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  • SPACE VEHICLES  (2,693)
  • Chemical Engineering  (1,794)
  • THERMODYNAMICS AND COMBUSTION  (1,363)
  • 1970-1974  (5,850)
Collection
Keywords
Publisher
Years
Year
  • 1
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    Architecture in outer space (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Mulilayer thin film structures consisting of systems of shells filled with gas at some pressure are recommended for outer space structures: Large mirrors to collect light and radio waves, protection against meteoric impact and damage, and for connectors between state space stations in the form of orbital rings. It is projected that individual orbital rings will multiply and completely seal a star trapping its high temperature radiation and transforming it into low temperature infrared and short wave radio emission; this radiation energy could be utilized for technological and biological processes.
    Keywords: SPACE VEHICLES
    Type: Inhabited Space, Pt. 2 (NASA-TT-F-820); p 161-169
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  • 2
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    Spacecraft of the future (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Manned interstellar expeditions require future ion propulsion rocket engines able to achieve a flight velocity of 0.3 times the speed of light, and a closed ecological system onboard the interstellar spacecraft that incorporates biological links and complicated technical facilities to insure long term life support for its crew.
    Keywords: SPACE VEHICLES
    Type: Inhabited Space, Pt. 2 (NASA-TT-F-820); p 135-153
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  • 3
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    Spacecraft (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The task of building a spacecraft is compared to the construction of an artificial cybernetic system able to acquire and process information. Typical features for future spacecraft are outlined and the assignment of duties in spacecraft control between automatic devices and the crew is analyzed.
    Keywords: SPACE VEHICLES
    Type: Inhabited Space, Pt. 2 (NASA-TT-F-820); p 2-16
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  • 4
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    Method of calculating gas dynamics and heat transfer in single stage refrigeration units (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: A generalized mathematical model of gas-dynamic and heat transfer processes in single-stage regenerative installations operating in Stirling, MacMahon, Gifford-MacMahon, and pulsating tube cycles is proposed. A numerical method os solving initial equations on a digital computer is given. This makes it possible to calculate the change in the thermodynamic parameters in the working cycle in different machine components, as well as the dependence of cold productivity on the temperature level in the steady regime.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Res. in the Ukraine, No. 3 (NASA-TT-F-15537); p 124-138
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  • 5
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    Measurements of sonic-boom overpressures from Apollo space vehicles (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: This paper presents representative results of sonic-boom overpressure data recorded during the launch and reentry of the Apollo 15 and 16 space vehicle systems. Comparisons are made between measured overpressures and those predicted using available theory. The measurements were obtained along the vehicle ground track at 68, 87, 92, 129, and 970 km downrange from the launch site during ascent, and at 9, 13, 55, 185, and 500 km from the splash-down point during reentry. Also included are tracings of the sonic-boom signatures along with a brief description of the launch and recovery test areas in which the measurements were obtained, the sonic-boom instrumentation deployment, flight profiles and operating conditions, and high-altitude weather information for the general measurement areas.
    Keywords: SPACE VEHICLES
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  • 6
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    The community satellite 1 (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: NASA's Applications Technology Satellite-6 is being used to test a variety of new space communications concepts requiring the use of a geosynchronous-orbit spacecraft. These include broadcast of health and education television programs to small, low-cost ground receiving units in remote regions. Other studies to be conducted are related to aeronautical and maritime communications, position-location, and traffic-control techniques. Questions concerning spacecraft tracking and data relay are also investigated. The 1,402 kg spacecraft consists essentially of an Earth Viewing Module connected to a deployable reflector antenna. Details regarding the planned experiments and the spacecraft design are discussed and a brief history of the ATS program is presented.
    Keywords: SPACE VEHICLES
    Type: Spaceflight; 16; Sept
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  • 7
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    Nonequilibrium boundary layer at a stagnation point for a hydrogen-helium stream over ablating graphite (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The nonequilibrium axisymmetric stagnation point boundary layer over an ablating graphite surface is considered. The external stream is a high temperature mixture of hydrogen and helium. Variable thermodynamic and transport properties are assumed. Lennard-Jones potential model is used to calculate the transport coefficients of each species. Although the mixture rules for viscosity of the gas mixture are used, the weighting functions are more sophisticated than those commonly employed. For the conductivity of the mixture, generalized Wassiljewa coefficients are used. Seven species with 28 dissociation/recombination reactions are considered. Hansen's model for the dissociation rate constants is employed. The recombination rate constants are obtained by invoking detailed balance principles assisted by the JANAF thermodynamic data and the Hansen-Pearson thermodynamic data for C3.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Acta Astronautica; 1; Mar
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  • 8
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    Effect of wall temperature spatial variations on aerodynamic heating to an actively cooled aircraft (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The design of cooled skin panels, which requires consideration of many parameters such as heat load, skin thickness, panel size, tube spacing, tube size, temperature limits, coolant flow, etc., must minimize weight and thermal stresses. A design procedure for such panels has been developed by Bell Aerospace Company (Helenbrook and Anthony, 1971). This design procedure assumes a uniform heating rate to the panel, i.e., the variation of aerodynamic heating rate due to the cyclic wall temperature distribution, which results from the discrete coolant tube locations in such a panel, has been neglected. This study was made to determine if these variations were sufficiently large to cause variations in aerodynamic heating rate which would require coupling of boundary layer and conductive thermal analysis solutions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Aircraft; 11; Aug. 197
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  • 9
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    Development of large earth orbital space station (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: This paper outlines the major aspects of the development of large earth orbital space stations. At the outset, the uses of the space station are surveyed and the major systems and configurational drivers enumerated. A representative 12-man space station, studied by the Space Division of North American Rockwell Corporation under NASA contract is described. The subsequent discussion centers around earth-to-orbit logistics and possible future missions with emphasis on the establishment of a branch station geosynchronous orbit. In dealing with the associated transportation between low and high orbits, the concept of a geospace shuttle station oscillating between near-earth and synchronous orbit is compared with conventional shuttle vehicles with chemical and nuclear propulsion. In the final part, the evolution of the 12-man space station to a larger space base is described.
    Keywords: SPACE VEHICLES
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  • 10
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    Finite-amplitude thermal convection in a spherical shell (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The properties of finite-amplitude thermal convection for a Boussinesq fluid contained in a spherical shell are investigated. All nonlinear terms are retained in the equations, and both axisymmetric and nonaxisymmetric solutions are studied. The velocity is expanded in terms of poloidal and toroidal vectors. Spherical surface harmonics resolve the horizontal structure of the flow, but finite differences are used in the vertical. With a few modifications, the transform method developed by Orszag (1970) is used to calculate the nonlinear terms, while Green's function techniques are applied to the poloidal equation and diffusion terms.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Fluid Mechanics; 63; May 15
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  • 11
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    On the propagation velocity of a detonation-shock combined wave (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A quasi-one-dimensional analysis and a generalized Chapman-Jouguet condition are developed for a gaseous free detonation in an inert environment. Two characteristic features derived from the results are that there exists a lower limit on the heat of combustion, the charge diameter, and the molecular weight of the ambient gas and that there are two propagation velocities for a parameter combination above a certain critical value. Therefore the detonation failure of a free gas column is a hydrodynamic rather than a chemical phenomenon.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Zeitschrift fuer angewandte Mathematik und Mechanik; 54; Mar. 197
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  • 12
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    Swept-slot film-cooling effectiveness in hypersonic turbulent flow (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Measurement results are presented for the surface equilibrium temperature downstream of swept slots, with sonic tangential air injection into a thick hypersonic turbulent boundary layer. These results are compared with unswept slot results for cooling effectiveness.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; May 1974
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  • 13
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    Mean flow development and surface heating for an attaching compressible free shear layer (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; May 1974
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  • 14
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    Space Shuttle - The new baseline (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Recent design alterations and refinements in the Space Shuttle program are considered with particular attention to the present baseline Shuttle configurations, performance characteristics, mission profiles, and flight and ground operations. Hardware and software development and testing, propulsion systems, entry trajectory events, and payload capability are covered. The refined Space Shuttle system design is characterized as one reflecting firm technical and economic considerations. Systems development is well under way, with all major contractors progressing on schedule.
    Keywords: SPACE VEHICLES
    Type: Astronautics and Aeronautics; 12; Jan. 197
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  • 15
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    Evolution of the heat transfer and flow in moderately short turbulent boundary layers in severe pressure gradients (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Journal of Heat and Mass Transfer; 17; Sept
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  • 16
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    Stability of a dual-spin satellite with two dampers (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The rotational stability of a dual-spin satellite consisting of a main body and a symmetric rotor, both spinning about a common axis, is investigated. The main body is equipped with a spring-mass damper, while a partially filled viscous ring damper is mounted on the rapidly spinning rotor. The effect of fluid motion on the rotational stability of the satellite is calculated, considering the fluid as a single particle moving in a tube with viscous damping. Time constants are obtained by solving approximate equations of motion for the nutation-synchronous and the spin-synchronous modes, and the results are found to agree well with the numerical integrations of the exact equations. A limit cycle may exist for some configurations; the nutation angle tends to increase in such cases.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 11; July 197
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  • 17
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    Aerodynamic heat transfer to RSI tile surfaces and gap intersections (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of the results of aerothermal heating tests of a simulated reusable surface insulation (RSI) tile array, performed on the sidewall of a Mach-10 hypersonic tunnel. In particular, the heating characteristics of the tile array, such as they result from heating inside the tile-expansion-space providing gaps between individual tiles, are investigated. The results include the finding that heating on the upstream face of a tile is strongly affected by the interacting longitudinal gap flow.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; June 197
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  • 18
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    Nonlinear unsteady contact heat conduction of two-layer shells in the presence of thermal radiation (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A technique is proposed for calculating the complex heat transfer of mated shells with the surrounding medium which also takes into account the temperature dependence of the contact thermal resistance between the shells. This technique can be used for thermal calculations and for calculations of the temperature stresses in two-layer space structure shells.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 169-177
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  • 19
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    Radiative cooling of bodies of arbitrary shape and variable volume in vacuum (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: On the basis of joint application of the Tolubinskii integral method and the perturbation method, the asymptotic unsteady temperature distribution is constructed for a region of arbitrary shape on the moving boundary of which there are located nonlinear heat sinks (sources), describing radiative cooling in a medium with zero temperature (in a vacuum).
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 160-168
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  • 20
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    Heat transfer with nucleate boiling of liquids under weak mass force field conditions (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The motion is examined of a vapor bubble growing and rising from a flat horizontal heater in the ideal fluid approximation and taking drag into account. Estimates are given of bubble lifetime, bubble radius at detachment, bubble detachment frequency, and time for the bubble to attain a constant rate of rise. The relations obtained for the microcharacteristics of the boiling process are used to determine the coefficients of heat transfer in developed nucleate boiling. A new form of the equations for describing heat transfer in nucleate boiling in dimensionless parameters is proposed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 131-159
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  • 21
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    Thermocapillary convection in weightless condition (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Results are presented of studies on thermocapillary instability of a liquid in a spherical layer with free surface and convection in a rectangular channel with horizontal temperature gradient. It is shown that in vessels partly filled with a viscous incompressible fluid and under essentially weightless conditions free convection may arise due to the surface tension temperature dependence.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 121-130
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  • 22
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    Transient cooling of solid bodies of classical form by radiation (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An approximate analytic method is presented for analysis of the unsteady process of radiative cooling of solid bodies of classical form. The nonlinear heat transfer problem is solved by the cascade linearization technique with use of the iteration method. Comparison of the results obtained even in the first approximation with the available numerical solutions indicates adequate engineering accuracy of the proposed technique.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 113-120
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  • 23
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    Thermal regime and temperature stresses in bodies during thermoradiational heating (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An approach is developed to the application of the perturbation method for the solution of problems with essential external nonlinearities, based on identification in the boundary condition of a small nonlinear complex which is considered a perturbing function. The solutions obtained in the first approximation with error of 1 to 2% in calculating the unsteady temperature fields are then used to determine the temperature stresses and deformations in solid bodies of classical form.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 88-98
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  • 24
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    Mars surface-to-orbit vehicles for sample return missions (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of the results of a Mars surface-to-orbit launch vehicle study using an upgraded atmospheric density profile and an ascent trajectory optimization program. Orbit insertion was achieved with velocity losses less than those found in an earlier study. Values of thrust-to-mass ratio which minimize velocity losses for dual-burn vehicles were found to be significantly greater than the values of thrust-to-launch-mass ratio for the minimum-velocity-loss continuous-burn vehicle. The use of a two-stage solid-propellant vehicle employing a spin-stabilized second stage offers an attractive design option for a Mars surface-to-orbit launch vehicle.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 11; June 197
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  • 25
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    ERTS-1, the spacecraft and its sensors (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The basic objectives of the ERTS-1 mission are defined as follows: (1) to determine what data can be acquired from an orbiting satellite on the natural and cultural resources and on the environment; and (2) to develop and demonstrate the combination of data-acquisition procedures and interpretative techniques which can make this new knowledge available for use in the many facets of man's life. A general description of the satellite's observatory system and its sensors is given, including the thermal control subsystem, the power subsystem, the attitude control subsystem, the orbit adjust subsystem, the telemetry and tracking systems, the communications and data handling subsystem, the return beam vidicon subsystem, the multispectral scanner subsystem, the two wideband video tape recorders, and the data collection subsystem.
    Keywords: SPACE VEHICLES
    Type: Journal of Environmental Sciences; 17; Mar
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  • 26
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    Skylab 1 and 2 - Pilots' report (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Details of powered flight are considered, giving attention to the lift-off, engine thrust, and separation from the S-1VB stage. The rendezvous checklist was performed on time and exactly prior to the first phasing maneuver. The Command Service Module was finally maneuvered to a position for hard docking. Attention is given to aspects of extravehicular activity during the mission and delays experienced in the separation procedure.
    Keywords: SPACE VEHICLES
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  • 27
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    Pioneer 10 (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: On Dec. 4, 1973, after 21 months in flight, Pioneer 10 passed by Jupiter at a distance within 130,000 km of its cloud tops. During the month before and after, instrumentation on the spacecraft made a number of scientific measurements of the Jupiter environment, thus completing one of three scientific objectives of the mission. Previously, Pioneer 10 had explored the asteroid belt and had completed the second scientific objective by determining that the belt did not present a hazard to spacecraft passing through it. The third objective, the exploration of interplanetary phenomena, started with the launch of Pioneer 10 and will not be completed until 1977 when the spacecraft nears the orbit of Uranus and the signal from the spacecraft becomes too weak to be heard at ground receivers.
    Keywords: SPACE VEHICLES
    Type: Science; 183; Jan. 25
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  • 28
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    Space processing experiments on sounding rockets (1974)
    In:  Other Sources
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    Publication Date: 2019-01-25
    Description: The use of sounding rockets for the conduct of, and verification of, processing experiments and techniques under conditions of weightlessness are summarized. The experimental payloads, project management, mission schedules are also discussed.
    Keywords: SPACE VEHICLES
    Type: Proc. of the 3d Space Processing Symp. on Skylab Results, Vol. 2; p 565-579
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  • 29
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    SERT D spacecraft study (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The SERT D (Space Electric Rocket Test - D) study defines a possible spacecraft project that would demonstrate the use of electric ion thrusters for long-term (5 yr) station keeping and attitude control of a synchronous orbit satellite. Other mission objectives included in the study were: station walking to satellite rendezvous and inspection, use of low cost attitude sensing system, use of an advanced solar array orientation and slip ring system, and an ion thruster integrated directly with a solar array power source. The SERT D spacecraft, if launched, will become SERT 3 the third space electric thruster test.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-71494
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  • 30
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    Apollo experience report: Thermal protection subsystem (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The Apollo command module was the first manned spacecraft to be designed to enter the atmosphere of the earth at lunar-return velocity, and the design of the thermal protection subsystem for the resulting entry environment presented a major technological challenge. Brief descriptions of the Apollo command module thermal design requirements and thermal protection configuration, and some highlights of the ground and flight testing used for design verification of the system are presented. Some of the significant events that occurred and decisions that were made during the program concerning the thermal protection subsystem are discussed.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7564 , JSC-S-383
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  • 31
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    Full wave modulator-demodulator amplifier apparatus (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A full-wave modulator-demodulator apparatus is described including an operational amplifier having a first input terminal coupled to a circuit input terminal, and a second input terminal alternately coupled to the circuit input terminal. A circuit is ground by a switching circuit responsive to a phase reference signal and the operational amplifier is alternately switched between a non-inverting mode and an inverting mode. The switching circuit includes three field-effect transistors operatively associated to provide the desired switching function in response to an alternating reference signal of the same frequency as an AC input signal applied to the circuit input terminal.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 32
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    Heat transfer to surface and gaps of RSI tile arrays in turbulent flow at Mach 10.3 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat transfer to gap walls and surface of a simulated reusable surface insulation (RSI) tile array are presented. The data were obtained in the thick, turbulent tunnel wall boundary layer of the Langley Continuous Flow Hypersonic Tunnel at a freestream Mach number of 10.3 and a freestream unit Reynolds number of one million. Pertinent test variables were: (1) tile array orientation (staggered and in-line), (2) gap width, (3) flow angularity, and (4) tile mismatch.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-71945
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  • 33
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    Computer-aided space shuttle orbiter wing design study (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An analytical and experimental investigation has been made to provide a space shuttle orbiter wing design that met the guideline requirements of landing performance, stability, and hypersonic trim for a specified center-of-gravity envelope. The analytical study was facilitated by the use of the Optimal Design Integration system (ODIN) and the experimental part of the investigation was conducted in the Langley low-turbulence pressure tunnel and the Langley continuous-flow hypersonic tunnel.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7478 , L-9099
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  • 34
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    Centaur Standard Shroud (CSS) full jettison test dynamic analysis (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: During the space power facility jettison tests, the non-domed half of the Centaur standard shroud was allowed to completely separate from its hinge connection and was caught in a horizontal catch net. A rigid body dynamic analysis that was performed to predict the half shroud prior to and after net contact is presented. Analytical predictions of the longitudinal and circumferential bending moments imposed on the half shroud by the catch net and the net pressure on the half shroud corrugated skin are also presented.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-71537 , E-7943
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  • 35
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    Removal of spacecraft-surface particulate contaminants by simulated micrometeoroid impacts (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A series of hypervelocity impacts has been conducted in an exploding lithium-wire accelerator to examine with a far-field holographic system the removal of particulate contaminants from external spacecraft surfaces subjected to micrometeoroid bombardment. The impacting projectiles used to simulate the micrometeoroids were glass spheres nominally 37 microns in diameter, having velocities between 4 and 17 km/sec. The particulates were glass spheres nominally 25, 50, and 75 microns in diameter which were placed on aluminum targets. For these test, particulates detached had velocities that were log-normally distributed. The significance of the log-normal behavior of the ejected-particulate velocity distribution is that the geometric mean velocity and the geometric standard deviation are the only two parameters needed to model completely the process of particles removed or ejected from a spacecraft surface by a micrometeoroid impact.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7494 , L-9269
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  • 36
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    Apollo experience report the command and service module milestone review process (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The sequence of the command and service module milestone review process is given, and the Customer Acceptance Readiness Review and Flight Readiness Review plans are presented. Contents of the System Summary Acceptance Documents for the two formal spacecraft reviews are detailed, and supplemental data required for presentation to the review boards are listed. Typical forms, correspondence, supporting documentation, and minutes of a board meeting are included.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7599 , JSC-S-389
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  • 37
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    Results of investigations on a 0.010-scale model of the configuration 3 space shuttle orbiter and external tank in the NASA/Ames Research Center 3.5-foot hypersonic wind tunnel (IA15) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted in a 3.5-foot hypersonic wind tunnel. The model used for this test was a 0.010-scale of the Configuration 2 Space Shuttle Orbiter and the External Tank. Six-component aerodynamic force and moment data were recorded over an angle of attack range from -8 deg to +30 deg at 0 deg and 5 deg angles of sideslip. Data was also recorded during beta sweeps of -8 deg to +10 deg at angles of attack of -10 deg, 0 deg, and 30 deg. All testing was done at Mach 7.3. Various elevon, rudder and orbiter to external tank attaching structures and fairings were tested to determine longitudinal and lateral-directional stability characteristics. Non-metric exhaust plumes were installed during a portion of the testing to determine the effects of the main propulsion system rocket plumes.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134089 , DMS-DR-2102
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  • 38
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    Feasibility of space disposal of radioactive nuclear waste. 2: Technical summary (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of transporting radioactive waste produced in the process of generating electricity in nuclear powerplants into space for ultimate disposal was investigated at the request of the AEC as a NASA in-house effort. The investigation is part of a broad AEC study of methods for long-term storage or disposal of radioactive waste. The results of the study indicate that transporting specific radioactive wastes, particularly the actinides with very long half-lives, into space using the space shuttle/tug as the launch system, appears feasible from the engineering and safety viewpoints. The space transportation costs for ejecting the actinides out of the solar system would represent less than a 5-percent increase in the average consumer's electric bill.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-2912 , E-7676
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  • 39
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    Bio-isolated dc operational amplifier (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A bio-isolated dc operational amplifier is described for use in making bioelectrical measurements of a patient while providing isolation of the patient from electrical shocks. The circuit contains a first operational amplifier coupled to the patient with its output coupled in a forward loop through a first optic coupler to a second operational amplifier. The output of the second operational amplifier is coupled to suitable monitoring circuitry via a feedback circuit including a second optic coupler to the input of the first operational amplifier.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 40
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    LC-oscillator with automatic stabilized amplitude via bias current control (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A stable excitation supply for measurement transducers is described. It consists of a single-transistor oscillator with a coil connected to the collector and a capacitor connected from the collector to the emitter. The output of the oscillator is rectified and the rectified signal acts as one input to a differential amplifier; the other input being a reference potential. The output of the amplifier is connected at a point between the emitter of the transistor and ground. When the rectified signal is greater than the reference signal, the differential amplifier produces a signal of polarity to reduce bias current and, consequently, amplification.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 41
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    Comparison of cooling effectiveness of turbine vanes with and without film cooling (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The cooling effectiveness of three film-cooled vanes were compared to the cooling effectiveness of two non-film-cooled vanes. The comparison indicated that, for the vane configurations and test conditions examined, film cooling had an adverse effect near the suction-surface trailing edge of the vanes. Film cooling was found to be beneficial on the pressure surface of the vanes.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-3022 , E-7860
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  • 42
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    Aerodynamic heating and loading within large open cavities in cone and cone-cylinder-flare models at Mach 6.7 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic heating and loading distributions within large cavities exposed by surface openings to hypersonic flow were determined in the 8-foot high-temperature structures tunnel. Cone and cone-cylinder-flare models with cavities having regular and irregular surface-opening shapes were aerothermally tested at various angles of attack up to 30 deg. Tests were conducted at a Mach number of 6.7, a total temperature of 1800 K, a dynamic pressure of 80 kPa, and a stream unit Reynolds number of 6,000,000 per meter. The results showed that the heating rates at internal reattachment were generally lower but of the same order as the corresponding external heating rates; however, other internal heating rates were an order of magnitude lower. The internal flow showed characteristics of being funneled into jets or being dispersed dependent upon the internal surface contour.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7403 , L-9157
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  • 43
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    Light bulb heat exchanger for magnetohydrodynamic generator applications - Preliminary evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The light-bulb heat-exchanger concept is investigated as a possible means of using a combustion heat source to supply energy to an inert gas MHD power generator system. In this concept, combustion gases flow through a central passage which consists of a duct with transparent walls through which heat is transferred by radiation to a radiation receiver which in turn heats the inert gas by convection. The effects of combustion-gas emissivity, transparent-wall-transmissivity, radiation-receiver emissivity, and the use of fins in the inert gas coolant passage are studied. The results indicate that inert gas outlet temperatures of 2500 K are possible for combustion temperatures of 3200 K and that sufficient energy can be transferred from the combustion gas to reduce its temperature to approximately 2000 K. At this temperature more conventional heat exchangers can be used.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7534 , E-7593
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  • 44
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    Vacuum jacketed composite propulsion feedlines for cryogenic launch and space vehicles. Volume 2: Appendixes (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N74-18505.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134554
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  • 45
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    Results of low speed wind tunnel tests on a .0405 scale model Rockwell Space Shuttle Orbiter tested both in free air and in the presence of a ground plane (OA16) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted on a .0405 scale representation of the space shuttle orbiter in a 7.75 x 11 foot low speed wind tunnel during the time period March 21, to April 17, 1973. The primary test objectives were to investigate both the aerodynamic and propulsion effects of various air breathing engine systems in free air and in the presence of the ground. The free air portion of this test investigated the aerodynamic effects of engine nacelle number, nacelle grouping, and nacelle location. For this testing the model was sting mounted on a six component internal strain gage balance entering through the model base. The ground plane portion of the aerodynamic test investigated the same nacelle effects at ground plane locations of full scale W.P. = 239.9, 209.3, 158.9, 108.5, and 7.78 in. At the conclusion of the aerodynamic test period the propulsion effects of various nacelle locations and freestream orientations in the presence of the ground were investigated.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128793 , DMS-DR-2038
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  • 46
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    Method for compression molding of thermosetting plastics utilizing a temperature gradient across the plastic to cure the article (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method is described for compression molding of thermosetting plastics composition. Heat is applied to the compressed load in a mold cavity and adjusted to hold molding temperature at the interface of the cavity surface and the compressed compound to produce a thermal front. This thermal front advances into the evacuated compound at mean right angles to the compression load and toward a thermal fence formed at the opposite surface of the compressed compound.
    Keywords: SPACE VEHICLES
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  • 47
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    Method of fabricating an article with cavities (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An article having a cavity with a thin bottom wall is provided by assembling a thin sheet, for example, a metal sheet, adjacent to the surface of a member having one or more apertures. A bonding adhesive is interposed between the thin sheet and the subadjacent member, and the thin sheet is subjected to a high fluid pressure. In order to prevent the differential pressure from being exerted against the thin sheet, the aperture is filled with a plug of solid material having a linear coefficient of thermal expansion higher than that of the member. When the assembly is subjected to pressure, the material is heated to a temperature such that its expansion exerts a pressure against the thin sheet thus reducing the differential pressure.
    Keywords: SPACE VEHICLES
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  • 48
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    An efficiency study on obtaining the minimum weight of a thermal protection system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Three minimizing techniques are evaluated to determine the most efficient method for minimizing the weight of a thermal protection system and for reducing computer usage time. The methods used (numerical optimization and nonlinear least squares) for solving the minimum-weight problem involving more than one material and more than one constraint are discussed. In addition, the one material and one constraint problem is discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-58126 , JSC-08678
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  • 49
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    A homogeneous heat pipe design code (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program was developed to facilitate parametric performance evaluation of heat pipes in lightweight heat rejection systems. A description of the code, user's manual, and sample inputs are provided. The emphasis is placed on the analysis and design of homogeneous wick heat pipes. The analysis of the annular heat pipe is included as part of the heat pipe radiator subroutine.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-136831 , JPL-TM-33-663
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  • 50
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    Apollo Saturn 511 effluent measurements from the Apollo 16 launch operations: An experiment (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experiment was performed in conjunction with the Apollo 16 launch to define operational and instrumentational problems associated with launch-vehicle exhaust effluent monitoring. Ground and airborne sampling were performed for CO, CO2, hydrocarbons, and particulates. Sampling systems included filter pads and photometers for particulates and whole-air grab samples for gases. Launch debris was identified in the particulate samples at ground level(taken immediately after launch) and in the airborne measurements (taken 40 to 50 minutes after launch approximately 40 km downwind of the pad). Operational problems were identified and included the need for higher instrumentation mobility and the need for real-time sampling instrumentation as opposed to collection-type samples such as the whole-air grab sample.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-2910 , L-9097
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  • 51
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    Demodulator for carrier transducers (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A carrier type transducer is supplied with a carrier wave via an audio amplifier, a filter, a frequency divider, and an oscillator. The carrier is modulated in accordance with the parameter being measured by the transducer and is fed to the input of a digital data system which may include a voltmeter. The output of the oscillator and the output of each stage of the divider are fed to an AND or a NAND gate and suitable variable and fixed delay circuits to the command input of the digital data system. With this arrangement, the digital data system is commanded to sample at the proper time so that the average voltage of the modulated carrier is measured. It may be utilized with ancillary circuitry for control of the parameter
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 52
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    System for stabilizing cable phase delay utilizing a coaxial cable under pressure (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Stabilizing the phase delay of signals passing through a pressurizable coaxial cable is disclosed. Signals from an appropriate source at a selected frequency, e.g., 100 MHz, are sent through the controlled cable from a first cable end to a second cable end which, electrically, is open or heavily mismatched at 100 MHz, thereby reflecting 100 MHz signals back to the first cable end. Thereat, the phase difference between the reflected-back signals and the signals from the source is detected by a phase detector. The output of the latter is used to control the flow of gas to or from the cable, thereby controlling the cable pressure, which in turn affects the cable phase delay.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 53
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    Apollo experience report: Development and use of specialized radio equipment for Apollo recovery operations (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: New personal communications equipment was required for the Apollo Program recovery operations. Two new, small, personal radios were developed and used successfully in the Apollo recovery program.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7587 , JSC-S-385
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  • 54
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    Effects of pressure, oxygen concentration, and forced convection on flame spread rate of Plexiglas, Nylon and Teflon (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experiments were conducted in which the burning of cylindrical materials in a flowing oxidant stream was studied. Plexiglas, Nylon, and Teflon fuel specimens were oriented such that the flames spread along the surface in a direction opposed to flowing gas. Correlations of flame spread rate were obtained that were power law relations in terms of pressure, oxygen concentration, and gas velocity.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7555 , E-7611
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  • 55
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    Spacecraft control section for the improved Small Astronomy Satellite (SAS) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The upgraded spacecraft control section for the Small Astronomy Satellite is able to point its thrust axis to any direction in space; it can also spin or slow its outer body rotation to zero for star-locked pointing of side viewing experiments. A programmable telemetry system and delayed command system enhance the inherent capability of a spacecraft designed to be used for a variety of experiments, each of which can be built independently and attached just prior to final acceptance testing and launch. The design of this new spacecraft, whose first launch is scheduled for 1975, is provided in sufficient detail to permit the reader to ascertain its suitability for specific experiments. A summary of the spacecraft characteristics, project reliability requirements, and environmental test conditions are included in the appendices.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-70569 , X-405-74-7
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  • 56
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    Film cooling in a combustor operating at fuel-rich exit conditions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Data were taken with a film-cooled test plate placed in the exhaust stream of a rectangular combustor. Results showed that in a fuel-rich zone, fuel entrained into the film-cooling air would burn at the conditions tested. Test conditions were cooling-gas flow rates, 9.5 and 5 percent of total gas flow; cooling-gas velocities, 23 and 12 m/sec; ambient-temperature cooling gas; hot-gas velocity, nominally 215 m/sec; fuel-air ratio to stoichiometric fuel-air ratio values of 0.1, 0.8, 1.0, 1.2, and 1.35, resulting in hot-gas temperatures from 590 to 2100 K; and atmospheric pressure. Analytical prediction of wall temperatures agreed reasonably well with experimental results.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7513 , E-7561
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  • 57
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    Liquefaction dynamics of n-octadecane in cylindrical coordinates (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The study presents one method of mathematically modeling the effects of gravity-induced free convection upon the melting phenomena of a finite paraffin slab. The theoretical model is based on the numerical computer solution of the solid phase and liquid phase energy equations, coupled with an imposed ideal-viscous flow approximation. An implicit alternating-direction technique is used as the finite-difference approximation for the basic energy equations in the numerical solution. The theoretical predictions are compared to experimental data from an annular test cell, in which n-octadecane, C18H38, was used as the test material. The results show that the model is a good first approximation to the solution of solid-liquid phase change involving gravity-induced free convection.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; May 1974
    Format: text
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  • 58
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    Unsteady temperature distribution in volume reflectors (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The development of unsteady temperature distributions in semitransparent scattering materials under the influence of arbitrary incident radiative flux with other than specified temperature boundary conditions is considered. Specifically, such a problem is considered for an approximate radiative transfer model which allows analytic solutions. The model represents the unsteady, one-dimensional, radiative heating of a weakly absorbing, semitransparent medium with specified conductive heat flux at one boundary. The radiation field is modeled using an approximation to the radiative heat flux obtained by solution of the Kubelka-Munk differential equations.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 12; May 1974
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  • 59
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    Automatic spacecraft detumbling by internal mass motion (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: In the operation of future manned space vehicles, there will always be a finite probability that an accident will occur which results in uncontrolled tumbling of a craft. Hard docking by a manned rescue vehicle is not acceptable because of the hazardous environment to which rescue crewmen would be exposed and excessive maneuvering accelerations during docking operations. A movable-mass control concept, which is activated upon initiation of tumbling and is autonomous, can convert tumbling motion into simple spin. The complete equations of motion for an asymmetric rigid spacecraft containing a movable mass are presented, and appropriate control law and system parameters are selected to minimize kinetic energy, resulting in simple spin about the major principal axis. Simulations indicate that for a large space station experiencing a collision, which results in tumbling, a 1% movable mass is capable of stabilizing motion in 2 hr.
    Keywords: SPACE VEHICLES
    Type: AIAA Journal; 12; Apr. 197
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  • 60
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    A movable-mass attitude stabilization system for cable-connected artificial-g space stations (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The development of an active, momentum-exchange system to be used for attitude stabilization of a class of cable-connected artificial-g space stations is studied. A system which employs a single movable control mass is examined for the control of a space station which has the physical appearance of two cylinders connected axially by cables. The dynamic model for the space station includes its aggregate rigid body rotation and relative torsional rotation between the bodies. A zero torsional stiffness design (one cable) and a maximum torsional stiffness design (eight cables) are examined in various stages of deployment, for selected spin velocities ranging from 4 rpm upwards. A linear, time-invariant, feed-back control system is employed, with gains calculated via a root-specification procedure. The movable mass controller provides critical wobble-damping capability for the crew quarters for all configurations and spin velocity.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 11; Mar. 197
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  • 61
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    Investigations on an 0.030-scale space shuttle vehicle configuration 140A/B orbiter model in the Ames Research Center 9 by 7-foot supersonic wind tunnel (OA53B) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind tunnel test of an 0.030-scale space shuttle vehicle orbiter configuration 140A/B model was conducted in the Ames Research Center 9- by 7-foot supersonic wind tunnel. This part of test series OA53 was conducted at Mach numbers of 1.60 and 2.00 and at Reynolds numbers ranging from 1.0 million per foot to 4.0 million per foot. The objective was to establish and verify longitudinal and lateral-directional aerodynamic performance, stability, and control characteristics for the configuration 140A/B SSV orbiter. Reynolds number studies were performed on certain nominal control-setting configurations, and examinations were made of the incremental effects of an alternate wing leading-edge configuration and of a sealed elevon-split construction. Six-component force and moment data, base and cavity pressures, bodyflap, elevon, speedbrake, and rudder hinge moments, and vertical tail forces and moments were measured for the orbiter.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134119 , DMS-DR-2178
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  • 62
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    Heat transfer tests of an 0.006-scale thin skin space shuttle thermocouple model (41-0) in the Langley Research Center variable density tunnel at M equals 8 (OH13) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Orbiter entry heating distributions were obtained, and phase change paint data was correlated with thermocouple data during a program of heat transfer testing on a 0.006 scale space shuttle orbiter vehicle. The orbiter was tested at 0, 30, and 35 degrees angle of attack at Reynolds numbers of 1, 2, 3, 4, and 6 million per foot. Temperature data were obtained from a total of 57 thermocouples.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134101 , DMS-DR-2096
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  • 63
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    Results of tests in the NASA/LaRC 31-inch CFHT on an 0.010-scale model (32-OT) of the space shuttle configuration 3 to determine the RCS jet flowfield interaction effects on aerodynamic characteristics (IA60/0A105), volume 2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted in the NASA Langley Research Center 31-inch continuous flow hypersonic wind tunnel from 14 February to 22 February 1974, to determine RCS jet interaction effect on the hypersonic aerodynamic and stability and control characteristics prior to RTLS abort separation. The model used was an 0.010-scale replica of the space shuttle vehicle configuration 3. Hypersonic stability data were obtained from tests at Mach 10.3 and dynamic pressure of 150 psf for the intergrated orbiter and external tank and the orbiter alone. RCS modes of pitch, yaw, and roll at free flight dynamic pressure simulation of 7, 20, and 50 psf were investigated. The effects of speedbrake, bodyflap, elevon, and aileron deflections were also investigated.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134106 , DMS-DR-2137-VOL-2
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  • 64
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    Investigation of space shuttle orbiter subsonic stability and control characteristics in the NAAL low speed wind tunnel (OA62B), volume 2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted on a sting-mounted 0.0405 scale representation of the 140A/B space shuttle orbiter in a 7.75 ft by 11 ft low speed wind tunnel during the period from November 14, 1973 to December 6, 1973. Establishment of basic longitudinal stability characteristics in and out of ground effect, and the establishment of lateral-directional stability characteristics in free air were the primary test objectives. The following effects and configurations were tested: (1) two dual podded nacelle configurations; (2) stability and control characteristics at nominal elevon deflections, rudder deflections, airleron deflections, rudder flare angles, and body flap deflections; (3) effects of various elevon and elevon/fuselage gaps on longitudinal stability and control; (4) pressures on the vertical tail at spanwise stations using pressure bugs; (5) aerodynamic force and moment data measured in the stability axis system by an internally mounted, six-component strain gage balance. For Vol. 1, see N74-32324.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134113 , DMS-DR-2104-VOL-2
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  • 65
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    A study of the feasibility of directly applying gas generator systems to space shuttle mechanical functions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This study examined the current status and potential application of pyrotechnic gas generators and energy convertors for the space shuttle program. While most pyrotechnic devices utilize some form of linear actuation, only limited use of rotary actuators has been observed. This latter form of energy conversion, using a vane-type actuator as optimum, offers considerable potential in the area of servo, as well as non-servo systems, and capitalizes on a means of providing prolonged operating times. Pyrotechnic devices can often be shown to provide the optimum means of attaining a truly redundant back-up to a primary, non-pyrotechnic system.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-2454
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    Apparatus for forming drive belts (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An apparatus for manufacturing belts, such as seamless belts, is provided, the apparatus has relatively movable rollers that are mounted in an oven. A belt blank, for example, of a thin polyester film, is rotated on the rollers as heat is applied. Four rollers, each mounted on a separate roller assembly, are movable along appropriate tracks while a fifth centrally located roller is stationary. A pair of dc motors are operatively connected to a speed reduction gear assembly to provide a pair of rotating drive shafts that extend into the oven. One rotating shaft drives all of the rollers through a rotational gear assembly while the other drive shaft is capable of positioning the movable rollers through respective rotating threaded shafts. Control devices are provided for controlling the motors while measuring devices are operatively connected to the positional drive shaft to indicate the position of the rollers.
    Keywords: SPACE VEHICLES
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    Capacitance multiplier and filter synthesizing network (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A circuit using a differential amplifier multiplies the capacitance of a discrete interating capacitor by (r sub 1 + R sub 2)/R sub 2, where R sub 1 and R sub 2 are values of discrete resistor coupling an input signal e sub 1 of the amplifier inputs. The output e sub 0 of the amplifier is fed back and added to the signal coupled by the resistor R sub 2 to the amplifier through a resistor of value R sub 1. A discrete resistor R sub x may be connected in series for a lag filter, and a discrete resistor may be connected in series with the capacitor for a lead-lag filter. Voltage dividing resistors R sub a and R sub b may be included in the feedback circuit of the amplifier output e sub o to independently adjust the circuit gain e sub i/e sub o.
    Keywords: THERMODYNAMICS AND COMBUSTION
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    The definition and specification of the near earth environmental criteria for spacecraft thermal design (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The variation of the earth's thermal and albedo radiation received by a near-earth orbiting space vehicle or space payload as a result of temporal variation of the earth atmosphere is discussed. A statistical study of current satellite data for determining probability distributions is proposed. With these distributions the thermal designer can define confidence levels on predicted temperature ranges which are compatible with engineering models for use in design, failure probabilities, and spacecraft cost estimates. Use of the distributions in environmental criteria guidelines is also considered.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64870
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    Development of electrical feedback controlled heat pipes and the advanced thermal control flight experiment (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development and characteristics of electrical feedback controlled heat pipes (FCHP) are discussed. An analytical model was produced to describe the performance of the FCHP under steady state and transient conditions. An advanced thermal control flight experiment was designed to demonstrate the performance of the thermal control component in a space environment. The thermal control equipment was evaluated on the ATS-F satellite to provide performance data for the components and to act as a thermal control system which can be used to provide temperature stability of spacecraft components in future applications.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-114751 , DTM-74-2
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    Asymmetrical booster ascent guidance and control system design study. Volume 1: Summary (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Dynamics and control, stability, and guidance analyses are summarized for the asymmetrical booster ascent guidance and control system design studies, performed in conjunction with space shuttle planning. The mathematical models developed for use in rigid body and flexible body versions of the NASA JSC space shuttle functional simulator are briefly discussed, along with information on the following: (1) space shuttle stability analysis using equations of motion for both pitch and lateral axes; (2) the computer program used to obtain stability margin; and (3) the guidance equations developed for the space shuttle powered flight phases.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134398 , REPT-5-2581-HOU-154-VOL-1
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    Asymmetrical booster guidance and control system design study. Volume 3: Space shuttle vehicle SRB actuator failure study (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The investigation of single actuator failures on the space shuttle solid rocket booster required the analysis of both square pattern and diamond pattern actuator configurations. It was determined that for failures occuring near or prior to the region of maximum dynamic pressure, control gain adjustments can be used to achieve virtually nominal mid-boost vehicle behavior. A distinct worst case failure condition was established near staging that could significantly delay staging. It is recommended that the square pattern be retained as a viable alternative to the baseline diamond pattern because the staging transient is better controlled resulting in earlier staging.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134400 , REPT-5-2581-HOU-154-VOL-3
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    Space shuttle SRM interim contract, part 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Essential studies and analyses required to integrate the SRM into the booster and overall space shuttle system. Emphasis was placed on the case, nozzle, insulation, and propellant components with resulting performance, weight, and structural load characteristics being generated. Effort conducted during the time period of this contract included studies, analyses, planning, and preliminary design activities. Technical requirements identified in the SRM Project Request for Proposal No. 8-1-4-94-98401 and Thiokol's proposed SRM design (designated Configuration 0) established the basis for this effort. The requirements were evaluated jointly with MSFC and altered where necessary to incorporate new information that evolved after issuance of the RFP and during the course of this interim contract. Revised water impact loads and load distributions were provided based on additional model test data and analytical effort conducted by NASA subsequent to the RFP release. Launch pad peaking loads into the SRM aft skirt were provided which also represented a change from RFP requirements. A modified SRM/External Tank (ET) attachment configuration with new structural load data was supplied by NASA, and direction was received to include a 2 percent inert weight contingency.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120404 , TWR-10075-PT-1 , PUBL-74334-PT-1
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    GEOS observation systems intercomparison investigation results (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of an investigation designed to determine the relative accuracy and precision of the different types of geodetic observation systems used by NASA is presented. A collocation technique was used to minimize the effects of uncertainties in the relative station locations and in the earth's gravity field model by installing accurate reference tracking systems close to the systems to be compared, and by precisely determining their relative survey. The Goddard laser and camera systems were shipped to selected sites, where they tracked the GEOS satellite simultaneously with other systems for an intercomparison observation.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-70722 , X-932-74-212
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    Atmospheric entry probes for outer planet exploration. Outer planet entry probe technical summary (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of unmanned space probes for investigating the conditions existing on and around the outer planets of the solar system is discussed. The subjects included in the report are: (1) the design of a common entry probe for outer planet missions, (2) the significant trades related to the development of a common probe design, (3) the impact of bus selection on probe design, (4) the impact of probe requirements on bus modifications, and (5) the key technology elements recommended for advanced development. Drawings and illustrations of typical probes are included to show the components and systems used in the space probes.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-137542
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    Operations analysis (study 2.1): Payload designs for space servicing (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Potential modes of operating in space in the space shuttle era are documented. The October 1973 NASA Mission Model provides a definition of various NASA and non-DOD automated payload configurations when employed in an expendable mode. The model also specifies a launch schedule for initial deployment of payloads as well as for subsequent replacements at periodic cycles. This model and its associated payload definitions serve as a foundation for the data presented in this report. The reference model has been revised to reflect automated space servicing of payloads as an operational concept instead of the existing expendable approach. The indication is that the bulk of a payload's subsystems and mission equipment require no support over the lifetime of the program. However, failure of a single unit could result in loss of the mission objectives. When space servicing is employed, the approach is to replace only that unit causing the anomaly. This concept affords an opportunity to standardize space replacable units, as well as to reduce the expense of logistics support, by allowing multiple servicing on any single upper stage/shuttle flight.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-139588 , ATR-74(7341)-3
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  • 76
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    Space shuttle/payload interface analysis. Volume 4: Business Risk and Value of Operations in Space (BRAVO). Part 3: Workbook (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A collection of blank worksheets for use on each BRAVO problem to be analyzed is supplied, for the purposes of recording the inputs for the BRAVO analysis, working out the definition of mission equipment, recording inputs to the satellite synthesis computer program, estimating satellite earth station costs, costing terrestrial systems, and cost effectiveness calculations. The group of analysts working BRAVO will normally use a set of worksheets on each problem, however, the workbook pages are of sufficiently good quality that the user can duplicate them, if more worksheet blanks are required than supplied. For Vol. 1, see N74-12493; for Vol. 2, see N74-14530.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-139592 , ATR-74(7334)-1-VOL-4-PT-3
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    Reusable Agena study. Volume 2: Technical (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The application of the existing Agena vehicle as a reusable upper stage for the space shuttle is discussed. The primary objective of the study is to define those changes to the Agena required for it to function in the reusable mode in the 100 percent capture of the NASA-DOD mission model. This 100 percent capture is achieved without use of kick motors or stages by simply increasing the Agena propellant load by using optional strap-on-tanks. The required shuttle support equipment, launch and flight operations techniques, development program, and cost package are also defined.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120362 , LMSC-D383059-VOL-2
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  • 78
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    Space shuttle/payload interface analysis. Volume 4: Business Risk and Value of Operations in Space (BRAVO). Part 1: Summary (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Background information is provided which emphasizes the philosophy behind analytical techniques used in the business risk and value of operations in space (BRAVO) study. The focus of the summary is on the general approach, operation of the procedures, and the status of the study. For Vol. 1, see N74-12493; for Vol. 2, see N74-14530.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-139591 , ATR-74(7334)-1-VOL-4-PT-1
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    Viscosity and thermal conductivity coefficients of gaseous and liquid oxygen (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Equations and tables are presented for the viscosity and thermal conductivity coefficients of gaseous and liquid oxygen at temperatures between 80 K and 400 K for pressures up to 200 atm. and at temperatures between 80 K and 2000 K for the dilute gas. A description of the anomalous behavior of the thermal conductivity in the critical region is included. The tabulated coefficients are reliable to within about 15% except for a region in the immediate vicinity of the critical point. Some possibilities for future improvements of this reliability are discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-2440
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    Hypersonic stability and control characteristics of the Rockwell International 139-B space shuttle orbiter (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The purpose of this study was to determine the hypersonic aerodynamic performance, longitudinal trim, static stability, and the extent of the center-of-gravity boundaries within the design control limits as well as to examine the effect of Reynolds number on the longitudinal stability of the 139-B space shuttle orbiter. A 0.004 scale model (34-0)was tested in helium over an angle-of-attack range of 18 deg to 54 deg at 0 deg and -minus 5 deg sideslip angles. The total pressure was varied for selected configurations to obtain a Reynolds number range, based on model length, from 0.51 million to 3.6 million at Mach numbers between 17.6 and 21.6 Surface oil-flow studies and electron-beam illuminated-flow studies were also conducted at angles-of-attack of 30 deg, 40 deg, and 50 deg for selected Reynolds numbers.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-71968
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    Parachute-deployment-parameter identification based on an analytical simulation of Viking BLDT AV-4 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A six-degree-of-freedom analytical simulation of parachute deployment dynamics developed at the Langley Research Center is presented. A comparison study was made using flight results from the Viking Balloon Launched Decelerator Test (BLDT) AV-4. Since there are significant voids in the knowledge of vehicle and decelerator aerodynamics and suspension system physical properties, a set of deployment-parameter input has been defined which may be used as a basis for future studies of parachute deployment dynamics. The study indicates the analytical model is sufficiently sophisticated to investigate parachute deployment dynamics with reasonable accuracy.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7678
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    Analysis of combustion instability in liquid propellant engines with or without acoustic cavities (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytical studies have been made of the relative combustion stability of various propellant combinations when used with hardware configurations representative of current design practices and with or without acoustic cavities. Two combustion instability models, a Priem-type model and a modification of the Northern Research and Engineering (NREC) instability model, were used to predict the variation in engine stability with changes in operating conditions, hardware characteristics or propellant combination, exclusive of acoustic cavity effects. The NREC model was developed for turbojet engines but is applicable to liquid propellant engines. A steady-state combustion model was used to predict the needed input for the instability models. In addition, preliminary development was completed on a new model to predict the influence of an acoustic cavity with specific allowance for the effects the nozzle, steady flow and combustion.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-134387 , R-9353
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    Reusable Centaur study. Volume 2: Final report (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N74-31346.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120373 , CASD-NAS-73-032-VOL-2
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    Payload/orbiter contamination control requirement study (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was conducted to determine and quantify the expected particulate and molecular on-orbit contaminant environment for selected space shuttle payloads as a result of major shuttle orbiter contamination sources. Individual payload susceptibilities to contamination are reviewed. The risk of payload degradation is identified and preliminary recommendations are provided concerning the limiting factors which may depend on operational activities associated with the payload/orbiter interface or upon independent payload functional activities. A basic computer model of the space shuttle orbiter which includes a representative payload configuration is developed. The major orbiter contamination sources, locations, and flux characteristics based upon available data have been defined and modeled.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120379 , MCR-74-93
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    MSFC Skylab Apollo Telescope Mount (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A technical history and management critique of the Skylab Apollo Telescope Mount (ATM) from initial conception through the design, manufacturing, testing and prelaunch phases is presented. A mission performance summary provides a general overview of the ATM's achievements in relationship to its design goals. Recommendations and conclusions applicable to hardware design, test program philosophy and performance, and program management techniques for the ATM with potential application to future programs are also discussed.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64811
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  • 86
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    MSFC Skylab thermal and environmental control system mission evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An evaluation of the performance of the Skylab thermal and environmental control system is presented. Actual performance is compared to design and functional requirements and anomalies and discrepancies and their resolution are discussed. The thermal and environmental control systems performed their intended role. Based on the experience gained in design, development and flight, recommendations are provided which may be beneficial to future system designs.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64822
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  • 87
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    Studies of heat source driven natural convection (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Natural convection energy transport in a horizontal layer of internally heated fluid with a zero heat flux lower boundary, and an isothermal upper boundary, has been studied. Quantitative information on the time-mean temperature distribution and the fluctuating component of temperature about the mean temperature in steady turbulent convection are obtained from a small thermocouple inserted into the layer through the upper bounding plate. Data are also presented on the development of temperature at several vertical positions when the layer is subject to both a sudden increase and to a sudden decrease in power input. For changes of power input from zero to a value corresponding to a Rayleigh number much greater than the critical linear stability theory value, a slight hysteresis in temperature profiles near the upper boundary is observed between the heat-up and cool-down modes.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-70232 , TR-3746-1
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  • 88
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    MSFC Skylab electrical power systems mission evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design, development, and operation of the Skylab electrical power system are discussed. The electrical systems for the airlock module of the orbital workshop and the Apollo telescope mount are described. Skylab is considered an integral laboratory, however, both cluster and module hardware distinct sections are included. Significant concept and requirement evolution, testing, and modifications resulting from tests are briefly summarized to aid in understanding the launch configuration description and the procedures and performance discussed for in-orbit operation. Specific problems encountered during Skylab orbital missions are analyzed.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64818
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  • 89
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    An analysis of the Venera 8 measurements (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analysis of the Venera 8 measurements yielded equatorial morning terminator horizontal and vertical winds which are similar to the winds obtained from the Venera 7 measurements. The lower boundary of the horizontal retrograde 4-day wind is defined by a 50-60% decrease in wind speed in the vicinity of 44 km and there exists a retrograde wind plateau of 15 to 40 m/s winds extending from 40 km down to the vicinity of 18 km where the winds decrease rapidly to the order of 0.1 m/s near the surface. Up drafts of 2 to 5 m/s exist in the vicinity of 20 to 30 km and are apparently associated with a slightly super adiabatic lapse rate. The temperature lapse-rate, surface radius, surface topography, and atmospheric structure are discussed.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-70706 , X-623-74-37
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  • 90
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    Comparative evaluation of existing expendable upper stages for space shuttle (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of existing expendable upper stages in the space shuttle during its early years of operation is evaluated. The Burner 2, Scout, Delta, Agena, Transtage, and Centaur were each studied under contract by their respective manufacturers to determine the extent and cost of the minimum modifications necessary to integrate the stage with the shuttle orbiter. A comparative economic analysis of thirty-five different families of these stages is discussed. Results show that the overall transportation system cost differences between many of the families are quite small. However, by considering several factors in addition to cost, it is possible to select one family as being representative of the capability of the minimum modification existing stage approach. The selected family meets all of the specified mission requirements during the early years of shuttle operation.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-71579 , E-8026
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  • 91
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    Skylab thruster attitude control system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Preflight activities and the Skylab mission support effort for the thruster attitude control system (TACS) are documented. The preflight activities include a description of problems and their solutions encountered in the development, qualification, and flight checkout test programs. Mission support effort is presented as it relates to system performance assessment, real-time problem solving, flight anomalies, and the daily system evaluation. Finally, the detailed flight evaluation is presented for each phase of the mission using system telemetry data. Data assert that the TACS met or exceeded design requirements and fulfilled its assigned mission objectives.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64852
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  • 92
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    MSFC Skylab lessons learned (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Key lessons learned during the Skylab Program that could have impact on on-going and future programs are presented. They present early and sometimes subjective opinions; however, they give insights into key areas of concern. These experiences from a complex space program management and space flight serve as an early assessment to provide the most advantage to programs underway. References to other more detailed reports are provided.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64860
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    Research study on stabilization and control: Modern sampled-data control theory. Continuous and discrete describing function analysis of the LST system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The dynamics of the Large Space Telescope (LST) control system were studied in order to arrive at a simplified model for computer simulation without loss of accuracy. The frictional nonlinearity of the Control Moment Gyroscope (CMG) Control Loop was analyzed in a model to obtain data for the following: (1) a continuous describing function for the gimbal friction nonlinearity; (2) a describing function of the CMG nonlinearity using an analytical torque equation; and (3) the discrete describing function and function plots for CMG functional linearity. Preliminary computer simulations are shown for the simplified LST system, first without, and then with analytical torque expressions. Transfer functions of the sampled-data LST system are also described. A final computer simulation is presented which uses elements of the simplified sampled-data LST system with analytical CMG frictional torque expressions.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120331
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    A system for spacecraft attitude control and energy storage (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A conceptual design for a double-gimbal reaction-wheel energy-wheel device which has three-axis attitude control and electrical energy storage capability is given. A mathematical model for the three-axis gyroscope (TAG) was developed, and a system of multiple units is proposed for attitude control and energy storage for a class of spacecraft. Control laws were derived to provide the required attitude-control torques and energy transfer while minimizing functions of TAG gimbal angles, gimbal rates, reaction-wheel speeds, and energy-wheel speed differences. A control law is also presented for a magnetic torquer desaturation system. A computer simulation of a three-TAG system for an orbiting telescope was used to evaluate the concept. The results of the study indicate that all control and power requirements can be satisfied by using the TAG concept.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7582 , L-9271
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  • 95
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    Apollo 16 mission report. Supplement 2: Service Propulsion system final flight evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Apollo 16 Mission was the sixteenth in a series of flights using Apollo flight hardware and included the fifth lunar landing of the Apollo Program. The Apollo 16 Mission utilized CSM 113 which was equipped with SPS Engine S/N 66 (Injector S/N 137). The engine configuration and expected performance characteristics are presented. Since previous flight results of the SPS have consistently shown the existence of a negative mixture ratio shift, SPS Engine S/N 66 was reorificed to increase the mixture ratio for this mission. The propellant unbalance for the two major engine firings is compared with the predicted unbalance. Although the unbalance at the end of the TEI burn is significantly different than the predicted unbalance, the propellant mixture ratio was well within limits. The SPS performed six burns during the mission, with a total burn duration of 575.3 seconds. The ignition time, burn duration and velocity gain for each of the six SPS burns are reported.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134365 , TRW-20029-H160-R0-00-SUPPL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 96
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    Digital servo controller (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A system, for generating a signal to control the rotation of a shaft supporting an antenna so that the antenna is rotated the shortest angular distance from a present angular position to a new desired angular position, was described. The system comprises a shaft encoder which generates a digital encoder signal indicating the present position of the shaft. A command signal is compared with the encoder signal to produce an analog signal for rotating the antenna. An error signal is produced for controlling the direction of rotation of the antenna.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 97
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    Results of tests in the NASA/LARC 31-inch CFHT on an 0.010-scale model (32-OT) of the space shuttle configuration 3 to determine the RCS jet flowfield interaction effects on aerodynamic characteristics (IA60/OA105), volume 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted in the NASA Langley Research Center 31-inch continuous Flow Hypersonic Wind Tunnel to determine RCS jet interaction effect on the hypersonic aerodynamic and stability and control characteristics prior to return to launch site (RTLS) abort separation. The model used was an 0.010-scale replica of the Space Shuttle Vehicle Configuration 3. Hypersonic stability data were obtained from tests at Mach 10.3 and dynamic pressure of 150 psf for the integrated Orbiter and external tank and the Orbiter alone. RCS modes of pitch, yaw, and roll at free flight dynamic pressure simulation of 7, 20, and 50 psf were investigated. The effects of speedbrake, bodyflap, elevon, and aileron deflections were also investigated.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134103 , DMS-DR-2137
    Format: application/pdf
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  • 98
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    Effluent sampling of Scout D and Delta launch vehicle exhausts (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Characterization of engine-exhaust effluents (hydrogen chloride, aluminum oxide, carbon dioxide, and carbon monoxide) has been attempted by conducting field experiments monitoring the exhaust cloud from a Scout-Algol III vehicle launch and a Delta-Thor vehicle launch. The exhaust cloud particulate size number distribution (total number of particles as a function of particle diameter), mass loading, morphology, and elemental composition have been determined within limitations. The gaseous species in the exhaust cloud have been identified. In addition to the ground-based measurements, instrumented aircraft flights through the low-altitude, stabilized-exhaust cloud provided measurements which identified CO and HCI gases and Al2O3 particles. Measurements of the initial exhaust cloud during formation and downwind at several distances have established sampling techniques which will be used for experimental verification of model predictions of effluent dispersion and fallout from exhaust clouds.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-2987 , L-9360
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 99
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    Aerodynamic and flow visualization studies of variations in the geometry of irregular planform wings at a Mach number of 20.3 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The longitudinal and summary lateral-directional stability characteristics have been obtained for a variety of irregular planform wings applied to a conceptual space shuttle orbiter. Three basic wing planforms with leading-edge sweep angles of 53.2 deg, 46.8 deg, and 35 deg were studied in conjunction with a series of inboard planform fillets with sweep angles up to 78 deg. The spanwise intersection point of the fillets and the basic wings was held constant. The data were obtained in the Langley 22-inch helium tunnel at a Mach number of 20.3 and a Reynolds number of 2.10 million based on model length. Model angle-of-attack range was from 0 deg to 54 deg at sideslip angles of 0 deg and minus 3.8 deg. Also included are results of a flow-visualization study consisting of electron-beam-illuminated flow and surface oil-flow patterns.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7650 , L-9382
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  • 100
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    Radiative property investigation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A detailed formulation of radiative heat transfer problems involving the use of bidirectional reflectance is discussed. Except for very simple systems this formulation is very intricate. For this reason and the fact that bidirectional data are scarce, such a formulation is not in common use. However, with the development of the digital computer there have been numerical methods developed for detailed radiative investigations using the bidirectional reflectance. Since computations using bidirectional reflectance are coming into use for spacecraft radiative studies, it is necessary to have reflectance data on the materials involved. Materials that are frequently studied are coatings which are used in controlling the thermal environment of spacecrafts. This study is primarily concerned with the bidirectional reflectance of zinc oxide which is one constituent commonly used for coatings.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-138459
    Format: application/pdf
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