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  • SPACE VEHICLES  (5,149)
  • AUXILIARY SYSTEMS  (2,897)
  • 1970-1974  (3,777)
  • 1965-1969  (4,267)
  • 1950-1954  (2)
  • 1925-1929
Collection
Keywords
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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    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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  • 5
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    The community satellite 1 (1974)
    In:  Other Sources
    Details
    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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  • 6
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    Development of large earth orbital space station (1974)
    In:  Other Sources
    Details
    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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  • 7
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    Space Shuttle - The new baseline (1974)
    In:  Other Sources
    Details
    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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  • 8
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    Stability of a dual-spin satellite with two dampers (1974)
    In:  Other Sources
    Details
    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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  • 9
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    Improvement of electric characteristics of lead accumulators under the action of ultrasounds (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Results are given of experiments conducted in order to improve the electric characteristics of lead accumulators by ultrasonic irradiation of their electrolytes. The experimental results discussed complete the research conducted on static Le2, Le3 and D. Quaiser cells whose solutions were irradiated beforehand with ultrasounds of the frequency of 1 MHz. It is demonstrated that the discharge currents and capacitances of the investigated cells keep to higher values even 1 year after ultrasonic irradiation of the electrolyte. The experimental results are discussed.
    Keywords: AUXILIARY SYSTEMS
    Type: The 4th Natl. Conf. on Acoustics, Vol. 2, B (NASA-TT-F-15663); p 204-209
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  • 10
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    Mars surface-to-orbit vehicles for sample return missions (1974)
    In:  Other Sources
    Details
    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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  • 11
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    ERTS-1, the spacecraft and its sensors (1974)
    In:  Other Sources
    Details
    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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  • 12
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    Skylab 1 and 2 - Pilots' report (1974)
    In:  Other Sources
    Details
    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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  • 13
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    Pioneer 10 (1974)
    In:  Other Sources
    Details
    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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  • 14
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    Space processing experiments on sounding rockets (1974)
    In:  Other Sources
    Details
    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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  • 15
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    SERT D spacecraft study (1974)
    In:  CASI
    Details
    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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  • 16
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    Apollo experience report: Thermal protection subsystem (1974)
    In:  CASI
    Details
    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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  • 17
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    Computer-aided space shuttle orbiter wing design study (1974)
    In:  CASI
    Details
    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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  • 18
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    Centaur Standard Shroud (CSS) full jettison test dynamic analysis (1974)
    In:  CASI
    Details
    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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  • 19
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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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  • 20
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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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  • 21
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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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  • 22
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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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  • 23
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    The development of a solar-powered residential heating and cooling system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Efforts to demonstrate the engineering feasibility of utilizing solar power for residential heating and cooling are described. These efforts were concentrated on the analysis, design, and test of a full-scale demonstration system which is currently under construction at the National Aeronautics and Space Administration, Marshall Space Flight Center, Huntsville, Alabama. The basic solar heating and cooling system under development utilizes a flat plate solar energy collector, a large water tank for thermal energy storage, heat exchangers for space heating and water heating, and an absorption cycle air conditioner for space cooling.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TM-X-70089 , M-TU-74-3
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  • 24
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    Comparative evaluation of solar, fission, fusion, and fossil energy resources. Part 1: Solar energy (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The utilization of solar energy to meet the energy needs of the U.S. is discussed. Topics discussed include: availability of solar energy, solar energy collectors, heating for houses and buildings, solar water heater, electric power generation, and ocean thermal power.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-137242
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  • 25
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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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  • 26
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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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  • 27
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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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  • 28
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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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  • 29
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    High voltage solar array experiments (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The interaction between the components of a high voltage solar array and a simulated space plasma is studied to obtain data for the design of a high voltage solar array capable of 15kW at 2 to 16kV. Testing was conducted in a vacuum chamber 1.5-m long by 1.5-m diameter having a plasma source which simulated the plasma conditions existing in earth orbit between 400 nautical miles and synchronous altitude. Test samples included solar array segments pinholes in insulation covering high voltage electrodes, and plain dielectric samples. Quantitative data are presented in the areas of plasma power losses, plasma and high voltage induced damage, and dielectric properties. Limitations of the investigation are described.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-121280
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  • 30
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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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  • 31
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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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  • 32
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    Design of H2-O2 space shuttle APU. Volume 1: APU design (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The H2-O2 space shuttle auxiliary power unit (APU) program is a NASA-Lewis effort aimed at hardware demonstration of the technology required for potential use on the space shuttle. It has been shown that a hydrogen-oxygen power unit (APU) system is an attractive alternate to the space shuttle baseline hydrazine APU system for minimum weight. It has the capability for meeting many of the heat sink requirements for the space shuttle vehicle, thereby reducing the amount of expendable evaporants required for cooling in the baseline APU. Volume 1 of this report covers preliminary design and analysis of the current reference system and detail design of the test version of this reference system. Combustor test results are also included. Volume 2 contains the results of the analysis of an initial version of the reference system and the computer printouts of system performance. The APU consists of subsystems for propellant feed and conditioning, turbopower, and control. Propellant feed and conditioning contains all heat exchangers, valves, and the combustor. The turbopower subsystem contains a two-stage partial-admission pressure-modulated, 400-hp, 63,000-rpm turbine, a 0-to 4-g lubrication system, and a gearbox with output pads for two hydraulic pumps and an alternator (alternator not included on test unit). The electronic control functions include regulation of speed and system temperatures; and start-and-stop sequences, overspeed (rpm) and temperature limits, failsafe provisions, and automatic shutdown provisions.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-121214 , AIRESEARCH-74-9874-PT-1
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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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  • 34
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    Design of H2-O2 space shuttle APU. Volume 2: Appendixes (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N74-15737.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-134485 , AIRESEARCH-74-9874-PT-2
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  • 35
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    Automatic spacecraft detumbling by internal mass motion (1974)
    In:  Other Sources
    Details
    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
    Format: text
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  • 36
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    A movable-mass attitude stabilization system for cable-connected artificial-g space stations (1974)
    In:  Other Sources
    Details
    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
    Format: text
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  • 37
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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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  • 38
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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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  • 39
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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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  • 40
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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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  • 41
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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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  • 42
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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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  • 43
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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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  • 44
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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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  • 45
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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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  • 46
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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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  • 47
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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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  • 48
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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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  • 49
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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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  • 50
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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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  • 51
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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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  • 52
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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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  • 53
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    Evaluation program for secondary spacecraft cells. Initial evaluation tests of General Electric Company standard and teflonated negative electrode 20.0 ampere-hour, nickel-cadmium spacecraft cells with auxiliary electrodes (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The standard plate cells exhibited higher average end-of-charge (EOC) voltages than the cells with teflonated negative plates; they also delivered a higher capacity output in ampere hours following these charges. All the cells reached a pressure of 20 psia before reaching the voltage limit of 1.550 volts during the pressure versus capacity test. The average ampere hours in and voltages at this pressure were 33.6 and 1.505 volts respectively for the teflonated negative plate cells and 35.5 and 1.523 volts for the standard plate cells. All cells exhibited pressure decay in the range of 1 to 7 psia during the last 30 minutes of the 1-hour open circuit stand. Average capacity out for the teflonated and standard negative plate cells was 29.4 and 29.9 ampere hours respectively.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-139654 , WQEC/C-74-337
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  • 54
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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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  • 55
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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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  • 56
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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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  • 57
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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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  • 58
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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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  • 59
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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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  • 60
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    Performance of finned thermal capacitors (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The performance of typical thermal capacitors, both in earth and orbital environments, was investigated. Techniques which were used to make predictions of thermal behavior in a one-g earth environment are outlined. Orbital performance parameters are qualitatively discussed, and those effects expected to be important under zero-g conditions are outlined. A summary of thermal capacitor applications are documentated, along with significant problem areas and current configurations. An experimental program was conducted to determine typical one-g performance, and the physical significance of these data is discussed in detail. Numerical techniques were employed to allow comparison between analytical and experimental data.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TN-D-7690
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  • 61
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    Transport dynamics of a high-power-density matrix-type hydrogen-oxygen fuel cell (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental transport dynamics tests were made on a space power fuel cell of current design. Various operating transients were introduced and transport-related response data were recorded with fluidic humidity sensing instruments. Also, sampled data techniques were developed for measuring the cathode-side electrolyte concentration during transient operation.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TN-D-7757 , E-7876
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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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  • 63
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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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  • 64
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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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  • 65
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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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  • 66
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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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  • 67
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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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  • 68
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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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  • 69
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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
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  • 70
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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
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  • 71
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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
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  • 72
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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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  • 73
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    Multi-kw dc power distribution system study program (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The first phase of the Multi-kw dc Power Distribution Technology Program is reported and involves the test and evaluation of a technology breadboard in a specifically designed test facility according to design concepts developed in a previous study on space vehicle electrical power processing, distribution, and control. The static and dynamic performance, fault isolation, reliability, electromagnetic interference characterisitics, and operability factors of high distribution systems were studied in order to gain a technology base for the use of high voltage dc systems in future aerospace vehicles. Detailed technical descriptions are presented and include data for the following: (1) dynamic interactions due to operation of solid state and electromechanical switchgear; (2) multiplexed and computer controlled supervision and checkout methods; (3) pulse width modulator design; and (4) cable design factors.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-120241
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  • 74
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    Nutation control during precession of a spin-stabilized spacecraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Precession maneuver control laws for single-spin spacecraft are investigated so that nutation is concurrently controlled. Analysis has led to the development of two types of control laws employing precession modulation for concurrent nutation control. Results were verified through digital simulation of a Synchronous Meteorological Satellite (SMS) configuration. An addition research effort was undertaken to investigate the cause and elimination of nutation anomalies in dual-spin spacecraft. A literature search was conducted and a dual-spin configuration was simulated to verify that nutational anomalies are not predicted by the existing nonlinear model. No conclusions were drawn as to the cause of the observed nutational anomalies in dual-spin spacecraft.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-138801 , CRL-74-4
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  • 75
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    MSFC Skylab Orbital Workshop, volume 5 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The various programs involved in the development of the Skylab Orbital Workshop are discussed. The subjects considered include the following: (1) reliability program, (2) system safety program, (3) testing program, (4) engineering program management, (5) mission operations support, and (6) aerospace applications.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64813-VOL-5
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  • 76
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    MSFC Skylab Orbital Workshop, volume 4 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design and development of specific systems on the Skylab Orbital Laboratory are discussed. The subjects considered are: (1) pressure garment conditioning system, (2) stowage system, (3) ground support equipment systems, and (4) marking systems illustrations of the system components are provided. Results of performance tests are discussed.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64813-VOL-4
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  • 77
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    MSFC Skylab Orbital Workshop, volume 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The technical aspects of the Skylab-Orbital Workshop are discussed. Original concepts, goals, design philosophy, hardware, and testing are reported. The final flight configuration, overall test program, and mission performance are analyzed. The systems which are examined are: (1) the structural system, (2) the meteoroid shield systems, and (3) the environmental/thermal control subsystem.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64813-VOL-1 , NASA-CR-120279
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  • 78
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    Space shuttle transportation system techniques for user/use development (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The problem of obtaining new uses for the Shuttle Transportation System (STS) was treated in the same way marketing problems are handled by industrial organizations. Techniques used by industry to obtain new ideas and customers were evaluated and analyzed for their relevance to the STS. Marketing barrier-data were used to develop strategy which called for a middleman organization to assist NASA in achieving its objectives. The importance of prompt initiation of the recommended strategy was established.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120259
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  • 79
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    Phase change paint tests on Rockwell orbiter/tank and orbiter alone configurations (OH3A/OH3B) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel tests were conducted on scale models of the space shuttle orbiter and external tank. The tests were designed to determine the basic heating rate and interference effects on the orbiter-tank configuration and to analyze the effectiveness of the thermal protective system on the reentry vehicle. The phase change paint techniques were used to determine areodynamic heating rates. Oil flow and schlieren photographs were used for flow visualization.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134075 , DMS-DR-2100
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  • 80
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    MSFC Skylab Orbital Workshop, volume 2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design and development of the Skylab Orbital Workshop are discussed. The subjects considered are: (1) thrust attitude control system, (2) solar array system, (3) electrical power distribution system, (4) communication and data acquisition system, (5) illumination system, and (6) caution and warning system.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64813-VOL-2
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  • 81
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    Development and correlation: Viking Orbiter analytical dynamic model with modal test (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Viking Orbiter (VO) experience in the achievement of a mathematical model is described along with the following project activities: (1) the generation of the overall plan for load analysis, an analytical dynamic model, and development tests; (2) the performance of VO subsystem static and modal tests; and (3) the correlation of the VO system model analysis and test. Success is attributed to the coordination of analysis and test using substructure modal coupling techniques.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-138728 , JPL-TM-33-690
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  • 82
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    MSFC Skylab Orbital Workshop, volume 3 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The waste management system for the Skylab Orbital Workshop is discussed. The general requirements of the system are presented. Illustrations of the components of the system are provided. Data concerning maximum expected performance capabilities are developed. The results of performance tests on the system components are reported. Emphasis is placed on the human factors engineering aspects of the system.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-64813-VOL-3
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  • 83
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    Assessment and control of electrostatic charges (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The experience is described of NASA and DOD with electrostatic problems, generation mechanisms, and type of electrostatic hazards. Guidelines for judging possible effects of electrostatic charges on space missions are presented along with mathematical formulas and definitions.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-SP-8111
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  • 84
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    Structure and function of an inorganic-organic separator for electrochemical cells: Preliminary study (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The structure of a new separator material for electrochemical cells has been investigated. Investigation into details of the separator structure showed it to be multilayered and to consist mainly of a quasi-impervious organic skin, a porous region of mixed organic and inorganic material, and an area of nonuniformly treated substrate. The essential feature of the coating (slurry) is believed to be interconnected pores which allow ionic conductivity. The interconnected pores are believed to be formed by the interaction of the plasticizer and inorganic fibers. The major failure mode of silver zinc cells using such a separator (zinc nodules shorting adjacent plates) was investigated.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TM-X-3080 , E-7871
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  • 85
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    General survey of solid-waste management (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Potential ways of providing solid-waste management for a building complex serviced by a modular integrated utility system (MIUS) were explored. Literature surveys were conducted to investigate both conventional and unusual systems to serve this purpose. The advantages and disadvantages of the systems most compatible with MIUS are discussed.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TM-X-58133 , JSC-08696
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  • 86
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    Performance of a Brayton power system with a space type radiator (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Test results of an experimental investigation to measure Brayton engine performance while operating at the sink temperatures of a typical low earth orbit are presented. The results indicate that the radiator area was slightly oversized. The steady state and transient responses of the power system to the sink temperatures in orbit were measured. During the orbital operation, the engine did not reach the steady state operation of either sun or shade conditions. The alternator power variation during orbit was + or - 4 percent from its mean value of 9.3 kilowatts.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TN-D-7708 , E-7799
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  • 87
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    VAMP: A computer program for calculating volume, area, and mass properties of aerospace vehicles (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computerized procedure developed for analyzing aerospace vehicles evaluates the properties of elemental surface areas with specified thickness by accumulating and combining them with arbitrarily specified mass elements to form a complete evaluation. Picture-like images of the geometric description are capable of being generated.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-2419 , LTN-10
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  • 88
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    SS/RCS surface tension propellant acquisition/expulsion tankage technology program (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An evaluation of published propellant physical property data together with bubble point tests of fine-mesh screen in propellants, was conducted. The effort consisted of: (1) the collection and evaluation of pertinent physical property data for hydrazine (N2H4), monomethylhydrazine (MMH), and nitrogen tetroxide (N2O4); (2) testing to determine the effect of dissolved pressurant gas, temperature, purity, and system cleanliness or contamination on system bubble point, and (3) the compilation and publishing of both the literature and test results. The space shuttle reaction control system (SS/RCS) is a bipropellant system using N2O4 and MMH, while the auxiliary power system (SS/APU) employs monopropellant N2H4. Since both the RCS and the APU use a surface tension device for propellant acquisition, the propellant properties of interest are those which impact the design and operation of surface tension systems. Information on propellant density, viscosity, surface tension, and contact angle was collected, compiled, and evaluated.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-140299 , MCR-74-278
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  • 89
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    WAATS: A computer program for Weights Analysis of Advanced Transportation Systems (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A historical weight estimating technique for advanced transportation systems is presented. The classical approach to weight estimation is discussed and sufficient data is presented to estimate weights for a large spectrum of flight vehicles including horizontal and vertical takeoff aircraft, boosters and reentry vehicles. A computer program, WAATS (Weights Analysis for Advanced Transportation Systems) embracing the techniques discussed has been written and user instructions are presented. The program was developed for use in the ODIN (Optimal Design Integration System) system.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-2420 , LTN-01R2
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  • 90
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    Development of modified vibration test criteria for qualifying space vehicle components (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simplified methods are described to estimate the test criteria of primary structures at component attachment points subjected to broadband random acoustic excitations. The current method utilizes a constant smeared component mass attenuation factor across the frequency range of interest. The developed method indicates that the attenuation factor is based on a frequency dependent ratio of the mechanical impedances of both the component and primary structures. The procedures used to predict the structural responses are considered as the present state-of-the-art and provide satisfactory prediction results. Example problems are used to illustrate the application procedures of the two methods and to compare the significant difference. It was found that the lower test criteria obtained by the impedance ratio method is due to the results of considering the effects of component/primary structure interaction.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120498 , WR-74-6
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  • 91
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    Mathematical crew motion disturbance models for spacecraft control system design (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Several techniques for modeling the disturbances to a spacecraft's attitude caused by moving crew members are presented. These disturbances can be the largest moments acting on a manned spacecraft, and knowledge of their effect is important in the sizing, design, and analysis/simulation of spacecraft attitude control systems. The modeling techniques are identified as two principal types: deterministic and stochastic. Three techniques of each type are presented. The deterministic models include point-mass motion derivatives and a discussion on dynamic models of moving crew members. The stochastic techniques are highlighted by a Fourier transform method and the representation of long-term crew disturbance activities as outputs from appropriately designed filters. A z-transform technique is developed to obtain a difference-equation form of stochastic models for use on digital computers. An appendix derives spacecraft equations of motion which can be used with many of the models discussed.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-70342
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  • 92
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    Description of the meteoroid detection experiment flown on the Pioneer 10 and 11 Jupiter flyby missions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The meteoroid detection experiment has the objective of measuring the population of 10 to the minus 9th power and 10 to the minus 8th power grams mass particles in interplanetary space with emphasis on making these measurements in the Asteroid Belt. The instrument design, which uses the pressurized-cell-penetration detection technique, and the tests involved in obtaining a flight-qualified instrument are described. The successful demonstration of flight-quality penetration detectors to function properly under long-term simulated space environments is also described.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7691 , L-9517
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  • 93
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    Thermal stress analysis of reusable surface insulation for shuttle (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An iterative procedure for accurately determining tile stresses associated with static mechanical and thermally induced internal loads is presented. The necessary conditions for convergence of the method are derived. An user-oriented computer program based upon the present method of analysis was developed. The program is capable of analyzing multi-tiled panels and determining the associated stresses. Typical numerical results from this computer program are presented.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-132502
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 94
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    Results of transonic/supersonic static stability wind tunnel tests of an 0.004-scale space shuttle orbiter model (0A49) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations of the configuration 4 space shuttle orbiter were conducted in the 14-inch trisonic wind tunnel during November and December 1973. Elevon, aileron, bodyflap, speedbrake, rudder effectiveness, and effects of ventral fins were investigated at angles of attack from -10 deg to 40 deg, angles of sideslip from -10 deg to +10 deg, and Mach numbers from 0.6 to 4.96. Resulting six-component static stability data and associated test information are presented.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134404 , DMS-DR-2095
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 95
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    Results of tests of a 0.010- and 0.015-scale models of space shuttle orbiter configurations 3 and 3A in the Ames Research Center 3.5 foot hypersonic wind tunnel (OA23) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Longitudinal and lateral-directional stability and control characteristics were evaluated at Mach numbers of 5.3, 7.3 and 10.3 at angles of attack up to 50 degrees with Beta = 0 degrees and, for a few cases, Beta = 5 degrees. Component force data, fuselage base pressures and shadowgraph patterns were recorded.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128799 , DMS-DR-2071
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 96
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    In-line task 57: Component evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design analysis tests were performed on selected power switching components to determine the possible applicability of off-the-shelf hardware to space shuttles. Various characteristics were also evaluated in those devices to determine the most desirable properties for the space shuttle.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-70363 , REPT-74-EG-13 , JSC-08941
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 97
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    Study of oxygen gas production phenomenon during stand and discharge in silver-zinc batteries (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Standard production procedures for manufacturing silver zinc batteries are evaluated and modified to reduce oxygen generation during open circuit stand and discharge. Production predictions of several variable combinations using analysis models are listed for minimum gassing, with emphasis on the concentration of potassium hydroxide in plate formation. A recommendation for work optimizing the variables involved in plate processing is included.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-140306
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 98
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    Energy and economic analysis of total energy systems for residential and commercial buildings (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Energy and economic analyses were performed for an on-site power-plant with waste heat recovery. The results show that for any specific application there is a characteristic power conversion efficiency that minimizes fuel consumption, and that efficiencies greater than this do not significantly improve fuel consumption. This type of powerplant appears to be a reasonably attractive investment if higher fuel costs continue.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TM-X-71617 , E-8099
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 99
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    Unknown
    Solar energy to heat and cool a new NASA Langley office building (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A solar heating and cooling system will be installed at a new NASA office building. The objective of this project is to establish a full-scale working test-bed facility to investigate solar energy for heating and cooling buildings. The energy collected will provide between 80 and 100 percent of the heating and cooling requirements during the cool months and between one-half and two-thirds of the cooling requirements in the summer. Thermal energy storage will be provided to bridge the gap between cloudy and clear days.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TM-X-71615 , E-8103
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 100
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    Long life, rechargeable nickel-zinc battery (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A production version of the inorganic separator was evaluated for improving the life of the nickel-zinc system. Nickel-zinc cells (7-10 Ah capacities) of different electrode separator configurations were constructed and tested. The nickel-zinc cells using the inorganic separator encasing the zinc electrode, the nickel electrode, or both electrodes had shorter lives than cells using Visking and cellophane separation. Cells with the inorganic separation all fell below 70% of their theoretical capacity within 30 cycles, but the cells constructed with organic separation required 80 cycles. Failure of the cells using the ceramic separator was irreversible capacity degradation due to zinc loss through cracks developed in the inorganic separator. Zinc loss through the separator was minimized with the use of combinations of the inorganic separator with Visking and cellophane. Cells using the combined separation operated 130 duty cycles before degrading to 70% of their theoretical capacity.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-134658 , GOULD-742-031
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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