4) test facilities, (5) quality control, and (6) scheduling.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120112 , SD72-SA-0032-VOL-4
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    Space tug point design study. Volume 3: Design definition. Part 1: Propulsion and mechanical, avionics, thermal control and electrical power subsystems (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was conducted to determine the configuration and performance of a space tug. Details of the space tug systems are presented to include: (1) propulsion systems, (2) avionics, (3) thermal control, and (4) electric power subsystems. The data generated include engineering drawings, schematics, subsystem operation, and component description. Various options investigated and the rational for the point design selection are analyzed.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-124023 , SD72-SA-0032-VOL-3-PT-1
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    Functional requirements for onboard management of space shuttle consumables, volume 2. (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was conducted to develop the functional requirements for onboard management of space shuttle consumables. A specific consumables management concept for the space shuttle vehicle was developed and the functional requirements for the onboard portion of the concept were generated. Consumables management is the process of controlling or influencing the usage of expendable materials involved in vehicle subsystem operation. The subsystems considered in the study are: (1) propulsion, (2) power generation, and (3) environmental and life support.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134145 , TRW-22104-H002-RO-00-VOL-2
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    Subsonic, transonic, and supersonic stability and control characteristics of the -147B space shuttle orbiter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted on 0.015 scale representations of two Space Shuttle Orbiter configurations in a trisonic wind tunnel from June 20, 1973 to June 30, 1973. The primary test objective was to define subsonic, transonic, and supersonic stability and control characteristics of the -147B Orbiter. Six-component aerodynamic force and moment data for the -147B Orbiter were recorded over an angle of attack range of -2 deg to 30 deg at Mach numbers of 0.6, 0.9, 1.2, 2.0, and 3.0. Reynolds numbers of 5.0, 7.0, 8.0, and 9.0 x 100000 6/ft were tested at Mach numbers less than 2.0 while testing at Mach 2.0 and 3.0 was conducted at a Reynolds number of 11.0 x 100000/ft. Eleven deflections of 0 deg, +15 deg, -20, deg and -40 deg; body flap deflections of 0 deg, +13.75 deg and -14.25 deg; and rudder flare angles of 24.92 deg and 54.92 deg were tested on the -147B Orbiter over the entire Mach number range. Testing of the -139B Orbiter was for data verification and configuration comparison purposes only.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128789 , DMS-DR-2061
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    Surface roughness effects on the subsonic aerodynamics of the Rockwell International 089B-139B orbiter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental test program was conducted to determine the effects of vehicle surface roughness on the subsonic aerodynamic characteristics of a 0.01875 scale model of a Rockwell International Space Shuttle Configuration. Surface roughness was simulated by applying a sparce coating of carborundum grit to the complete model. Various grit sizes were investigated. Tests were conducted in the Langley Low Turbulence Pressure Tunnel at a constant nominal Mach number of 0.25 with Reynolds number varying from 2 to 12 x 10 to the 6th power per foot. Angle of attack was varied from about -2 to 28 deg at 0 deg and 6 deg angle of sideslip.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128782 , DMS-DR-2056
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    Surface roughness effects on the supersonic aerodynamics of the Rockwell International 089B-139 orbiter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental test program was conducted to determine the effects of vehicle surface roughness on the supersonic aerodynamic characteristics of a 0.01875 scale model of a space shuttle configuration. Surface roughness was simulated by applying a sparse coating of carborundum grit to complete model. Various grit sizes were investigated. The tests were conducted in a wind tunnel at Mach numbers from 1.60 to 4.63. The angle of attack was varied from about -2 deg to as much as 42 deg at 0 deg and + or - 3 deg of sideslip. The angle of sideslip was varied from -8 deg to 8 deg at angles of attack from 0 deg to 40 deg.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128796 , DMS-DR-2054
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    Space shuttle solid rocket booster recovery system definition, volume 1 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The performance requirements, preliminary designs, and development program plans for an airborne recovery system for the space shuttle solid rocket booster are discussed. The analyses performed during the study phase of the program are presented. The basic considerations which established the system configuration are defined. A Monte Carlo statistical technique using random sampling of the probability distribution for the critical water impact parameters was used to determine the failure probability of each solid rocket booster component as functions of impact velocity and component strength capability.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120106 , MCR-73-247-VOL-1
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    Molding process for imidazopyrrolone polymers (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A process is described for producing shaped articles of imidazopyrrolone polymers comprising molding imidazopyrrolone polymer molding power under pressure and at a temperature greater than 475 C. Moderate pressures may be employed. Preferably, prior to molding, a preform is prepared by isostatic compression. The preform may be molded at a relatively low initial pressure and temperature; as the temperature is increased to a value greater than 475 C., the pressure is also increased.
    Keywords: SPACE VEHICLES
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    Experimental validation of a landing-dynamics computer program for legged spacecraft landers (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Validation of a landing-dynamics computer program has been accomplished by comparing analytical data with data from a limited experimental program. Agreement obtained established the subject landing-dynamics computer program as a reliable design tool for legged spacecraft landers.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7301 , L-8726
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  • 65
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    Flight-determined stability and control characteristics of the M2-F3 lifting body vehicle (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight data were obtained over a Mach number range from 0.4 to 1.55 and an angle-of-attack range from -2 deg to 16 deg. Lateral-directional and longitudinal derivatives, reaction control rocket effectiveness, and longitudinal trim information obtained from flight data and wind-tunnel predictions are compared. The effects of power, configuration change, and speed brake are discussed.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7511 , H-791
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  • 66
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    Crew interface specifications development functions, phase 3A (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The findings and data products developed during the crew interface specification study for inflight maintenance and stowage functions are presented. Guidelines are provided for improving the present progress of defining, controlling, and managing the flight crew requirements. The following data products were developed: (1) description of inflight maintenance management process, (2) specifications for inflight maintenance management requirements, and (3) suggested inflight maintenance data processing reports for logistics management.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134147
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  • 67
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    Acquisition/expulsion system for earth orbital propulsion system study. Volume 5: Earth storable design (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A comprehensive analysis and parametric design effort was conducted under the earth-storable phase of the program. Passive Acquisition/expulsion system concepts were evaluated for a reusable Orbital Maneuvering System (OMS) application. The passive surface tension technique for providing gas free liquid on demand was superior to other propellant acquisition methods. Systems using fine mesh screens can provide the requisite stability and satisfy OMS mission requirements. Both fine mesh screen liner and trap systems were given detailed consideration in the parametric design, and trap systems were selected for this particular application. These systems are compatible with the 100- to 500-manned mission reuse requirements.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134157 , MCR-73-97-VOL-5
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  • 68
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    Acquisition/expulsion system for earth orbital propulsion system study. Volume 4: Flight test article (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two orbital test plans were prepared to verify one of the passive cryogenic storage tank/feedline candidate designs. One plan considered the orbital test article to be launched as a dedicated payload using an Atlas F burner launching configuration. The second plan proposed to launch the orbital test article as a secondary payload on the Titan E/Centaur proof flight. The secondary payload concept was pursued until January 1973, when work to build the hardware for this phase of the contract was terminated for lack of a sponsor for the flight. The dedicated payload launched on an Atlas F is described.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134156 , MCR-73-97-VOL-4
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  • 69
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    Acquisition/expulsion system for earth orbital propulsion system study. Volume 3: Cryogenic test (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A ground test program was conducted to verify several of the design methods and techniques that were used in designing cryogenic acquisition/expulsion systems. The testing of a 63.5-cm diameter DSL subscale model was particularly significant. Under these tests, the operational characteristics of the DSL concept were verified using LH2 and LN2. Demonstration of the gas free liquid expulsion characteristics was accomplished by expelling LH2 under -1 g using both GH2 and GHe pressurization. Loading of the acquisition/expulsion device was successfully accomplished using LH2 and LN2. The liquid free vapor venting performance of the model was limited because of the thermal stratification under the -1 g test conditions.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134155 , MCR-73-97-VOL-3
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  • 70
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    Acquisition/expulsion system for earth orbital propulsion system study. Volume 1: Summary report (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design, construction, and quality control tests on a dual screen liner device for the space shuttle orbiter cryogenic fuel tank and feedliner system are summarized. The dual stainless steel mesh of the device encloses eight liquid fuel channels and provides the liquid/vapor interface stability required for low gravity orbits.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134153 , MCR-73-97-VOL-1
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  • 71
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    Acquisition/expulsion system for earth orbital propulsion system study. Volume 2: Cryogenic design (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Detailed designs were made for three earth orbital propulsion systems; (1) the space shuttle (integrated) OMS/RCS, (2) the space shuttle (dedicated) OMS (LO2), and (3) the space tug. The preferred designs from the integrated OMS/RCS were used as the basis for the flight test article design. A plan was prepared that outlines the steps, cost, and schedule required to complete the development of the prototype DSL tank and feedline (LH2 and LO2) systems. Ground testing of a subscale model using LH2 verified the expulsion characteristics of the preferred DSL designs.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134154 , MCR-73-97-VOL-2
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  • 72
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    Stability and control characteristics of a Langley concept space shuttle orbiter (LO-100) at low subsonic speeds (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental aerodynamic investigation was conducted on a 0.01 scale model of a Langley concept space shuttle orbiter (LO-100) in the Langley Low Turbulence Pressure Tunnel at a Mach number of 0.25 and at a Reynolds number of 5.4 million per foot. The angle of attack was varied from about -2 deg to 24 deg at 0 deg and 5 deg sideslip. The configuration was tested at elevon settings of 0 deg, -5 deg, -10 deg, and -15 deg for a body base flap setting of 0 deg and at 0 deg, -10 deg, and -15 deg for a body base flap setting of -18 deg. The effect of rudder flare angle was obtained using 0 deg, 20 deg, and 40 deg, flare settings.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128787 , DMS-DR-2070
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  • 73
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    Results of tests in the MSFC 14 x 14 inch trisonic wind tunnel on a .004 scale model of the Rockwell International Space Shuttle Vehicle 3, (integrated configuration) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted during mid-July, 1973 on a .004 scale model of the Rockwell International integrated configuration Space Shuttle Vehicle 3. The purpose of the tests was three fold: (1) to determine the static stability characteristics of the integrated vehicle, utilizing the Vehicle 3 orbiter configuration; (2) to determine the effect of interstage structure and tank external fuel lines on the integrated vehicle aerodynamic characteristics; (3) to determine the effects of the aft interstage structure on orbiter aerodynamic loads. Data were recorded on the integrated vehicle (test no. 579) at angles of attack and sideslip ranging from -10 deg to 10 deg over a Mach number schedule from 0.6 to 4.96. Data were obtained on the orbiter alone in the presence of the external tank with SRB attached (test no. 580) at angles of attack from -10 deg to 10 deg over a Mach number range from .6 to 1.96. Plotted data are presented in the body axis system.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128788 , DMS-DR-2063
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  • 74
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    High temperature antenna development for space shuttle, volume 1 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design concepts for high temperature flush mounted Space Shuttle Orbiter antenna systems are discussed. The design concepts include antenna systems for VHF, L-band, S-band, C-band and Ku-band frequencies. The S-band antenna system design was completed and test hardware fabricated. It was then subjected to electrical and thermal testing to establish design requirements and determine reuse capabilities. The thermal tests consisted of applying ten high temperature cycles simulating the Orbiter entry heating environment in an arc tunnel plasma facility and observing the temperature distributions. Radiation pattern and impedance measurements before and after high temperature exposure were used to evaluated the antenna systems performance. Alternate window design concepts are considered. Layout drawings, supported by thermal and strength analyses, are given for each of the antenna system designs. The results of the electrical and thermal testing of the S-band antenna system are given.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134136 , MDC-E0896-VOL-1
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  • 75
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    Development of flame-resistant structures for use in the Apollo and Skylab programs (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flame-resistant materials have been designed and fabricated to meet certain end-use criteria established by NASA with emphasis on meeting established flammability standards. The program had three general phases: (1) fabrication of candidate sample structures for evaluation by the Structures and Mechanics Division and/or NASA contractors; (2) physical testing of the structures developed; and (3) supply of required quantities of specific items for fabrication into prototype and/or flight items for the Apollo and Skylab programs.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134133
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  • 76
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    Results of tests OA12 and IA9 in the Ames Research Center unitary plan wind tunnels on an 0.030-scale model of the space shuttle vehicle 2A to determine aerodynamic loads, volume 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted in Unitary Plan wind tunnels on a 0.30 scale model of the space shuttle. Tests were conducted on the integrated configuration and on the isolated orbiter. The integrated vehicle was tested at angles of attack and sideslip from minus 8 degrees to plus 8 degrees. The isolated orbiter was tested at angles of attack from minus 15 degrees to plus 40 degrees and angles of sideslip from minus 10 degrees to plus 10 degrees as dictated by trajectory considerations. The effects of orbiter/external tank incidence angle and deflected control surfaces on aerodynamic loads were investigated.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128794-VOL-2 , DMS-DR-2032-VOL-2
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  • 77
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    Static stability and control effectiveness of models 12-0 and 34-0 of the vehicle 3 configuration, volume 3 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Static stability and control effectiveness characteristics of two 0.004 scale models of the vehicle 3 configuration are reported. The components investigated consisted of a single aft body, vertical/rudder, OMS pods with two interchangeable wings, four interchangeable forward bodies, four trimmers, and a spoiler. The test was conducted in 14 x 14 inch trisonic wind tunnel over a Mach number range from 0.6 to 4.96. Angles of attack from 0 to 60 degrees and angles of sideslip from -10 to 10 degrees at 0, 10, 20,30, and 40 degrees angle of attack were tested. Elevon, body flap, and speed brake deflection composed the parametric considerations. No grit was placed on the models during the test. The tabulated source data and incremental data figures are presented.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128780-VOL-3 , DMS-DR-2055-VOL-3
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  • 78
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    Quantitative understanding of explosive stimulus transfer (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The mechanisms of detonation transfer across hermetically sealed interfaces created by necessary interruptions in high explosive trains, such as at detonators to explosive columns, field joints in explosive columns, and components of munitions fuse trains are demostrated. Reliability of detonation transfer is limited by minimizing explosive quantities, the use of intensitive explosives for safety, and requirements to propagate across gaps and angles dictated by installation and production restraints. The major detonation transfer variables studied were: explosive quanity, sensitivity, and thickness, and the separation distances between donor and acceptor explosives.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-2341
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  • 79
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    Hypersonic performance, stability and control characteristics of a .0075 scale model Rockwell International 089B-139B orbiter configuration (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made in the Langley Continuous Flow Hypersonic Tunnel at a Mach number of 10.3 to study the hypersonic aerodynamic characteristics of a Rockwell International shuttle orbiter configuration. Tests were made at a Reynolds number of 790,000 x 106 based on body length with an angle-of-attack range of 10 to 35 deg and sideslip variations of +1 to -9 deg. The effects of elevon and body flap deflection were investigated.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128783 , DMS-DR-2066
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  • 80
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    Supersonic aerodynamic characteristics associated with variations in the geometry of the forward portion of irregular planform wings (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The experimental longitudinal and lateral-directional stability characteristics of a Langley conceptual space shuttle orbiter design have been obtained for a series of inboard planform fillets in a unitary plan wind tunnel. Fillet sweep angles up to 78 deg were investigated while holding the spanwise intersection of the fillet and wing constant. The data were obtained at Mach numbers of 2.36 to 4.63 and at Reynolds numbers (depending on Mach number) of 1.5 million to 2.5 million per foot. The angle of attack was varied from about minus 2 deg to 44 deg at 0 deg and 3 deg of sideslip.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128791 , DMS-DR-2052
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  • 81
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    Unified powered flight guidance (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A complete revision of the orbiter powered flight guidance scheme is presented. A unified approach to powered flight guidance was taken to accommodate all phases of exo-atmospheric orbiter powered flight, from ascent through deorbit. The guidance scheme was changed from the previous modified version of the Lambert Aim Point Maneuver Mode used in Apollo to one that employs linear tangent guidance concepts. This document replaces the previous ascent phase equation document.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134149 , DOC-24
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  • 82
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    Deorbit targeting (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The navigation and control of the space shuttle during atmospheric entry are discussed. A functional flow diagram presenting the basic approach to the deorbit targeting problem is presented. The major inputs to be considered are: (1) vehicle state vector, (2) landing site location, (3) entry interface parameters, (4) earliest desired time of landing, and (5) maximum cross range. Mathematical models of the navigational procedures based on controlled thrust times are developed.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134151 , DOC-14-REV-1
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  • 83
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    Rendezvous targeting (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Revisions to be included in 'Space Shuttle Guidance, Navigation and Control Design Equations' are reported. Technical changes include: (1) a plane change maneuver was incorporated in the program's logic; (2) in the search for an apsidal crossing, program checks were included to update through intervals of pi in the case of near circular orbits or close proximity to an apsidal point; (3) following an astronaut overwrite of a Lambert maneuver, the state vector was updated to establish a new target vector for use in the powered flight routine; and (4) following the computation of each maneuver, the position vector of the primary vehicle was offset - to help compensate for the effects of the finite maneuver - prior to the update of the state vector to the next maneuver point. Input and output variables, detailed flow diagrams a functional flow diagram, and a description of equations are presented.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134150 , DOC-7-REV-3
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  • 84
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    Rendezvous terminal phase automatic braking sequencing and targeting (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The purpose of the rendezvous terminal phase braking program is to provide the means of automatically bringing the primary orbiter within desired station keeping boundaries relative to the target satellite. A detailed discussion is presented on the braking program and its navigation, targeting, and guidance functions.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134152 , DOC-15-REV-2
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  • 85
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    Wind tunnel test of the 0.015-scale Rockwell International space shuttle vehicle orbiter in the Ames 6 by 6 foot supersonic wind tunnel (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental investigations were performed in a 6- by 6-Foot Supersonic wind tunnel on a 0.015-scale model of the Rockwell International space shuttle vehicle (SSV) 2A orbiter. The purpose of the test was to investigate the longitudinal and lateral-directional characteristics of the vehicle. In addition, hinge moments were measured on the rudder and elevons. Buffet onset was investigated using wing trailing edge pressures and a strain gauge instrumented panel mounted in the wing. The model was tested through a Mach range from 0.6 to 2.0 at a constant unit Reynolds number of 2.5 million. Pitch runs were made at angles of attack from minus 2 deg to +26 deg with beta = 0 deg and 5 deg; yaw runs were made in the range from minus 5 deg to 10 deg of sideslip at angles of attack of 0 deg and 10 deg. Static pressures were measured at the fuselage base and the trailing edges of the wing and rudder. Boundary layer transition was fixed for some runs using distributed roughness strips.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128790 , DMS-DR-2050
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  • 86
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    Skylab 2 post-launch report (RCS 76-0000-00048) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The launch vehicle stages for SL-2, the CSM experiments, and their associated support equipment are reported. The performance of KSC systems in support of processing and launch of the SL-2 are described along with major processing events for each launch vehicle stage, the spacecraft, and the general experiments of the SL-2 S/V. The final countdown and hold times are noted and a summary of the launch vehicle is included. The weather conditions at launch time and the range support activities are given.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-69453
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  • 87
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    Pressure loads and aerodynamic force information for the -89A space shuttle orbiter configuration, volume 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted on an 0.0405 scale representation of the Rockwell -89A Light Weight Space Shuttle Orbiter. The test purpose was to obtain pressure loads data in the presence of the ground for orbiter structural strength analysis. Aerodynamic force data was also recorded to allow correlation with all pressure loads information. Angles of attack from minus 3 deg to 18 deg and angles of sideslip of 0 deg, plus or minus 50 deg, and plus or minus 10 deg were tested in the presence of the NAAL ground plane. Static pressure bugs were used to obtain a pressure loads survey of the basic configuration, elevon deflections of 5 deg, 10 deg, 15 deg, and minus 20 deg and a rudder deflection of minus 15 deg, at a tunnel dynamic pressure of 40 psi. The test procedure was to locate a maximum of 30 static pressure bugs on the model surface at various locations calculated to prevent aerodynamic and physical interference. Then by various combinations of location the pressure bugs output was to define a complete pressure survey for the fuselages, wing, vertical tail, and main landing gear door.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128758-VOL-1 , DMS-DR-2021-VOL-1
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  • 88
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    Results of tests OA12 and IA9 in the Ames Research Center unitary plan wind tunnels on an 0.030-scale model of the space shuttle vehicle 2A to determine aerodynamic loads, volume 1 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted in unitary plan wind tunnels on an 0.030-scale replica of the space shuttle vehicle configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The investigation included tests on the integrated (launch) configuration and tests on the isolated orbiter (entry configuration). The integrated vehicle was tested at angles of attack and sideslip from minus 8 deg to plus 8 deg. The isolated orbiter was tested at angles of attack from minus 15 deg to plus 40 deg and angles of sideslip from minus 10 deg to plus 10 deg are dictated by trajectory considerations. The effects of orbiter/external tank incidence and deflected control surfaces on aerodynamic loads were also investigated.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128794-VOL-1 , DMS-DR-2032-VOL-1
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  • 89
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    Engineering report. Part 3: NASA lightweight wheel and brake sub-system. Lightweight brake development (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development of light weight wheel and brake systems designed to meet the space shuttle type requirements was investigated. The study includes the use of carbon graphite composite and beryllium as heat sink materials and the compatibility of these heat sink materials with the other structural components of the wheel and brake.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134130 , REPT-4239-PT-3
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  • 90
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    Engineering report. Part 2: NASA wheel and brake material tradeoff study for space shuttle type environmental requirements (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The study included material selection and trade-off for the structural components of the wheel and brake optimizing weight vs cost and feasibility for the space shuttle type application. Analytical methods were used to determine section thickness for various materials, and a table was constructed showing weight vs. cost trade-off. The wheel and brake were further optimized by considering design philosophies that deviate from standard aircraft specifications, and designs that best utilize the materials being considered.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134129 , REPT-4239-PT-2
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  • 91
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    Mission SL-4 (AS 208/CM 118/IMU 34)G and N error analysis (Skylab 4) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Data on the gyro and navigation system performance and operation for the command module are presented. Each reported failure was analyzed with respect to its likelihood of occurence in flight and its impact on the mission.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134131 , E-2795
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  • 92
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    Results of investigations on a 0.015-scale model 2A configuration of the Rockwell International space shuttle orbiter in the NASA/Ames Research Center 3.5 foot hypersonic wind tunnel (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted in the NASA/Ames 3.5-Foot Hypersonic wind Tunnel during the interim April 9-18, 1973 on a 0.015-scale model of the Rockwell International Space Shuttle Orbiter, configuration 2A. Six component aerodynamic force and moment data were recorded over an angle of attack range from -3 deg to 42 deg at 0 deg angle of sideslip and from -10 deg to 10 deg sideslip at 0 deg and 45 deg constant angle of attack. Test Mach numbers were 5.27 and 7.32 at unit Reynolds number of 2.5 million per foot. Various elevon, rudder, speedbrake, and body flap deflections were tested to determine longitudinal and lateral-directional stability characteristics and to establish trim capability.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128786 , DMS-DR-2044
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  • 93
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    Lightweight tire concept for space shuttle (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Various tests were conducted on a 49x17/26 PR aircraft tire that had been designed as a lightweight tire for use on the C-5A military transport. This tire is approximately 25 per cent lighter than a tire of the same size and ply rating that would be used in commercial airline service. The tires were tested at 40 per cent, 37 per cent, and 35 per cent deflections. These deflections were obtained by adjusting the inflation pressure while the load on the tire remained constant at 60,000 pounds. It was determined that the tire would operate successfully under the test conditions at 35% deflection. Prior to testing, the tires were subjected to conditions of high vacuum and low temperature. It was determined that the tires were not adversely affected by these conditions.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134127 , ATD-2751
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    Study of a quasi-microscope design for planetary landers (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Viking Lander fascimile camera, in its present form, provides for a minimum object distance of 1.9 meters, at which distance its resolution of 0.0007 radian provides an object resolution of 1.33 millimeters. It was deemed desirable, especially for follow-on Viking missions, to provide means for examing Martian terrain at resolutions considerably higher than that now provided. This led to the concept of quasi-microscope, an attachment to be used in conjunction with the fascimile camera to convert it to a low power microscope. The results are reported of an investigation to consider alternate optical configurations for the quasi-microscope and to develop optical designs for the selected system or systems. Initial requirements included consideration of object resolutions in the range of 2 to 50 micrometers, an available field of view of the order of 500 pixels, and no significant modifications to the fascimile camera.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-132315
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  • 95
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    Desiccant humidity control system (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A regenerable sorbent system was investigated for controlling the humidity and carbon dioxide concentration of the space shuttle cabin atmosphere. The sorbents considered for water and carbon dioxide removal were silica gel and molecular sieves. Bed optimization and preliminary system design are discussed along with system optimization studies and weight penalites.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134126 , REPT-73-9313
    Format: application/pdf
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  • 96
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    Space shuttle lightning protection criteria document (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The lightning environment for design is defined and imposes the requirements that the design must satisfy to insure the protection of the space shuttle vehicle system from the direct and indirect effects of lightning. Specifications, criteria, and guidelines provide a practical and logical approach to the protection problems. Protection against the indirect effects of lightning is intimately involved with the electromagnetic compatibility and electromagnetic interference functions. While this document does not deal specifically with electromagnetic compatibility and electromagnetic interference, it does deal with the interactions between lightning protection measures and measures employed for electromagnetic compatibility and control of electromagnetic interference.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-69454 , JSC-07636
    Format: application/pdf
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  • 97
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    Results of tests OA12 and IA9 in the Ames Research Center Unitary Plan Wind Tunnels on an 0.030-scale model of the Space Shuttle Vehicle 2A to determine aerodynamic loads, volume 3 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted in the NASA/ARC Unitary Plan Wind Tunnels during April and May 1973, on an 0.030-scale replica of the Space Shuttle Vehicle Configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The investigation included tests IA9A, B and C on the integrated (launch) configuration and tests OA12A and C on the isolated orbiter (entry configuration). The integrated vehicle was tested at angles of attack and sideslip from -8 degrees to +8 degrees. The isolated orbiter was tested at angles of attack from -15 degrees to +40 degrees and angles of sideslip from -10 degrees to +10 degrees to as dictated by trajectory considerations. The effects of orbiter/external tank incidence angle and deflected control surfaces on aerodynamic loads were also investigated.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128794-VOL-3 , DMS-DR-2032-VOL-3
    Format: application/pdf
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  • 98
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    Catalysis study for space shuttle vehicle thermal protection systems (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental results on the problem of reducing aerodynamic heating on space shuttle orbiter surfaces are presented. Data include: (1) development of a laboratory flow reactor technique for measuring gamma sub O and gamma sub N on candidate materials at surfaces, T sub w, in the nominal range 1000 to 2000, (2) measurements of gamma sub O and gamma sub N above 1000 K for both the glass coating of a reusable surface insulation material and the siliconized surface of a reinforced pyrolyzed plastic material, (3) measurement of the ablation behavior of the coated RPP material at T sub w is greater than or equal to 2150 K, (4) X-ray photoelectron spectral studies of the chemical constituents on these surfaces before and after dissociated gas exposure, (5) scanning electron micrograph examination of as-received and reacted specimens, and (6) development and exploitation of a method of predicting the aerodynamic heating consquences of these gamma sub O(T sub w) and gamma sub N(T sub w) measurements for critical locations on a radiation cooled orbiter vehicle.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134124
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  • 99
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    Space shuttle/payload interface analysis (study 2.4). Volume 1: Executive summary (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The space shuttle/payload interface analysis is presented. The analysis consists of the following sections: (1) payload capture and cost analysis, (2) business risk and value of operations in space analysis, and (3) payload community analysis. The primary objective of the study was to furnish a method for tracing capture/cost analyses conducted by other study groups.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-136125 , ATR-74(7334)-1-VOL-1
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  • 100
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    Single-stage experimental evaluation of tandem-airfoil rotor stator blading for compressors. Part 6: Data and performance for stage D (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An axial flow compressor stage, having single-airfoil blading, was designed for zero rotor prewhirl, constant rotor work across the span, and axial discharge flow. The stage was designed to produce a pressure ratio of 1.265 at a rotor tip velocity of 757 ft/sec. The rotor had an inlet hub/tip ratio of 0.8. The design procedure accounted for the rotor inlet boundary layer and included the effects of axial velocity ratio and secondary flow on blade row performance. The objectives of this experimental program were: (1) to obtain performance with uniform and distorted inlet flow for comparison with the performance of a stage consisting of tandem-airfoil blading designed for the same vector diagrams; and (2) to evaluate the effectiveness of accounting for the inlet boundary layer, axial velocity ratio, and secondary flows in the stage design. With uniform inlet flow, the rotor achieved a maximum adiabatic efficiency of 90.1% at design equivalent rotor speed and a pressure ratio of 1.281. The stage maximum adiabatic efficiency at design equivalent rotor speed with uniform inlet flow was 86.1% at a pressure ratio of 1.266. Hub radial, tip radial, and circumferential distortion of the inlet flow caused reductions in surge pressure ratio of approximately 2, 10 and 5%, respectively, at design rotor speed.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134511 , PWA-FR-5852-PT-6
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