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  • Other Sources  (2,610)
  • PROPULSION SYSTEMS  (1,456)
  • GENERAL  (1,154)
  • 1970-1974  (2,610)
Collection
  • Other Sources  (2,610)
Source
Keywords
Years
Year
  • 1
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    Who owns the moon? (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: It is stipulated that all of mankind owns the moon and that lunar exploration must be exclusively for peaceful purposes. In addition to the right to build stations on the moon, every country has the right to utilize the moon's natural resources. This includes: exploration, extraction, and processing of minerals and other natural resources, and their utilization and processing for local needs and possible also for export to earth.
    Keywords: GENERAL
    Type: Inhabited Space, Pt. 2 (NASA-TT-F-820); p 177-184
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  • 2
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    Reduction of diesel engine exhaust noise in the petroleum mining industry (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: An important noise source in a drilling plant is Diesel engine exhaust. In order to reduce this noise, a reactive silencer of the derivative resonator type was proposed, calculated from the acoustic and design point of view and applied. As a result of applying such a silencer on the exhaust conduit of a Diesel engine the noise level dropped down to 18 db.
    Keywords: PROPULSION SYSTEMS
    Type: The 4th Natl. Conf. on Acoustics, Vol. 1A (NASA-TT-F-15375); p 156-162
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  • 3
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    Electric propulsion - Now (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The state of the art of electric propulsion technology is discussed with a review of the many difficult engineering problems which must be resolved before the incorporation of electric propulsion in space missions. Interferences with the spacecraft and its scientific instrumentation, conducted and radiated electromagnetic interferences during the switching and processing of large electrical loads, and mercury and other eroded materials deposition on the spacecraft are indicated among the engineering and design challenges to be overcome and resolved.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Student Journal; 12; Apr. 197
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  • 4
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    Quiet engine from NASA (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Engine designs resulting from the NASA sponsored quiet engine program are described in terms of their possible use on the DC-8. These engines have high bypass ratios for low jet noise and low-speed, low-noise fans. Experiments were carried out on various fan designs with different tip speeds. The advantage of low tip speeds and high lift coefficients has been demonstrated. The engines are equipped with flight-standard nacelles with acoustic suppression. It is estimated that these improvements will reduce DC-8 noise by about 26EPNdB-29EPNdB.
    Keywords: PROPULSION SYSTEMS
    Type: Flight International; 106; July 25
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  • 5
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    Mariner Venus/Mercury '73 - A strategy of cost control (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Mariner Venus/Mercury '73 project kept within its originally established goals for schedule, performance, and cost. Underlying this development success was the availability of the Mariner technology. But meeting the goals demanded management determination, planning, and discipline to make optimum use of state-of-the-art technology. The present work points out management approaches and techniques that kept schedules and controlled costs, the intent being to stimulate thought about how to do the same with future spacecraft and payloads.
    Keywords: GENERAL
    Type: Astronautics and Aeronautics; 12; June 197
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  • 6
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    Putting all our noise technology to work (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An assessment of the present state of the art in noise reduction technology indicates that this technology has the potential for effectively attaining this goal - a conclusion that is in apparent conflict with the frequently voiced complaints on intolerable noise levels near airports. Measures are suggested for a more vigorous implementation of available technology in practice to combat the aircraft noise problem.
    Keywords: PROPULSION SYSTEMS
    Type: Astronautics and Aeronautics; 12; Jan. 197
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  • 7
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    Specialist conference: Propellant pressing (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: APL Bull. of the 20th Interagency Solid Propulsion Meeting, Vol. 4; p 427-437
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  • 8
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    Multitopic load chart for the design office subdivison (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The methods of development, designation and application of the charts under multitopic conditions are considered.
    Keywords: GENERAL
    Type: Technol. for the Production of Space Equipment (NASA-TT-F-15766); p 15-20
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  • 9
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    Organization of operations with respect to checking drawings (drawing checking procedure) (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: One of the basic conditions of high quality manufacture of instruments is the error free developed design documentation. A procedure is described for organizing the design check of the drawings.
    Keywords: GENERAL
    Type: Technol. for the Production of Space Equipment (NASA-TT-F-15766); p 21-24
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  • 10
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    PERT simulation of experimental design work (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The basic principles of constructing the models and rules for their application in the development of PERT charts are discussed.
    Keywords: GENERAL
    Type: Technol. for the Production of Space Equipment (NASA-TT-F-15766); p 11-14
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  • 11
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    Characteristic features of determining the labor input and estimated cost of the development and manufacture of equipment (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The difficulties in obtaining exact calculation data for the labor input and estimated cost are noted. The method of calculating the labor cost of the design work using the provisional normative indexes with respect to individual forms of operations is proposed. Values of certain coefficients recommended for use in the practical calculations of the labor input for the development of new scientific equipment for space research are presented.
    Keywords: GENERAL
    Type: Technol. for the Production of Space Equipment (NASA-TT-F-15766); p 3-10
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  • 12
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    Government-Industry Data Exchange Program (GIDEP) (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Government-Industry Data Exchange Program (GIDEP) was originated in 1959 by the Army, Navy, and Air Force Ballistic Missile Agencies. Known at that time as IDEP--Interservice Data Exchange Program--its intent was to eliminate duplicate testing of parts and components by disseminating pertinent test data among Department of Defense contractors and various government agencies. In 1966 both the National Aeronautics and Space Administration and the Canadian Military Electronics Standards Agency (CAMESA) recognized the value of the data provided by the program and became participants. Today, GIDEP provides the interchange of specialized technical data to all the military services, participating government contractors and numerous government agencies such as the Atomic Energy Commission, Federal Aviation Administration, Defense Supply Agency, and the Small Business Administration.
    Keywords: GENERAL
    Type: NBS The Role of Cavitation in Mech. Failures; p 166-170
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  • 13
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    Erosion and the gas turbine engine, part 2 (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Procedures for protecting aircraft engines from impact damage due to sand and dust particles are discussed. One system is to develop a filtration system to remove most of the solid particles. Another method is to design blade materials and blade protection coatings. The concepts of erosion within aircraft engines are explained. Curves are presented to show the effect of impingement angle on ductile and elastic modes of erosion. Engine sand and dust ingestion tests were conducted on T63-A-5A engines and the results are produced in graph form. The results of tests conducted in a dynamic erosion facility are analyzed.
    Keywords: PROPULSION SYSTEMS
    Type: NBS The Role of Cavitation in Mech. Failures; p 129-145
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  • 14
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    Application of describing functions for evaluation of space shuttle landing aid display concepts (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: AF Inst. of Technol. Proc. of the 10th Ann. Conf. on Manual Control; p 677-703
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  • 15
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    Future terminal air traffic management concepts (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: AF Inst. of Technol. Proc. of the 10th Ann. Conf. on Manual Control; p 477-501
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  • 16
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    Simulator evaluation of three situation and guidance displays for V/STOL zero-zero landings (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: AF Inst. of Technol. Proc. of the 10th Ann. Conf. on Manual Control; p 439-465
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  • 17
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    Decision behavior with changing signal strength (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: AF Inst. of Technol. Proc. of the 10th Ann. Conf. on Manual Control; p 1-38
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  • 18
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    An evaluation of a predictor used with two different aircraft map display orientations (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: AF Inst. of Technol. Proc. of the 10th Ann. Conf. on Manual Control; p 397-426
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  • 19
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    Digitally controlled transient waveform testing: Alternative method to slow sine sweep (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull. No. 44, Part 3; p 1-5
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  • 20
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    Determining an optimal set of research experiments (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Description of a procedure for optimal selection of research experiments to be performed aboard the Space Shuttle. The procedure is designed to provide the study team with a credible approach to their task. The procedure is characterized as methodologically sound and based on assumptions which reasonably approximate the real conditions. The data-gathering techniques proposed are accepted by scientifically trained personnel.
    Keywords: GENERAL
    Type: IEEE Transactions on Engineering Management; EM-21; Feb. 197
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  • 21
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    Influence of noise requirements on STOL propulsion system designs (1974)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: The severity of proposed noise goals for STOL systems has resulted in a new design approach for aircraft propulsion systems. It has become necessary to consider the influence of the noise goal on the design of engine components, engine systems, and the integrated nacelle, separately and collectively, from the onset of the design effort. This integrated system design approach is required in order to effect an optimization of the propulsion and aircraft system. Results from extensive design studies and pertinent test programs are presented which show the effect of noise specifications on component and system design, and the trade-offs possible of noise versus configuration and performance. The design optimization process of propulsion systems for powered lift systems is presented beginning with the component level and proceeding through to the final integrated propulsion system. Designs are presented which are capable of meeting future STOL noise regulations and the performance, installation and economic penalties are assessed as a function of noise level.
    Keywords: PROPULSION SYSTEMS
    Type: AGARD V(STOL Propulsion Systems; 17 p
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  • 22
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    Teleoperator equations of motion (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Keywords: GENERAL
    Type: NASA-CR-150043 , SR-S-30
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  • 23
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    Flight velocity effects on jet noise of several variations of a twelve-chute suppressor installed on a plug nozzle (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Because of the relatively high takeoff speeds of supersonic transport aircraft, it is important to know whether the flight velocity effects the noise level of suppressor nozzles. To investigate this, a modified F-106B aircraft was used to conduct a series of flyover and static tests on a 12-chute suppressor installed on an uncooled plug nozzle. Comparison of flyover and static spectra indicated that flight velocity adversely affected noise suppressions of the 12-chute configurations.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2918 , E-7449
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  • 24
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    FORTRAN program to generate engine inlet flow contour maps and distortion parameters (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program is presented and described that generates jet engine inlet flow contour maps and inlet flow distortion parameters. The program input consists of an array of measurements describing the flow conditions at the engine inlet. User-defined distortion parameters may be calculated.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2967 , E-7572
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  • 25
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    Thrust performance of isolated plug nozzles with two types of 40-spoke noise suppressor at Mach numbers from 0 to 0.45 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Plug nozzles with two types of 40-spoke noise suppressor were tested at free-stream Mach numbers from 0 to 0.45 and over a range of nozzle pressure ratios from 1.5 to 4.0. In additon, an unsuppressed plug nozzle and a Supersonic Tunnel Association nozzle were also tested to provide baseline levels of thrust performance. The unsuppressed plug nozzle had an efficiency of 98 percent at an assumed takeoff pressure ratio of 3.0 and at Mach 0.36. At the same condition the suppressor nozzles had efficiencies of approximately 83.5 percent.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2951 , E-7541
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  • 26
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    Flight velocity effects on jet noise of several variations of a 48-tube suppressor installed on a plug nozzle (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Because of the relatively high takeoff speeds of supersonic transport aircraft, it is important to know if the flight velocity affects the noise level of suppressor nozzles. To investigate this, a modified F-106B aircraft was used to conduct a series of flyover and static tests on a 48-tube suppressor installed on an uncooled plug nozzle. Comparison of flyover and static spectra indicated that flight velocity had little effect on the noise suppression of the 48-tube suppressor configuration. However, flight velocity adversely affected noise suppression of the 48-tube suppressor with an acoustic shroud and plug installed.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2919 , E-7513
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  • 27
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    SERT C project study (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The SERT C (Space Electric Rocket Test - C) project study defines a spacecraft mission that would demonstrate the technology readiness of ion thruster systems for primary propulsion and station keeping applications. As a low cost precursor, SERT C develops the components and systems required for subsequent Solar Electric Propulsion (SEP) applications. The SERT C mission requirements and preliminary spacecraft and subsystem design are described.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71508
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  • 28
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    Modification of one man life raft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A one man inflatable life raft is described. The raft has an inflatable tube perimetrically bounding the occupant receiving space with a flexible floor member. A zippered opening in the floor allows entry and facilitates the use of a constant diameter tube. An airtight fabric bulkhead divides the peripheral tube longitudinally into inflatable tube sections, where if either tube section were punctured, the bulkhead would move into the punctured section to substitute for the punctured wall portion and maintain the inflatable volume of the tube. The floor member is attached to the central portion of the tube wall so that either side of the raft can be the up side.
    Keywords: GENERAL
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  • 29
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    Method of making rolling element bearings (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method is described of making rolling elements by forming low mass cores having either hollow centers or being of a low mass material. The low mass cores are plated and heat treated to provide hard surfaces on the rolling elements. After grinding to the proper diameter the rolling elements are assembled between races to form a hearing.
    Keywords: GENERAL
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  • 30
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    Temperature compensated digital inertial sensor (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A circuit which maintains the inertial element of a gyroscope or accelerometer at a constant position by delivering pulses to a rebalancing motor is discussed. The circuit compensates for temperature changes by using a temperature sensor that varies the threshold of inertial element movement required to generate a rebalance pulse which reacts to changes in viscosity of the flotation fluid. The output of the temperature sensor also varies the output level of the current source to compensate for changes in the strength of the magnets of the rebalancing motor. The sensor also provides a small signal to the rebalance motor to provide a temperature dependent compensation for fixed drift or fixed bias.
    Keywords: GENERAL
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  • 31
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    A guide for performing system safety analysis (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A general guide is presented for performing system safety analyses of hardware, software, operations and human elements of an aerospace program. The guide describes a progression of activities that can be effectively applied to identify hazards to personnel and equipment during all periods of system development. The general process of performing safety analyses is described; setting forth in a logical order the information and data requirements, the analytical steps, and the results. These analyses are the technical basis of a system safety program. Although the guidance established by this document cannot replace human experience and judgement, it does provide a methodical approach to the identification of hazards and evaluation of risks to the system.
    Keywords: GENERAL
    Type: NASA-TM-X-64799
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  • 32
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    Adaptive voting computer system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer system is reported that uses adaptive voting to tolerate failures and operates in a fail-operational, fail-safe manner. Each of four computers is individually connected to one of four external input/output (I/O) busses which interface with external subsystems. Each computer is connected to receive input data and commands from the other three computers and to furnish output data commands to the other three computers. An adaptive control apparatus including a voter-comparator-switch (VCS) is provided for each computer to receive signals from each of the computers and permits adaptive voting among the computers to permit the fail-operational, fail-safe operation.
    Keywords: GENERAL
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  • 33
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    Two-dimensional cold-air cascade study of a film-cooled turbine stator blade. 1: Experimental results of pressure-surface film cooling tests (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of film coolant ejection from the pressure side of a stator blade was determined in a two-dimensional cascade. Stator exit surveys were made for each of six rows of coolant holes. Successive multirow tests were made with two, three, four, five, and six rows of coolant holes open. The results of the multirow tests are compared with the predicted multirow performance obtained by adding the single-row data. Results are presented in terms of stator primary-air efficiency as a function of coolant fraction.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3045 , E-7817
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  • 34
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    An overview of the National Space Science data Center Standard Information Retrieval System (SIRS) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A general overview is given of the National Space Science Data Center (NSSDC) Standard Information Retrieval System. A description, in general terms, the information system that contains the data files and the software system that processes and manipulates the files maintained at the Data Center. Emphasis is placed on providing users with an overview of the capabilities and uses of the NSSDC Standard Information Retrieval System (SIRS). Examples given are taken from the files at the Data Center. Detailed information about NSSDC data files is documented in a set of File Users Guides, with one user's guide prepared for each file processed by SIRS. Detailed information about SIRS is presented in the SIRS Users Guide.
    Keywords: GENERAL
    Type: NASA-TM-X-69903 , NSSDC-74-09
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  • 35
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    Comparative evaluation of solar, fission, fusion, and fossil energy resources, part 3 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The role of nuclear fission reactors in becoming an important power source in the world is discussed. The supply of fissile nuclear fuel will be severely depleted by the year 2000. With breeder reactors the world supply of uranium could last thousands of years. However, breeder reactors have problems of a large radioactive inventory and an accident potential which could present an unacceptable hazard. Although breeder reactors afford a possible solution to the energy shortage, their ultimate role will depend on demonstrated safety and acceptable risks and environmental effects. Fusion power would also be a long range, essentially permanent, solution to the world's energy problem. Fusion appears to compare favorably with breeders in safety and environmental effects. Research comparing a controlled fusion reactor with the breeder reactor in solving our long range energy needs is discussed.
    Keywords: GENERAL
    Type: NASA-CR-138117
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  • 36
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    Publications of the Jet Propulsion Laboratory, January - December 1973 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Five classes of publications are included in this bibliography: (1) Technical Reports in which the information is complete for a specific accomplishment and is intended for a wide audience. (2) Articles from the bimonthly Deep Space Network Progress Report. Each volume's collection of articles presents a periodical survey of current accomplishments by the Deep Space Network. (3) Technical Memorandums, in which the information is complete for a specific accomplishment but is intended for a limited audience to satisfy unique requirements. (4) Articles from the JPL Quarterly Technical Review. Each article summarizes a recent important development, interim or final results, or an advancement in the state of the art in a scientific or engineering endeavor, This publication has been discontinued, and the issues indexed in this bibliography are the last to be published. (5) Articles published in the open literature. The publications are indexed by: (1) author, (2) subject, and (3) publication type and number. A descriptive entry appears under the name of each author of each publication; an abstract is included with the entry for the primary (first-listed) author.
    Keywords: GENERAL
    Type: NASA-CR-138171 , JPL-BIBL-39-15
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  • 37
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    NSSDC and WDC-A-R and S document availability and distribution services (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The documents available from the National Space Science Data Center and the World Data Center A for Rockets and Satellites are described. The availability, costs, ordering procedures for documents presently available, and the procedures for obtaining future documents are given.
    Keywords: GENERAL
    Type: NASA-TM-X-69904 , NSSDC/WDC-A-R/S-74-10
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  • 38
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    Comparative evaluation of solar, fission, fusion, and fossil energy resources. Part 5: Conclusions and recomendations (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Air pollution resulting from the use of fossil fuels is discussed. Phenomena relating to the emission of CO2 such as the greenhouse effect and multiplier effect are explored. Particulate release is also discussed. The following recommendations are made for the elimination of fossil fuel combustion products in the United States: development of nuclear breeder reactors, use of solar energy systems, exploration of energy alternatives such as geothermal and fusion, and the substitution of coal for gas and oil use.
    Keywords: GENERAL
    Type: NASA-CR-138183
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  • 39
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    Comparative evaluation of solar, fission, fusion, and fossil energy resources. Part 4: Energy from fossil fuels (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The conversion of fossil-fired power plants now burning oil or gas to burn coal is discussed along with the relaxation of air quality standards and the development of coal gasification processes to insure a continued supply of gas from coal. The location of oil fields, refining areas, natural gas fields, and pipelines in the U.S. is shown. The technologies of modern fossil-fired boilers and gas turbines are defined along with the new technologies of fluid-bed boilers and MHD generators.
    Keywords: GENERAL
    Type: NASA-CR-138188
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  • 40
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    Skylab-2 handheld photography alphabetized geographical features list (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This publication represents a relisting of the Skylab-2, PTD Handheld Photography Catalog. The purpose of this publication is to provide imagery researchers a supplement to the PTD Catalog by alphabetically sorting together all similar major and minor features. Some cross-referencing of feature names was accomplished where the authors deemed necessary; however, no attempt was made to exhaust all possible means of cross-referencing. An example of the cross-referencing which was done: Kuril Islands may be found under the major feature column and also as a minor feature of Islands.
    Keywords: GENERAL
    Type: NASA-CR-134245 , LEC-2059
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  • 41
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    Basic performance of a multilayer insulation system containing 20 to 160 layers (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted to determine the thermal effectiveness of an aluminized Mylar-silk net insulation system containing up to 160 layers. The experimentally measured heat flux was compared with results predicted by using (1) a previously developed semi-empirical equation and (2) an effective-thermal-conductivity value. All tests were conducted at a nominal hot-boundary temperature of 294 K (530 R) with liquid hydrogen as the heat sink. The experimental results show that the insulation performed as expected and that both the semi-empirical equation and effective thermal conductivity of a small number of layers were adequate in predicting the thermal performance of a large number of layers of insulation.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-7659 , E-7815
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  • 42
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    Dispensing targets for ion beam particle generators (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A target for dispensing high energy protons or neutrons or ionized atoms or ionized molecules is provided which comprises a container for the target gas, which is at atmospheric or higher pressure. The container material can release the target gas in the spot where the container is heated above a predetermined temperature by the impact of an ion beam where protons or neutrons are desired, or by electrons where ionized atoms or molecules are desired. On the outside of the container, except for the region where the beam is to impact, there is deposited a layer of a metal which is imperious to gaseous diffusion. A further protective coating of a material is placed over the layer of metal, except at the region of the ion impact area in order to adsorb any unreacted gas in the vacuum in which the target is placed, to thereby prevent reduction of the high vacuum, as well as contamination of the interior of the vacuum chamber.
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  • 43
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    Method and apparatus for optically monitoring the angular position of a rotating mirror (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An optical system monitors the angular position of a rotating scanning mirror to indicate the effective start and end of each scan. At a certain angular position, a ray of energy transmitted to the mirror is reflected a plurality of times between the reflectors associated with the optical system and the line on the mirror parallel to the axis, and then to a detector to sense that angular position. A single optical system may be arranged to sense a plurality of different angular positions for each revolution of the mirror.
    Keywords: GENERAL
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  • 44
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    Trends in State and Federal land use law relating to inventories, monitoring and evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description and analysis of selected State and Federal laws relating to land use inventories, monitoring, and evaluation is presented. Legal requirements and information systems for land use in the following states are reviewed: Colorado, Delaware, Florida, Hawaii, Indiana, Kansas, Maine, Mississippi, Missouri, Oklahoma, Pennsylvania, Tennessee, Utah, Vermont, and West Virginia.
    Keywords: GENERAL
    Type: NASA-CR-137332
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  • 45
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    Airline return-on-investment model for technology evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This report presents the derivation, description, and operating instructions for a computer program (TEKVAL) which measures the economic value of advanced technology features applied to long range commercial passenger aircraft. The program consists of three modules; and airplane sizing routine, a direct operating cost routine, and an airline return-on-investment routine. These modules are linked such that they may be operated sequentially or individually, with one routine generating the input for the next or with the option of externally specifying the input for either of the economic routines. A very simple airplane sizing technique was previously developed, based on the Brequet range equation. For this program, that sizing technique has been greatly expanded and combined with the formerly separate DOC and ROI programs to produce TEKVAL.
    Keywords: GENERAL
    Type: NASA-CR-132382
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  • 46
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    High speed shutter (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A shutter element is described which is formed by a loop of an electrically conductive ribbon disposed adjacent to the end of a passageway to be shuttered. The shuttered end of the passageway is cut at an acute angle. The two leg portions of the ribbon loop are closely spaced to each other and disposed in a plane parallel to the axis of the passageway. A pulse of high current is switched through the loop to cause the current flowing in opposite directions through adjacent leg portions of the ribbon. This produces a magnetically induced pressure on one of the legs of the ribbon forcing the leg over the end of the passageway in gas tight sealing engagement, and thereby blocking passageway.
    Keywords: GENERAL
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  • 47
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    Heat transfer device (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A heat transfer device is characterized by an hermetically sealed tubular housing including a tubular shell terminating in spaced end plates, and a tubular mesh wick concentrically arranged and operatively supported within said housing. The invention provides an improved wicking restraint formed as an elongated and radially expanded tubular helix concentrically related to the wick and adapted to be axially foreshortened and radially expanded into engagement with the wick in response to an axially applied compressive load. The wick is continuously supported in a contiguous relationship with the internal surfaces of the shell.
    Keywords: GENERAL
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  • 48
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    Reinforced polyquinoxaline gasket and method of preparing the same (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A gasket or seal resistant to ionizing radiation and liquid hydrogen temperatures is made up of a laminated polyquinoxaline resin-fiberglass cloth body portion and a molded polyquinoxaline encapsulating film. The laminated body is prepared by stacking thin sheets of the resin alternately with fiberglass cloth and heating the assembly under pressure with the temperature, pressure and resin film thickness being controlled so that only partial impregnation of the fiberglass cloth is produced. The encapsulating resin film is preheated at about 300 f and applied to the laminate body by molding at a temperature of about 625 F. The molded gasket is then deflashed and post-cured by heating at 675 to 700 F.
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  • 49
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    High field CdS detector for infrared radiation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An infrared radiation detector including a cadmium sulfide platelet having a cathode formed on one of its ends and an anode formed on its other end is presented. The platelet is suitably doped such that stationary high-field domains are formed adjacent the cathode when based in the negative differential conductivity region. A negative potential is applied to the cathode such that a high-field domain is formed adjacent to the cathode. A potential measuring probe is located between the cathode and the anode at the edge of the high-field domain and means are provided for measuring the potential at the probe whereby this measurement is indicative of the infrared radiation striking the platelet.
    Keywords: GENERAL
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  • 50
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    Apparatus for remote handling of materials (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Apparatus for remote handling of materials are described. A closed housing is provided with first and second containers and first and second reservoirs for holding materials to be mixed. The materials are transferable from the reservoirs to the first container where they are mixed. The mixed materials are then conveyed from the first container to the second container preferably by dumping the mixed materials into a funnel positioned over the second container. The second container is then moved to a second position for analysis of the mixed materials. For example, the materials may be ignited and the flame analyzed. Access, such as a sight port, is provided in the housing at the analysis position. The device provides a simple and inexpensive apparatus for safely mixing a pyrophoric material and an oxidizer which together form a thermite type mixture that burns to produce a large quantity of heat and light.
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  • 51
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    Inverter ratio failure detector (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A failure detector which detects the failure of a dc to ac inverter is disclosed. The inverter under failureless conditions is characterized by a known linear relationship of its input and output voltages and by a known linear relationship of its input and output currents. The detector includes circuitry which is responsive to the detector's input and output voltages and which provides a failure-indicating signal only when the monitored output voltage is less by a selected factor, than the expected output voltage for the monitored input voltage, based on the known voltages' relationship. Similarly, the detector includes circuitry which is responsive to the input and output currents and provides a failure-indicating signal only when the input current exceeds by a selected factor the expected input current for the monitored output current based on the known currents' relationship.
    Keywords: GENERAL
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  • 52
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    A contemporary view of systems engineering (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The concept of a 'system' is defined, and the 'systems approach' is discussed. Four contemporary examples of the systems approach are presented: an operations research project, the planning-programming-budgeting system, an information processing system, and aerospace programs.
    Keywords: GENERAL
    Type: NASA-CR-136833 , JPL-TM-33-667
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  • 53
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    Multifunction audio digitizer (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An illustrative embodiment of the invention includes apparatus which simultaneously produces both direct delta modulation and pulse code modulation. An input signal, after amplification, is supplied to a window comparator which supplies a polarity control signal to gate the output of a clock to the appropriate input of a binary up-down counter. The control signals provide direct delta modulation while the up-down counter output provides pulse code modulation.
    Keywords: GENERAL
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  • 54
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    Diffusion welding in air (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Solid state welding a butt joint by fusion welding the peripheral surfaces to form a seal is described along with, autogenetically cleaning the faying or mating surfaces of the joint by heating the abutting surfaces to 1,200 C and heating to the diffusion welding temperature in air.
    Keywords: GENERAL
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  • 55
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    Solar array study for solar electric propulsion spacecraft for the Encke rendezvous mission (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The work is described which was performed on the design, analysis and performance of a 20 kW rollup solar array capable of meeting the design requirements of a solar electric spacecraft for the 1980 Encke rendezvous mission. To meet the high power requirements of the proposed electric propulsion mission, solar arrays on the order of 186.6 sq m were defined. Because of the large weights involved with arrays of this size, consideration of array configurations is limited to lightweight, large area concepts with maximum power-to-weight ratios. Items covered include solar array requirements and constraints, array concept selection and rationale, structural and electrical design considerations, and reliability considerations.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-136860 , JPL-TM-33-668
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  • 56
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    Performance of a hydrogen burner to simulate air entering scramjet combustors (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted to determine the performance of a hydrogen burner used to produce a test gas that simulates air entering a scramjet combustor at various flight conditions. The test gas simulates air in that it duplicates the total temperature, total pressure, and the volume fraction of oxygen of air at flight conditions. The main objective of the tests was to determine the performance of the burner as a function of the effective exhaust port area. The conclusions were: (1) pressure oscillations of the chugging type were reduced in amplitude to plus or minus 2 percent of the mean pressure level by proper sizing of hydrogen, oxygen, and air injector flow areas; (2) combustion efficiency remained essentially constant as the exhaust port area was increased by a factor of 3.4; (3) the mean total temperature determined from integrating the exit radial gas property profiles was within plus or minus 5 percent of the theoretical bulk total temperature; (4) the measured exit total temperature profile had a local peak temperature more than 30 percent greater than the theoretical bulk total temperature; and (5) measured heat transfer to the burner liner was 75 percent of that predicted by theory based on a flat radial temperature profile.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-7567 , L-9363
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  • 57
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    Experimental investigation of a 4 and 1/2 stage turbine with very high stage loading factor. 2: Turbine performance (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The experimental test program results of a 4 1/2-stage turbine with a very high stage loading factor are presented. A four-stage turbine was tested with and without outlet turning vanes. The 4 1/2-stage turbine achieved a design point total-to-total efficiency of 0.853. The outlet turning vane design point performance was 0.4 percent of the overall 4 1/2-stage turbine efficiency. Tests were conducted at various levels of Reynolds number and indicated decreases in turbine efficiency and equivalent weight flow with decreasing Reynolds number.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-2363 , R73AEG163
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  • 58
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    Single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors. Part 7: Data and performance for stage E (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An axial flow compressor stage, having tandem airfoil blading, was designed for zero rotor prewhirl, constant rotor work across the span, and axial discharge flow. The stage was designed to produce a pressure ratio of 1.265 at a rotor tip velocity of 757 ft/sec. The rotor has an inlet hub/tip ratio of 0.8. The design procedure accounted for the rotor inlet boundary layer and included the effects of axial velocity ratio and secondary flow on blade row performance. The objectives of this experimental program were (1) to obtain performance with uniform and distorted inlet flow for comparison with the performance of a stage consisting of single-airfoil blading designed for the same vector diagrams and (2) to evaluate the effectiveness of accounting for the inlet boundary layer, axial velocity ratio, and secondary flows in the stage design.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134529 , FR-5955
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  • 59
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    Exploratory tests of two strut fuel injectors for supersonic combustion (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of supersonic mixing and combustion tests performed with two simple strut injector configurations, one with parallel injectors and one with perpendicular injectors, are presented and analyzed. Good agreement is obtained between static pressure measured on the duct wall downstream of the strut injectors and distributions obtained from one-dimensional calculations. Measured duct heat load agrees with results of the one-dimensional calculations for moderate amounts of reaction, but is underestimated when large separated regions occur near the injection location. For the parallel injection strut, good agreement is obtained between the shape of the injected fuel distribution inferred from gas sample measurements at the duct exit and the distribution calculated with a multiple-jet mixing theory. The overall fraction of injected fuel reacted in the multiple-jet calculation closely matches the amount of fuel reaction necessary to match static pressure with the one-dimensional calculation. Gas sample measurements with the perpendicular injection strut also give results consistent with the amount of fuel reaction in the one-dimensional calculation.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-7581 , L-9428
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  • 60
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    Automatic real-time pair-feeding system for animals (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A pair feeding method and apparatus are provided for experimental animals wherein the amount of food consumed is immediately delivered to a normal or control animal so that there is a qualitative, quantitative and chronological correctness in the pair feeding of the two animals. This feeding mechanism delivers precisely measured amounts of food to a feeder. Circuitry is provided between master and slave feeders so that there is virtually no chance of a malfunction of the feeding apparatus, causing erratic results. Recording equipment is also provided so that an hourly record is kept of food delivery.
    Keywords: GENERAL
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  • 61
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    Dual measurement ablation sensor (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A dual measurement ablation sensor for measuring both char-interface and surface recession at a point in an ablating material is described. The sensor permits measurement of the thickness of the char layer. Char-interface recession is indicated by a drop in the resistance to a current passed through the ablation material. Surface recession is indicated by the closing of an electrical circuit when melting causes the release of a spring switch.
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  • 62
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    Jet engine exhaust noise due to rough combustion and nonsteady aerodynamic sources (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: PROPULSION SYSTEMS
    Type: Acoustical Society of America; vol. 56
    Format: text
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  • 63
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    Center for development technology and program in technology and human affairs (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The role of technology in nontraditional higher education with particular emphasis on technology-based networks is analyzed nontraditional programs, institutions, and consortia are briefly reviewed. Nontraditional programs which utilize technology are studied. Technology-based networks are surveyed and analyzed with regard to kinds of students, learning locations, technology utilization, interinstitutional relationships, cost aspects, problems, and future outlook.
    Keywords: GENERAL
    Type: NASA-CR-140016 , R(T)-74/3 , THA-74/5
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  • 64
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    Eight cm technology thruster development (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A structural integrated ion thruster with 8-cm beam diameter (SIT-8) was developed for attitude control and stationkeeping of synchronous satellites. As optimized, the system demonstrates a thrust T=1.14 mlb (not corrected for beam V sub B = 1200 V (I sub sp = 2200 sec) total propellant utilization efficiency nu sub u = 59.8% (is approximately 72% without auxiliary pulse-igniter electrode), and electrical efficiency n sub E 61.9%. The thruster incorporates a wire-mesh anode and tantalum cover surfaces to control discharge chamber flake formation and employs an auxiliary pulse-igniter electrode for hollow-cathode ignition. When the SIT-8 is integrated with the compatible SIT-5 propellant tankage, the system envelope is 35 cm long by 13 cm flange bolt circle with a mass of 9.8 kg including 6.8 kg of mercury propellant. Two thrust vectoring systems which generate beam deflections in two orthogonal directions were also developed under the program and tested with the 8-cm thruster. One system vectors the beam over + or - 10 degrees by gimbaling of the entire thruster (not including tankage), while the other system vectors the beam over + or - 7 degrees by translating the accel electrode relative to the screen electrode.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134685
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  • 65
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    Overall and blade-element performance of a 1.20-pressure-ratio fan stage at design blade setting angle (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 51-cm-diam. model of a short-haul fan stage was tested. Surveys of the air flow conditions ahead of the rotor, between the rotor and stator, and behind the stator were made over the stable operating range of the stage. At the design speed of 213.3 m/sec and weight flow of 26.7 kg/sec, the stage pressure ratio and efficiency are 1.18 and 0.87, respectively. The rotor peak efficiency of 0.92 occurred at flow rate of 30.5 kg/sec. Peak stage efficiency of 0.09 was obtained at 110 percent speed at a pressure ratio of 1.218 and a weight flow of 30.2 kg/sec. Maximum stage pressure ratio is 1.269 at 120 percent speed.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3101 , E-7791
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  • 66
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    Task 12 data dump (phase 2) OME integrated thrust chamber test report (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The characteristics and performance of the orbit maneuvering engine for the space shuttle are discussed. Emphasis is placed on the regeneratively cooled thrust chamber of the engine. Tests were conducted to determine engine operating parameters during the start, shutdown, and restart. Characteristics of the integrated thrust chamber and the performance and thermal conditions for blowdown operation without supplementary boundary layer cooling were investigated. The results of the test program are presented.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-140250 , ASR74-229
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  • 67
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    Preparing oxidizer coated metal fuel particles (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A solid propellant composition of improved efficiency is described which includes an oxidizer containing ammonium perchlorate, and a powered metal fuel, preferably aluminum or beryllium, in the form of a composite. The metal fuel is contained in the crystalline lattice framework of the oxidizer, as well as within the oxidizer particles, and is disposed in the interstices between the oxidizer particles of the composition. The propellant composition is produced by a process comprising the crystallization of ammonium perchlorate in water, in the presence of finely divided aluminum or beryllium. A suitable binder is incorporated in the propellant composition to bind the individual particles of metal with the particles of oxidizer containing occluded metal.
    Keywords: PROPULSION SYSTEMS
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  • 68
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    Operations planning simulation: Model study (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of simulation modeling for the identification of system sensitivities to internal and external forces and variables is discussed. The technique provides a means of exploring alternate system procedures and processes, so that these alternatives may be considered on a mutually comparative basis permitting the selection of a mode or modes of operation which have potential advantages to the system user and the operator. These advantages are measurements is system efficiency are: (1) the ability to meet specific schedules for operations, mission or mission readiness requirements or performance standards and (2) to accomplish the objectives within cost effective limits.
    Keywords: GENERAL
    Type: NASA-CR-120429 , SU-OPS-RP-74-0001
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  • 69
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    Nonlinear models for estimating GSFC travel requirements (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A methodology is presented for estimating travel requirements for a particular period of time. Travel models were generated using nonlinear regression analysis techniques on a data base of FY-72 and FY-73 information from 79 GSFC projects. Although the subject matter relates to GSFX activities, the type of analysis used and the manner of selecting the relevant variables would be of interest to other NASA centers, government agencies, private corporations and, in general, any organization with a significant travel budget. Models were developed for each of six types of activity: flight projects (in-house and out-of-house), experiments on non-GSFC projects, international projects, ART/SRT, data analysis, advanced studies, tracking and data, and indirects.
    Keywords: GENERAL
    Type: NASA-TN-D-7642 , G-7415 , D-7642
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  • 70
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    Technology utilization in a non-urban region: Further impact and technique of the Technology Use Studies Center (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Updated information pertaining to clients who receive and use information disseminated by the Technology Use Studies Center (TUSC) is reported. Charts are provided which indicate TUSC's performance in information dissemination and technical assistance in terms of quantities of searches accomplished during several contract years. The faculty information service is described, along with details of cooperation with other agencies. Specific searches are listed according to subject, client, and client location, and a measure of client response to services provided is indicated by the included selection of transfer and impact reports. The impetus behind the formation of the general aviation news letter is also described.
    Keywords: GENERAL
    Type: NASA-CR-139565
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  • 71
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    Extended temperature range ACPS thruster investigation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The successful hot fire demonstration of a pulsing liquid hydrogen/liquid oxygen and gaseous hydrogen/liquid oxygen attitude control propulsion system thruster is described. The test was the result of research to develop a simple, lightweight, and high performance reaction control system without the traditional requirements for extensive periods of engine thermal conditioning, or the use of complex equipment to convert both liquid propellants to gas prior to delivery to the engine. Significant departures from conventional injector design practice were employed to achieve an operable design. The work discussed includes thermal and injector manifold priming analyses, subscale injector chilldown tests, and 168 full scale and 550 N (1250 lbF) rocket engine tests. Ignition experiments, at propellant temperatures ranging from cryogenic to ambient, led to the generation of a universal spark ignition system which can reliably ignite an engine when supplied with liquid, two phase, or gaseous propellants. Electrical power requirements for spark igniter are very low.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134655
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  • 72
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    Space shuttle maneuvering engine reusable thrust chamber program. Task 11: Low Epsilon stability test plan (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The performance and heat transfer characteristics of a doublet element type injector for the space shuttle orbiter maneuvering engine thrust chamber were investigated. Ths stability characteristics were evaluated over a range of chamber pressures and mixture ratios. The specific objectives of the test were: (1) to determine whether stability has been influenced by injection of boundary layer coolant across the cavity entrance, (2) if the injector is stable, to determine the minimum cavity area required to maintain stability, and (3) if the injector is unstable, to determine the effects of entrance geometry and increased area on stability.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134359 , ASR74-204
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  • 73
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    Advanced supersonic technology propulsion system study (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This study had the objectives of determining the most promising conventional and variable cycle engine types; the effect of design cruise Mach number (2.2, 2.7 and 3.2) on a commercial supersonic transport; effect of advanced engine technology on the choice of engine cycle; and effect of utilizing hydrogen as the engine fuel. The technology required for the engines was defined, and the levels of development to ensure availability of this technology in advanced aircraft propulsion systems were assessed. No clearcut best conventional or variable cycle engine was identified. The dry bypass turbojet and the duct burning turbofans were initially selected as the best conventional engines, but later results, utilizing augmentation at takeoff, added the mixed-flow augmented turbofan as a promising contender. The modulating air flow, three-rotor variable cycle engine identified the performance features desired from VCE concepts (elimination of inlet drag and reduction in afterbody drag), but was a very heavy and complex engine.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-143634 , R74AEG330
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  • 74
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    Terminal-shock and restart control of a Mach 2.5, mixed compression inlet coupled to a turbofan engine (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of an experimental program conducted on a mixed-compression inlet coupled to a turbofan engine are presented. Open-loop frequency response data are presented that show the response of shock position (as measured by an average inlet static pressure) to sinusoidal airflow disturbances produced at the compressor face station. Also presented are results showing the effect of different passive terminations (a choke plate or a long duct) on the characteristics of the inlet. Transfer functions obtained by using experimental data are presented and compared to the experimental data. Closed-loop frequency response of shock position (with a proportional-plus-integral controller) is presented. In addition, transient data are presented that show the unstart-restart characteristics of the inlet.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3104 , E-7924
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  • 75
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    Digital servo control of random sound test excitation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digital servocontrol system for random noise excitation of a test object in a reverberant acoustic chamber employs a plurality of sensors spaced in the sound field to produce signals in separate channels which are decorrelated and averaged. The average signal is divided into a plurality of adjacent frequency bands cyclically sampled by a time division multiplex system, converted into digital form, and compared to a predetermined spectrum value stored in digital form. The results of the comparisons are used to control a time-shared up-down counter to develop gain control signals for the respective frequency bands in the spectrum of random sound energy picked up by the microphones.
    Keywords: GENERAL
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  • 76
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    Star scanner (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A star scanner on a spin stabilized spacecraft is described which includes a reticle with a pair of slits having different separations as a function of the spacecraft vertical plane, to form a V slit. The time between a star image crossing one of the slits relative to a reference telemetry time provides an indication of azimuth angle. The time between the image crossing the two slits provides an indication of elevation angle of the star. If a star cluster is detected such that two stars pass the slits in less time than normally required for a single star to cross the two slits, an indication of the cluster occurrence is derived. Means are provided to prevent effective detection of large celestial bodies, such as the sun or moon.
    Keywords: GENERAL
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  • 77
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    Centrifugal lyophobic separator (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A centrifugal separator is described using a lyophobic filter for removing liquid particles from a mixed stream of gas and liquid under various negative or positive external acceleration conditions as well as zero g or weightless conditions. Rotating the lyophobic filter and inclining the filter to the entering flow improves the lyophobic properties of the filter, provides gross separation of larger liquid particles, and prevents prolonged contact of liquid droplets with the spinning filter which might change the filter properties or block the filter.
    Keywords: GENERAL
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  • 78
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    Determinants of project success (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The interactions of numerous project characteristics, with particular reference to project performance, were studied. Determinants of success are identified along with the accompanying implications for client organization, parent organization, project organization, and future research. Variables are selected which are found to have the greatest impact on project outcome, and the methodology and analytic techniques to be employed in identification of those variables are discussed.
    Keywords: GENERAL
    Type: NASA-CR-139407
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  • 79
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    Automated Firearms Identification System (AFIDS), phase 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Items critical to the future development of an automated firearms identification system (AFIDS) have been examined, with the following specific results: (1) Types of objective data, that can be utilized to help establish a more factual basis for determining identity and nonidentity between pairs of fired bullets, have been identified. (2) A simulation study has indicated that randomly produced lines, similar in nature to the individual striations on a fired bullet, can be modeled and that random sequences, when compared to each other, have predictable relationships. (3) A schematic diagram of the general concept for AFIDS has been developed and individual elements of this system have been briefly tested for feasibility. Future implementation of such a proposed system will depend on such factors as speed, utility, projected total cost and user requirements for growth. The success of the proposed system, when operational, would depend heavily on existing firearms examiners.
    Keywords: GENERAL
    Type: NASA-CR-139371 , JPL-SP-43-8
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  • 80
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    Analytic models of ducted turbomachinery tone noise sources. Volume 3: Program test case results (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Computer programs for analyzing the acoustic properties of turbomachinery with ducted flow were developed. The models include component interactions and rotor alone. Test case results determined from the computer programs are presented.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-132445 , D6-43296-3
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  • 81
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    Development of a short pulsed solid propellant plasma thruster (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The experimental results are summarized that were obtained in the development of a Teflon solid propellant pulsed plasma thruster. The feasibility was established of storing and feeding solid propellant in the form of an open circular loop into an operational thruster. This technique was verified to be practical by feeding over 20 inches of Teflon into a micro-thruster over an accumulated life test of 1858 hours. High energy density capacitors were evaluated under vacuum conditions when the capacitor is coupled directly to a plasma thruster. Numerous early capacitor failures were encountered. It was concluded that essentially all of the failures encountered in a vacuum environment are due to an internal electrical breakdown that will occur inside a capacitor that is not truly hermetically sealed. A steady input power significantly in excess of 130 watts can safely be tolerated if heat conduction can be provided to a sink whose temperature is about 16 C. A vacuum life test of the capacitor bank was carried out while discharging into a milli-lb. (milli-Newton) type pulsed plasma thruster. More than 1500 hours of vacuum testing of this milli-Newton type system has been accumulated without any capacitor problems. Recommendations are made for future capacitor designs.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-139272 , MS172R0001
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  • 82
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    Analytic models of ducted turbomachinery tone noise sources. Volume 2: Subprogram documentation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytical models were developed for computing the periodic sound pressures of subsonic fans in an infinite hardwall annular duct with uniform flow. The computer programs are described which are used for numerical computations of sound pressure mode amplitudes. The data are applied to the acoustic properties of turbomachinery.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-132444 , D6-43296-2
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  • 83
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    Analytic models of ducted turbomachinery tone noise sources. Volume 1: Analysis (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analytic models developed for computing the periodic sound pressure of subsonic fans and compressors in an infinite, hardwall annular duct with uniform flow are described. The basic sound-generating mechanism is the scattering into sound waves of velocity disturbances appearing to the rotor or stator blades as a series of harmonic gusts. The models include component interactions and rotor alone.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-132443 , D6-43296-1
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  • 84
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    Noise generated by quiet engine fans. 2: Fan A (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A significant effort within the NASA Quiet Engine Program has been devoted to acoustical evaluation at the Lewis Research Center noise test facility of a family of full-scale fans. This report, documents the noise results obtained with fan A - a 1.5-pressure-ratio, 1160-ft/sec-tip-speed fan. The fan is described and some aerodynamic operating data are given. Far-field noise around the fan was measured for a variety of configurations pertaining to acoustical treatment and over a range of operating conditions. Complete results of 1/3-octave band analysis of the data are presented in tabular form. Included also are power spectra and sideline perceived noise levels. Some representative 1/3-octave band data are presented graphically, and sample graphs of continuous narrow-band spectra are also provided.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3066 , E-7857
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  • 85
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    Instantaneous distortion in a Mach 2.5, 40-percent-internal-contraction inlet and its effect on turbojet stall margin (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental wind tunnel investigation was conducted to determine the effects of time-variant distortions produced in a supersonic inlet on a J85-GE-13 turbojet engine. Results are presented principally in terms of instantaneous distortion amplitudes and total-pressure contours measured through compressor stall. They indicate that, although a time-averaged distortion may be far from a stall-inducing value, corresponding instantaneous distortion amplitudes can approach or exceed this value. Seven engine stall events were studied. In six of these events instantaneous distortion peaks of sufficient magnitude to cause stall were observed in the time period shortly before stall was detected.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3002 , E-6294
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  • 86
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    Erosion in radial inflow turbines. Volume 2: Balance of centrifugal and radial drag forces on erosive particles (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The particle motion in two-dimensional free and forced inward flowing vortices is considered. A particle in such a flow field experiences a balance between the aerodynamic drag forces that tend to drive erosive particles toward the axis, and centrifugal forces that prevent these particles from traveling toward the axis. Results predict that certain sizes of particles will achieve a stable orbit about the turbine axis in the inward flowing free vortex. In this condition, the radial drag force is equal to the centrifugal force. The sizes of particles that will achieve a stable orbit is shown to be related to the gas flow velocity diagram at a particular radius. A second analysis yields a description of particle sizes that will experience a centrifugal force that is greater than the radial component of the aerodynamic drag force for a more general type of particle motion.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134616
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  • 87
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    Conceptual design studies of lift/cruise fans for military transports (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study program for conceptual design studies of remote lift and lift/cruise fan systems to meet the requirements of military V/STOL aircraft was conducted. Parametric performance and design data are presented for fans covering a range of pressure ratios, including both single and two stage fan concepts. The gas generator selected for these fan systems was the J101-GE-100 engine. Noise generation and transient response were determined for selected fan systems.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134636 , R74AEG283
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  • 88
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    Measurement of plasma temperature and density using radiation absorption (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A procedure, using a light beam of predetermined wavelength, preferably monochromatic, for measuring plasma characteristics is presented. Light absorbed by the plasma is used to obtain an absorption coefficient for the plasma. From this known coefficient and independent measurement of either the electron density or temperature of the plasma, an equation may be solved to obtain other unknown quantities. In this procedure, the absorption coefficient of the plasma is derived simultaneously for two probing light beams of substantially different predetermined wavelengths. These two coefficients are used to solve the two equations, which are in turn used to determine plasma electron density and temperature.
    Keywords: GENERAL
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  • 89
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    Heat conduction controlled combustion for scramjet applications (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of heat conduction flame generated in a premixed supersonic stream is discussed. It is shown that the flame is controlled initially by heat conduction and then by chemical reaction. Such a flame is shorter than the diffusion type of flame and therefore it requires a much shorter burner. The mixing is obtained by injecting the hydrogen in the inlet. Then the inlet can be cooled by film cooling.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-132446
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  • 90
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    A Markovian model for assessment of personnel hiring plans (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: As a result of the current economic environment, many organizations are having to operate with fewer resources. In the manpower area, these constraints have forced organizations to operate within well-defined hiring plans. Exceeding personnel ceilings is in most cases an intolerable situation. A mathematical model, based on the theory of Markov processes, is presented which can be used to assess the chances of success of personnel hiring plans. The model considers a plan to be successful if the final population size, at the end of the planning period, lies within a range specified by management. Although this model was developed to assess personnel hiring plans at the Goddard Space Flight Center, it is directly applicable wherever personnel hiring plans are used.
    Keywords: GENERAL
    Type: NASA-TN-D-7640 , G-7410
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  • 91
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    Recording and cataloging hazards information, revision A (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A data collection process is described for the purpose of discerning causation factors of accidents, and the establishment of boundaries or controls aimed at mitigating and eliminating accidents. A procedure is proposed that suggests a discipline approach to hazard identification based on energy interrelationships together with an integrated control technique which takes the form of checklists.
    Keywords: GENERAL
    Type: NASA-TM-X-64782
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  • 92
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    California four cities program, 1971 - 1973 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A pilot project in aerospace-to-urban technology application is reported. Companies assigned senior engineering professionals to serve as Science and Technology Advisors to participating city governments. Technical support was provided by the companies and JPL. The cities, Anaheim, Fresno, Pasadena, and San Hose, California, provided the working environment and general service support. Each city/company team developed and carried out one or more technical or management pilot projects together with a number of less formalized technology efforts and studies. An account and evaluation is provided of the initial two-year phase of the program.
    Keywords: GENERAL
    Type: NASA-CR-138768 , JPL-SP-43-4
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  • 93
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    Computer programs for pressurization (RAMP) and pressurized expulsion from a cryogenic liquid propellant tank (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis to predict the pressurant gas requirements for the discharge of cryogenic liquid propellants from storage tanks is presented, along with an algorithm and two computer programs. One program deals with the pressurization (ramp) phase of bringing the propellant tank up to its operating pressure. The method of analysis involves a numerical solution of the temperature and velocity functions for the tank ullage at a discrete set of points in time and space. The input requirements of the program are the initial ullage conditions, the initial temperature and pressure of the pressurant gas, and the time for the expulsion or the ramp. Computations are performed which determine the heat transfer between the ullage gas and the tank wall. Heat transfer to the liquid interface and to the hardware components may be included in the analysis. The program output includes predictions of mass of pressurant required, total energy transfer, and wall and ullage temperatures. The analysis, the algorithm, a complete description of input and output, and the FORTRAN 4 program listings are presented. Sample cases are included to illustrate use of the programs.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-7504 , E-7654
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  • 94
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    The hard start phenomena in hypergolic engines. Volume 2: Combustion characteristics of propellants and propellant combinations (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The combustion characteristics of hypergolic propellants are described. A research project was conducted to determine if the reaction control system engine propellants on Apollo spacecraft undergo explosive reaction when subjected to conditions present in the engine at the time of ignition. Combustion characteristics pertinent to the hard-start phenomenon are considered. The thermal stability of frozen mixtures of hydrazine-based fuels with nitrogen tetroxide was analyzed. Results of the tests are presented in the form of tables and graphs.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134314 , BM-IR-1646-VOL-2
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  • 95
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    Economic effects of propulsion system technology on existing and future transport aircraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of an airline study of the economic effects of propulsion system technology on current and future transport aircraft are presented. This report represents the results of a detailed study of propulsion system operating economics. The study has four major parts: (1) a detailed analysis of current propulsion system maintenance with respect to the material and labor costs encountered versus years in service and the design characteristics of the major elements of the propulsion system of the B707, b727, and B747. (2) an analysis of the economic impact of a future representative 1979 propulsion system is presented with emphasis on depreciation of investment, fuel costs and maintenance costs developed on the basis of the analysis of the historical trends observed. (3) recommendations concerning improved methods of forecasting the maintenance cost of future propulsion systems are presented. A detailed method based on the summation of the projected labor and material repair costs for each major engine module and its installation along with a shorter form suitable for quick, less detailed analysis are presented, and (4) recommendations concerning areas where additional technology is needed to improve the economics of future commercial propulsion systems are presented along with the suggested economic benefits available from such advanced technology efforts.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134645
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  • 96
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    Specific wavelength colorimeter (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A self contained, specific wavelength, single beam colorimeter is described for direct spectrophotometric measurement of the concentration of a given solute in a test sample. An electrical circuit employing a photoconductive cell converts the optical output into a linear, directly readable meter output. The colorimeter is simple to operate and is adapted for use in zero gravity conditions. In a specific application, the colorimeter is designed to analyze the concentration of iodine in potable water carried aboard a space vehicle such as the 4B stage of Skylab.
    Keywords: GENERAL
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  • 97
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    Magnetocaloric pump (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A vessel having inlet and outlet valves is disposed in a container with a fluid to be pumped which may be evolved from a liquid in the container below the vessel. A magnetocaloric substance is disposed in the vessel and causes fluid vapor in the vessel to expand and be expelled through the outlet valve. Vapor is drawn in through the inlet valve as the substance cools. The inlet valves may be one-way check valves or may be solenoid valves energized at appropriate times by timing circutis. A timer controlled heating element may also be disposed in the vessel to operate in conjunction with the magnetic field.
    Keywords: GENERAL
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  • 98
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    Apparatus for conducting flow electrophoresis in the substantial absence of gravity (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A zero-g, constant flow electrophoretic separating apparatus is presented. The apparatus is composed a deflecting member to spread carrier fluid across a conduit, and an end wall with a valve located in the conduit past the separation electrodes from which layers of carrier and sample may be extracted. Electrode electrolyte is separated from the carrier and continually circulated and cleaned.
    Keywords: GENERAL
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  • 99
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    Three mirror glancing incidence system for X-ray telescope (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A telescope suitable for soft X-ray astronomical observations consists of a paraboloid section for receiving rays at a grazing angle and a hyperboloid section which receives reflections from the paraboloid at a grazing angle and directs them to a predetermined point of focus. A second hyperboloid section is centrally located from the other two surfaces and positioned to reflect from its outer surface radiation which was not first reflected by the paraboloid. A shutter is included to assist in calibration.
    Keywords: GENERAL
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  • 100
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    Apparatus for establishing flow of a fluid mass having a known velocity (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An apparatus for establishing a flow of fluid mass, such as gas, having a known velocity is introduced. The apparatus is characterized by an hermetically sealed chamber conforming to a closed-loop configuration and including a throat and a plurality of axially displaceable pistons for sweeping through the throat a stream of gas including a core and an unsheared boundary layer. Within the throat there is a cylindrical coring body concentrically related to the throat for receiving the core, and a chamber surrounding the cylindrical body for drawing off the boundary layer, whereby the velocity of the core is liberated from the effects of the velocity of the boundary layer.
    Keywords: GENERAL
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