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  • Chemical Engineering  (1,794)
  • PROPULSION SYSTEMS  (1,456)
  • BIOTECHNOLOGY  (1,374)
  • 1970-1974  (4,624)
Collection
Keywords
Publisher
Years
Year
  • 1
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    Lunar microcosmos (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: A human habitat on the lunar surface requires energy recycling metabolites based on the utilization of vegetative plants that are good photosynthesizers. Selection criteria involve reactions to fertilization by human excrements, suitability as food for man (with or without fractionation), physiological effects of prolonged ingestion of these plants, and technical methods for returning inedible portions back into the cycle.
    Keywords: BIOTECHNOLOGY
    Type: Inhabited Space, Pt. 2 (NASA-TT-F-820); p 53-61
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  • 2
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    Data on the acoustic comfort of passengers in railroad cars and soundproofing recommendations (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Acoustic passenger comfort in railroad cars is represented by the following values: Total noise level in db, octave sound spectrum in db, and indices of intelligibility. The noise level perceived inside the car results from two components: one due to the penetration of air noise, and another due to the transmission of vibrations through solids. Measurement results show the necessity of improving bogie and bogie-body connections, intensification of soundproofing of the floor, adaption of windows with double panes, etc.
    Keywords: BIOTECHNOLOGY
    Type: The 4th Natl. Conf. on Acoustics, Vol. 1A (NASA-TT-F-15375); p 218-223
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  • 3
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    Some aspects of sound discomfort caused by streetcar traffic (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Streetcar noise was investigated on different lines and inside different types by sonometer measurements. The results showed variations of the total noise intensity between 88-97 db. In some squares with heavy traffic the total noise intensity reached 106 db. Noise intensity measurements inside different types of streetcars brought to light high values between 101-106 db, while in the case of the new silent type of streetcar the values were 86-87 db. The importance of the sound discomfort produced by streetcar traffic is emphasized, inasmuch as the noise intensity exceeds by far the values recommended by communal hygiene.
    Keywords: BIOTECHNOLOGY
    Type: The 4th Natl. Conf. on Acoustics, Vol. 1A (NASA-TT-F-15375); p 212-217
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  • 4
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    Level, peculiarities and effects of coal mine noise on pit workers (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: There exists a correlation between noise intensity and spectrum and degree of hearing impairment in the different professional categories in the pit. Most affected are dross miners and drillers. In these, the first degree of hypoacusia sets in within the first five years of exposure. Deafness begins at a frequency of 4,000 Hz, but often enough (20%) at 2,000 Hz as well, progressively evolving through the classical stages if exposure to noise continues. In the coal bearing basins investigated, the noise level is, on the whole, 31.2%, but the conventional zone is not involved by more than 6.3%. Technological and medical measures are proposed for the purpose of avoiding these troubles in the future.
    Keywords: BIOTECHNOLOGY
    Type: The 4th Natl. Conf. on Acoustics, Vol. 1A (NASA-TT-F-15375); p 170-176
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  • 5
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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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  • 6
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    Oxygen utilization of the human left ventricle - An indirect method for its evaluation and clinical considerations (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An analytical method is presented for determining the oxygen consumption rate of the intact heart working (as opposed to empty but beating) human left ventricle. Use is made of experimental recordings obtained for the chamber pressure and the associated dimensions of the LV. LV dimensions are determined by cineangiocardiography, and the chamber pressure is obtained by means of fluid-filled catheters during retrograde or transeptal catheterization. An analytical method incorporating these data is then employed for the evaluation of the LV coronary oxygen consumption in five subjects. Oxygen consumption for these subjects was also obtained by the conventional clinical method in order to evaluate the reliability of the proposed method.
    Keywords: BIOTECHNOLOGY
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  • 7
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    Angiocardiographic methods for determination of left ventricular geometry and volume (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Methods are described for calculating left ventricular (LV) dimensions and chamber volumes from radiographic films. The use of biplane films for the calculation of LV volume and volume change is based on the assumption of an ellipsoidal geometry. Calculation of LV volumes from biplane films usually overestimated known volumes in postmortem hearts regardless of the methods used for volume calculation. The reasons for this are probably best explained by the fact that a smooth-surface ellipse is used to represent the irregular cavity of the LV chamber. LV volume calculated from data in a single plane compared favorably and closely with volumes calculated from biplane films. A table of normal values of ventricular volume established by angiographic studies is presented.
    Keywords: BIOTECHNOLOGY
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  • 8
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    Cardiac mechanics: Physiological, clinical, and mathematical considerations (1974)
    In:  Other Sources
    Details
    Publication Date: 2016-03-07
    Description: Recent studies concerning the basic physiological and biochemical principles underlying cardiac muscle contraction, methods for the assessment of cardiac function in the clinical situation, and mathematical approaches to cardiac mechanics are presented. Some of the topics covered include: cardiac ultrastructure and function in the normal and failing heart, myocardial energetics, clinical applications of angiocardiography, use of echocardiography for evaluating cardiac performance, systolic time intervals in the noninvasive assessment of left ventricular performance in man, evaluation of passive elastic stiffness for the left ventricle and isolated heart muscle, a conceptual model of myocardial infarction and cardiogenic shock, application of Huxley's sliding-filament theory to the mechanics of normal and hypertrophied cardiac muscle, and a rheological modeling of the intact left ventricle. Individual items are announced in this issue.
    Keywords: BIOTECHNOLOGY
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  • 9
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    Electric propulsion - Now (1974)
    In:  Other Sources
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    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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  • 10
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    A model of heat transfer in immersed man (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An equation representing man's thermal balance under water is considered. The equation states that the body thermal loading from metabolic heat production and artificial heat input must be offset by respiratory and environmental heat exchange to maintain a constant body temperature. Critical body regions are affected by cold-water thermal stress. A model of the thermoregulatory system may be divided into the physical-controlled system and the dynamic controlling system. The thermal model is simulated by computer programs.
    Keywords: BIOTECHNOLOGY
    Type: Annals of Biomedical Engineering; 2; 1974
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  • 11
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    Quiet engine from NASA (1974)
    In:  Other Sources
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    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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  • 12
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    Analytic model for assessing the thermal performance of scuba divers (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A biothermal model with a physically-controlled subsystem and a dynamically-controlled subsystem is developed to simulate the thermoregulatory system of man under immersed conditions. The model is consistent with experimental data for seminude subjects immersed to neck in cool to temperate water and for 'wet-suited' subjects immersed to neck in cold water. Equations are derived for predicting body temperatures under various dive conditions.
    Keywords: BIOTECHNOLOGY
    Type: Journal of Hydronautics; 8; July 197
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  • 13
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    Untoward effects of a sympathomimetic amine (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Presentation and discussion of a clinical report describing asymptomatic multifocal ventricular premature contractions in a professional pilot. He had been taking heavy doses of a systemic decongestant agent, pseudoephedrine, prescribed by a physician. He was taken off the medication, and over the next few days the PVCs became less frequent, then disappeared. It is pointed out that physician's instructions to pilots must be given with the realization that some airmen may follow the instructions too zealously in an attempt to remain on flying status.
    Keywords: BIOTECHNOLOGY
    Type: Aerospace Medicine; 45; May 1974
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  • 14
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    Orthostatic tolerance in dehydrated, heat-acclimated men following exercise in the heat (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: BIOTECHNOLOGY
    Type: Aerospace Medicine; 45; May 1974
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  • 15
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    Plasma volume and blood constituent shifts during +Gz acceleration after bedrest with exercise conditioning (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: BIOTECHNOLOGY
    Type: Aerospace Medicine; 45; Apr. 197
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  • 16
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    Putting all our noise technology to work (1974)
    In:  Other Sources
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    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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  • 17
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    Effect of bed rest and exercise on body balance (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A battery of 11 body balance tests was administered to 7 men before and after 14 days of bedrest. Seven men who had not undergone bed rest served as controls. During bed rest, each subject underwent daily either isotonic, isometric, or no leg exercise. The results showed that, for the bed-rested no exercise, isotonic exercise, and isometric exercise groups, 2 weeks of bed rest produces significant body balance decrements on 3, 4, and 5 of the 11 tests, respectively. Daily leg exercise did not prevent the debilitating effects of bed rest on body balance. After bed rest, balance skill was relearned rapidly so that in most tests, performance had reached prebed-rest levels by the third recovery day. These data suggest that balance impairment is not due to loss of muscular strength in the legs but, perhaps, to a bed-rest-related change in the neurally coded information to postural control centers.
    Keywords: BIOTECHNOLOGY
    Type: Journal of Applied Physiology; 36; Mar. 197
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  • 18
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    Dynamic optometer (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A dynamic optometer that electronically records the position of the anterior surface of the human lens is described. The geometrical optics of the eye and optometer, and the scattering of light from the lens, are closely examined to determine the optimum conditions for adjustment of the instrument. The light detector and associated electronics are also considered, and the operating conditions for obtaining the best signal-to-noise ratio are determined.
    Keywords: BIOTECHNOLOGY
    Type: Optical Society of America; vol. 64
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  • 19
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    Internal tibial torsion correction study (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A quantitative study of internal torsion in the entire tibial bone was performed by using strain gauges to measure the amount of deformation occuring at different locations. Comparison of strain measurements with physical dimensions of the bone produced the modulus of rigidity and its behavior under increased torque. Computerized analysis of the stress distribution shows that more strain occurs near the torqued ends of the bones where also most of the twisting and fracturing takes place.
    Keywords: BIOTECHNOLOGY
    Type: NASA. Goddard Space Flight Center Summer Inst. in Biomed. Eng., 1973; 23 p
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  • 20
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    Design of an automatic weight scale for an isolette (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The design of an infant weight scale is reported that fits into an isolette without disturbing its controlled atmosphere. The scale platform uses strain gages to measure electronically deflections of cantilever beams positioned at its four corners. The weight of the infant is proportional to the sum of the output voltages produced by the gauges on each beam of the scale.
    Keywords: BIOTECHNOLOGY
    Type: NASA. Goddard Space Flight Center Summer Inst. in Biomed. Eng., 1973; 15 p
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  • 21
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    The design of an experiment for employing the hearer-feeler differentiation device, part B (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An experimental test design is outlined to separate feelers from hearers in the evaluation of persons with varying degrees of hearing impairments. Speech envelope cues are derived from a white noise device containing filters for different frequencies that produce speech awareness thresholds.
    Keywords: BIOTECHNOLOGY
    Type: NASA. Goddard Space Flight Center Summer Inst. in Biomed. Eng., 1973; 6 p
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  • 22
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    The design of a device for hearer and feeler differentiation, part A (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A speech modulated white noise device is reported that gives the rhythmic characteristics of a speech signal for intelligible reception by deaf persons. The signal is composed of random amplitudes and frequencies as modulated by the speech envelope characteristics of rhythm and stress. Time intensity parameters of speech are conveyed through the vibro-tactile sensation stimuli.
    Keywords: BIOTECHNOLOGY
    Type: NASA. Goddard Space Flight Center Summer Inst. in Biomed. Eng., 1973; 12 p
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  • 23
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    Surface potential profiles (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The gathering of surface potential profiles by computerized processing of electrocardiogram data is projected. These profiles are concerned with the detail of localized potentials on the human body and are obtained by voltages plotted against electrode positions with time as the variable held constant. Sample and hold circuits are considered for processing the multiplexed signal and to digitize and code it for the tape recorder.
    Keywords: BIOTECHNOLOGY
    Type: NASA. Goddard Space Flight Center Summer Inst. in Biomed. Eng., 1973; 15 p
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  • 24
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    Surgical suite environmental control system (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Theoretical and experimental work for a systems analysis approach to the problem of surgical suit exhaust systems centered on evaluation of halothane absorbing filters. An activated charcoal-alumina-charcoal combination proved to be the best filter for eliminating halothane through multilayer absorption of gas molecules.
    Keywords: BIOTECHNOLOGY
    Type: NASA. Goddard Space Flight Center Summer Inst. in Biomed. Eng., 1973; 24 p
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  • 25
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    Erosion and the gas turbine engine, part 2 (1974)
    In:  Other Sources
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    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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  • 26
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    Simple device for automatically transferring broth cultures (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: BIOTECHNOLOGY
    Type: Applied Microbiology; 27; Mar. 197
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  • 27
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    A wireless respiration failure detection system (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: BIOTECHNOLOGY
    Type: Medical and Biological Engineering; 12; May 1974
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  • 28
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    Light flashes observed by astronauts on Apollo 11 through Apollo 17 (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The crew members on the last seven Apollo flights observed light flashes that are tentatively attributed to cosmic ray nuclei (atomic number equal to or greater than 6) penetrating the head and eyes of the observers. Analyses of the event rates for all missions has revealed an anomalously low rate for transearth coast observations with respect to translunar coast observations.
    Keywords: BIOTECHNOLOGY
    Type: Science; 183; Mar. 8
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  • 29
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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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  • 30
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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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  • 31
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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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  • 32
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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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  • 33
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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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  • 34
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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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  • 35
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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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  • 36
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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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    Power spectral density analysis of the electromyogram from a work task performed in a full pressure suit (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Surface electromyograms (EMG) taken from three upper torso muscles during a push-pull task were analyzed by a power spectral density technique to determine the utility of the spectral analysis for identifying changes in the EMG caused by muscular fatigue. The results confirmed the value of the frequency analysis for identifying fatigue producing muscular performance. Data revealed reliable differences between muscles in fatigue induced responses to various locations in the reach envelope at which the subjects were required to perform the push-pull exercise, and the differential sensitivity of individual muscles to the various reach positions; i.e., certain reach positions imposed more fatigue related shifts in EMG power than did others. It was found that a pressurized space suit changed the pattern of normal shirtsleeve muscle fatigue responses in all three of the muscles.
    Keywords: BIOTECHNOLOGY
    Type: NASA-TM-X-58136 , JSC-09004
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  • 38
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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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  • 39
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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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  • 40
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    Robot arm dynamics and control (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Variations in total inertia and gravity loads at the joint outputs are treated along with the relative importance of gravity and acceleration-generated reaction torques or forces versus inertia torques or forces. The relation between the dynamical state equations in explicit terms and servoing the manipulator is briefly discussed in the framework of state variable feedback control which also forms the basis of adaptive manipulator control. Exact state equations were determined for total inertia and gravity loads at the joint outputs as a function of joint variables, using the constant inertial and geometric parameters of the individual links defined in the respective link coordinate frames. The range of maximum variations in total inertia and gravity loads at the joint outputs was calculated for both no load and load in the hand. The main result is the construction of a set of greatly simplified state equations which describe the total inertia and gravity load variations at the output of the six joints with an average error of less than 5%.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-136935 , JPL-TM-33-669
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  • 41
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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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  • 42
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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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  • 43
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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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  • 44
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    Design development and test: Two-gas atmosphere control subsystem (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An atmosphere control subsystem (ACS) was developed for NASA-IBJSC which is designed to measure the major atmospheric constituents in the manned cabin of the space shuttle orbiter and control the addition of oxygen and nitrogen to maintain the partial pressures of these gases within very close limits. The ACS includes a mass spectrometer sensor (MSS) which analyzes the atmosphere of a shuttle vehicle pressurized cabin, and an electronic control assembly (ECA). The MSS was built and tested to meet the requirements for flight equipment for the M-171 Metabolic Analyzer experiment for the Skylab flight program. The instrument analyzes an atmospheric gas sample and produces continuous 0-5 vdc analog signals proportional to the partial pressures of H2, O2, N2, H2O, CO2 and total hydrocarbons having a m/e ratio between 50 and 120. It accepts signals from the MSS proportional to the partial pressures of N2 and O2 and controls the supply of these gases to the closed cabin.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-134190 , MDC-G4971
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  • 45
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    Development and fabrication of heat-sterilizable inhalation therapy equipment (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development of a completely heat sterilizable intermittent positive pressure breathing (IPPB) ventilator in an effort to reduce the number of hospital acquired infections is reported. After appropriate changes in materials and design were made, six prototype units were fabricated and were successfully field tested in local hospitals. Most components of the modified ventilators are compatible with existing machines. In all but a few instances, such as installation of bacteria-retentive filters and a modified venturi, the change over from non-heat-sterilizable to sterilizable units was accomplished by replacement of heat labile materials with heat stable materials.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-136832 , JPL-TM-33-670
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  • 46
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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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  • 47
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    Telemetry of left ventricular diameter and pressure measurements from unrestrained animals (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Keywords: BIOTECHNOLOGY
    Type: Journal of Applied Physiology; 37; Aug. 197
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  • 48
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    Tracking with head position using an electrooptical monitor (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An electrooptical head-position monitoring system was designed and built and is used in single-axis and three-axis 'hands-off' control tasks. The monitor consists of a transparent plexiglass body-fixed helmet provided with a set of eight silicon photodetectors sensing pitch, roll, and yaw motions of the head. Two light-emitting diodes, attached to the pilot's helmet liner, provide the ac modulated near infrared radiation. Head control is compared with conventional manual control for single-axis and three-axis tracking tasks. Both performance curves and describing functions are presented.
    Keywords: BIOTECHNOLOGY
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  • 49
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    Development of a Korotkov sound processor for automatic identification of auscultatory events. I - Specification of preprocessing bandpass filters (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Frequency bands that best discriminate the Korotkov sounds at systole and at diastole from the sounds immediately preceding these events are defined. Korotkov sound data were recorded from five normotensive subjects during orthostatic stress (lower body negative pressure) and bicycle ergometry. A spectral analysis of the seven Korotkov sounds centered about the systolic and diastolic auscultatory events revealed that a maximum increase in amplitude at the systolic transition occurred in the 18-26-Hz band, while a maximum decrease in amplitude at the diastolic transition occurred in the 40-60-Hz band. These findings were remarkably consistent across subjects and test conditions. These passbands are included in the design specifications for an automatic blood pressure measuring system used in conjuction with medical experiments during NASA's Skylab program.
    Keywords: BIOTECHNOLOGY
    Type: IEEE Transactions on Biomedical Engineering; BME-21; Mar. 197
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  • 50
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    Development of a Korotkov sound processor for automatic identification of auscultatory events. II - Decision logic specifications and operational verification (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: BIOTECHNOLOGY
    Type: IEEE Transactions on Biomedical Engineering; BME-21; Mar. 197
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  • 51
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    Membrane water deaerator investigation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The purpose of the membrane water deaerator program was to develop data on a breadboard hollow fiber membrane unit that removes both dissolved and evolved gas from a water transfer system in order to: (1) assure a hard fill of the EVLSS expendable water tank; (2) prevent flow blockage by gas bubbles in circulating systems; and (3) prevent pump cavitation.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-140259 , AIRESEARCH-74-10072
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  • 52
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    Space shuttle/food system study. Volume 2, appendix E: Alternate flight systems analysis (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The functional requirements of stowage, preparation, serving, consumption, and cleanup were applied to each of the five food mixes selected for study in terms of the overall design of the space shuttle food system. The analysis led to a definition of performance requirements for each food mix, along with a definition of equipment to meet those requirements. Weight and volume data for all five systems, in terms of food and packaging, support equipment, and galley installation penalties, are presented.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-134377
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  • 53
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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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  • 54
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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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  • 55
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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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  • 56
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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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  • 57
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    Preliminary flight prototype waste collection subsystem (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The zero gravity test program demonstrated the feasibility and practicability of collecting urine from both male and female crew members in a zero gravity environment in an earthlike manner not requiring any manual handling of urine containers. In addition, the testing demonstrated that a seat which is comfortable in both regimes of operation could be designed for use on the ground and in zero-gravity. Further, the tests showed that the vortex liquid/air separator is an effective liquid/air separation method in zero gravity. Visual observations indicate essentially zero liquid carry over. The system also demonstrated its ability to handle post elimination wipes without difficulty. The designs utilized in the WCS were verified as acceptable for usage in the space shuttle or other space vehicles.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-104240 , SVHSER-6509
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  • 58
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    Space shuttle food system study. Volume 1: System design report (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Data were assembled which define the optimum food system to support the space shuttle program, and which provide sufficient engineering data to support necessary requests for proposals towards final development and installment of the system. The study approach used is outlined, along with technical data and sketches for each functional area. Logistic support analysis, system assurance, and recommendations and conclusions based on the study results are also presented.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-134374
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    Corrosion control and disinfection studies in spacecraft water systems (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Disinfection and corrosion control in the water systems of the Saturn 5 Orbital Workshop Program are considered. Within this framework, the problem areas of concern are classified into four general areas: disinfection; corrosion; membrane-associated problems of disinfectant uptake and diffusion; and taste and odor problems arising from membrane-disinfectant interaction.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-140197
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  • 60
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    Role of man in flight experiment payloads, phase 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The identification of required data for studies of Spacelab experiment functional allocation, the development of an approach to collecting these data from the payload community, and the specification of analytical methods necessary to quantitatively determine the role of man in specific Spacelab experiments are presented. A generalized Spacelab experiment operation sequence was developed, and the parameters necessary to describe each signle function in the sequence were identified. A set of functional descriptor worksheets were also drawn up. The methodological approach to defining the role of man was defined as a series of trade studies using a digial simulation technique. The tradeoff variables identified include scientific crew size, skill mix, and location. An existing digital simulation program suitable for the required analyses was identified and obtained.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-120398
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  • 61
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    Earth orbital teleoperator system man-machine interface evaluation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The teleoperator system man-machine interface evaluation develops and implements a program to determine human performance requirements in teleoperator systems.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-139598 , H-4-1
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  • 62
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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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    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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  • 64
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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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  • 65
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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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  • 66
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    Firefighter's compressed air breathing system pressure vessel development program (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The research to design, fabricate, test, and deliver a pressure vessel for the main component in an improved high-performance firefighter's breathing system is reported. The principal physical and performance characteristics of the vessel which were required are: (1) maximum weight of 9.0 lb; (2) maximum operating pressure of 4500 psig (charge pressure of 4000 psig); (3) minimum contained volume of 280 in. 3; (4) proof pressure of 6750 psig; (5) minimum burst pressure of 9000 psig following operational and service life; and (6) a minimum service life of 15 years. The vessel developed to fulfill the requirements described was completely sucessful, i.e., every category of performence was satisfied. The average weight of the vessel was found to be about 8.3 lb, well below the 9.0 lb specification requirement.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-134384 , MCR-73-214
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  • 67
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    Space shuttle/food system study. Volume 2, Appendix G: Ground support system analysis. Appendix H: Galley functional details analysis (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The capabilities for preflight feeding of flight personnel and the supply and control of the space shuttle flight food system were investigated to determine ground support requirements; and the functional details of an onboard food system galley are shown in photographic mockups. The elements which were identified as necessary to the efficient accomplishment of ground support functions include the following: (1) administration; (2) dietetics; (3) analytical laboratories; (4) flight food warehouse; (5) stowage module assembly area; (6) launch site module storage area; (7) alert crew restaurant and disperse crew galleys; (8) ground food warehouse; (9) manufacturing facilities; (10) transport; and (11) computer support. Each element is discussed according to the design criteria of minimum cost, maximum flexibility, reliability, and efficiency consistent with space shuttle requirements. The galley mockup overview illustrates the initial operation configuration, food stowage locations, meal assembly and serving trays, meal preparation configuration, serving, trash management, and the logistics of handling and cleanup equipment.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-134379
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    Space shuttle/food system study. Volume 2, Appendix F: Flight food and primary packaging (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analysis and selection of food items and primary packaging, the development of menus, the nutritional analysis of diet, and the analyses of alternate food mixes and contingency foods is reported in terms of the overall food system design for space shuttle flight. Stowage weights and cubic volumes associated with each alternate mix were also evaluated.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-134378
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  • 69
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    Six-man, self-contained carbon dioxide concentrator subsystem for Space Station Prototype (SSP) application (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A six man, self contained, electrochemical carbon dioxide concentrating subsystem for space station prototype use was successfully designed, fabricated, and tested. A test program was successfully completed which covered shakedown testing, design verification testing, and acceptance testing.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-114742 , LSI-ER-170-34
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  • 70
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    Space shuttle/food system. Volume 2, Appendix C: Food cooling techniques analysis. Appendix D: Package and stowage: Alternate concepts analysis (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The relative penalties associated with various techniques for providing an onboard cold environment for storage of perishable food items, and for the development of packaging and vehicle stowage parameters were investigated in terms of the overall food system design analysis of space shuttle. The degrees of capability for maintaining both a 40 F to 45 F refrigerated temperature and a 0 F and 20 F frozen environment were assessed for the following cooling techniques: (1) phase change (heat sink) concept; (2) thermoelectric concept; (3) vapor cycle concept; and (4) expendable ammonia concept. The parameters considered in the analysis were weight, volume, and spacecraft power restrictions. Data were also produced for packaging and vehicle stowage parameters which are compatible with vehicle weight and volume specifications. Certain assumptions were made for food packaging sizes based on previously generated space shuttle menus. The results of the study are shown, along with the range of meal choices considered.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-134376
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  • 71
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    Space shuttle/food system study. Volume 2, Appendix A: Active heating system-screening analysis. Appendix B: Reconstituted food heating techniques analysis (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Technical data are presented which were used to evaluate active heating methods to be incorporated into the space shuttle food system design, and also to evaluate the relative merits and penalties associated with various approaches to the heating of rehydrated food during space flight. Equipment heating candidates were subject to a preliminary screening performed by a selection rationale process which considered the following parameters; (1) gravitational effect; (2) safety; (3) operability; (4) system compatibility; (5) serviceability; (6) crew acceptability; (7) crew time; (8) development risk; and (9) operating cost. A hot air oven, electrically heated food tray, and microwave oven were selected for further consideration and analysis. Passive, semi-active, and active food preparation approaches were also studied in an effort to determine the optimum method for heating rehydrated food. Potential complexity, cost, vehicle impact penalties, and palatability were considered in the analysis. A summary of the study results is provided along with cost estimates for each of the potential sytems
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-134375
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  • 72
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    Research on the properties of circadian systems amenable to study in space (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Three areas of inquiry are reported for the Skylab Experiment S-071 whose objective was to study the circadian system of a mammal during space flight. The thermoregulatory behavior of the Perognathus longimembris, or little pocket mouse, was studied under conditions of constant dark and constant temperature in the prolonged weightless environment of Skylab. The following specific questions were studied: (1) the effects of weightlessness on circadian periodicity in the little pocket mouse; (2) stability of the free-running circadian period of body temperature of the little pocket mouse exposed to simulated launch stress; and (3) characteristics of the circadian rhythm of body temperature in the little pocket mouse. Diagrams of the electronic circuitry and hardware used in the experiment are shown and results are given in both graphical and tabular form. The methods used in the experiment are fully documented, along with conclusions and recommendations for future research.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-137523
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  • 73
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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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  • 74
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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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  • 75
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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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  • 76
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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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  • 77
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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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  • 78
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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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  • 79
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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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  • 80
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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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  • 81
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    A description of model 3B of the multipurpose ventricular actuating system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The multipurpose ventricular actuating system is a pneumatic signal generating device that provides controlled driving pressures for actuating pulsatile blood pumps. Overall system capabilities, the timing circuitry, and calibration instruction are included.
    Keywords: BIOTECHNOLOGY
    Type: NASA-TM-X-71570 , E-8009
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  • 82
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    Fabrication of neurophysiological monitoring systems (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A system designed to collect electroencephalographic, electro-oculographic, electromyographic, and head motion data is described. The portable instrumentation provides a rapid and simple means by which neurophysiological data can be obtained by the patient in his home and the taped data returned to the laboratory for analysis. The system was designed primarily for the study of sleep.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-2416
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  • 83
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    Manipulator system man-machine interface evaluation program (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Application and requirements for remote manipulator systems for future space missions were investigated. A manipulator evaluation program was established to study the effects of various systems parameters on operator performance of tasks necessary for remotely manned missions. The program and laboratory facilities are described. Evaluation criteria and philosophy are discussed.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-120218 , H-4-3
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  • 84
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    Ride quality evaluation 1: Questionnaire studies of airline passenger comfort (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: As part of a larger effort to assess passenger comfort in aircraft, two questionnaires were administered: one to ground-based respondents; the other to passengers in flight. Respondents indicated the importance of various factors influencing their satisfaction with a trip, the perceived importance of various physical factors in determining their level of comfort, and the ease of time spent performing activities in flight. The in-flight sample also provided a rating of their level of comfort and of their willingness to fly again. Comfort ratings were examined in relation to (1) type of respondent, (2) type of aircraft, (3) characteristics of the passengers, (4) ease of performing activities, and (5) willingness to fly again.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-139368 , MEMO-403214
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  • 85
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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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  • 86
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    Laboratory demonstration model: Active cleaning technique device (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The technique which utilizes exposure to a plasma to remove contaminants from a surface was incorporated into a laboratory model which demonstrates active cleaning by both plasma cleaning and ion sputtering modes of operation. The development phase is reported and includes discussion of the plasma tube configuration, device design, and performance tests. A general description of the active cleaning device is provided which includes information on the main power/plasma discharge sensors, and the power, gas supply, and ion accelerator systems. Development of the active cleaning species at high vacuum conditions is described and results indicate that plasma cleaning occurs in the region of a visible plume which extends from the end of the plasma tube. Recommendations are made for research to determine the plasma cleaning mechanism and the plasma species responsible for the cleaning, as well limitations on the type of contaminants that can be removed.
    Keywords: BIOTECHNOLOGY
    Type: NASA-CR-120292 , D180-18031-1
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  • 87
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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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  • 88
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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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  • 89
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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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  • 90
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    Prediction of pressure and flow transients in a gaseous bipropellant reaction control rocket engine (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: An analytic model is developed to predict pressure and flow transients in a gaseous hydrogen-oxygen reaction control rocket engine feed system. The one-dimensional equations of momentum and continuity are reduced by the method of characteristics from partial derivatives to a set of total derivatives which describe the state properties along the feedline. System components, e.g., valves, manifolds, and injectors are represented by pseudo steady-state relations at discrete junctions in the system. Solutions were effected by a FORTRAN IV program on an IBM 360/65. The results indicate the relative effect of manifold volume, combustion lag time, feedline pressure fluctuations, propellant temperature, and feedline length on the chamber pressure transient. The analytical combustion model is verified by good correlation between predicted and observed chamber pressure transients. The developed model enables a rocket designer to vary the design parameters analytically to obtain stable combustion for a particular mode of operation which is prescribed by mission objectives.
    Keywords: PROPULSION SYSTEMS
    Type: Computers and Fluids; 2; Aug. 197
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  • 91
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    Clinical applications of angiocardiography (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Several tables are presented giving left ventricular (LV) data for normal patients and patients with heart disease of varied etiologies, pointing out the salient features. Graphs showing LV pressure-volume relationships (compliance) are presented and discussed. The method developed by Rackley et al. (1964) for determining left ventricular mass in man is described, and limitations to the method are discussed. Some clinical methods for determining LV oxygen consumption are briefly described, and the relation of various abnormalities of ventricular performance to coronary artery disease and ischemic heart disease is characterized.
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  • 92
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    Energy exchanges of swimming man (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Three male swimmers underwent 10-min resting and 20-min swimming (breaststroke) exposures in a swimming flume. Water temperatures in separate exposures were 18, 26, and 33 C. At each water temperature the subjects rested and swam at water velocities of 0.50, 0.75, and 0.95 m/sec, which were designed to produce around 40, 70, and 100% of maximal aerobic power. Measurements were made of esophageal temperature, four skin temperatures, water temperature, heat flow from five local skin surfaces (Hatfield-Turner disks), and oxygen uptake. Calculations were made of mean area-weighted skin temperature and heat flow, metabolic rate, and heat storage. Internal body temperature changes after 20 min of swimming were related to water temperature, swimming intensity, and body composition.
    Keywords: BIOTECHNOLOGY
    Type: Journal of Applied Physiology; 36; Apr. 197
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  • 93
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    Effects of hypercapnia and bedrest on psychomotor performance (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Two weeks of continuous exposure to simulated weightlessness (bedrest) and/or an elevated (30 torr) CO2 environment had no detrimental effect on complex tracking performance, eye-hand coordination, or problem-solving ability. These results were consistent with previously reported behavioral findings which investigated these two factors only as independent stressors.
    Keywords: BIOTECHNOLOGY
    Type: AD-778501 , SAM-TR-73-338 , Aerospace Medicine; 45; Apr. 197
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  • 94
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    NaK-nitrogen liquid metal MHD converter tests at 30 kw (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of electrical power generation with an ambient temperature liquid-metal MHD separator cycle is demonstrated by tests in which a NaK-nitrogen LM-MHD converter was operated at nozzle inlet pressures ranging from 100 to 165 N/sq cm, NaK flow rates from 46 to 72 kg/sec, and nitrogen flow rates from 2.4 to 3.8 kg/sec. The generator was operated as an eight-phase linear induction generator, with two of the eight phases providing magnetic field compensation to minimized electrical end losses at the generator channel inlet and exit.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Journal; 12; Jan. 197
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  • 95
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    A study of the durability of beryllium rocket engines (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N74-35204.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-140309 , R-9557-1
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  • 96
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    A study of the durability of beryllium rocket engines (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental test program was performed to demonstrate the durability of a beryllium INTEREGEN rocket engine when operating under conditions simulating the space shuttle reaction control system. A vibration simulator was exposed to the equivalent of 100 missions of X, Y, and Z axes random vibration to demonstrate the integrity of the recently developed injector-to-chamber braze joint. An off-limits engine was hot fired under extreme conditions of mixture ratio, chamber pressure, and orifice plugging. A durability engine was exposed to six environmental cycles interspersed with hot-fire tests without intermediate cleaning, service, or maintenance. Results from this program indicate the ability of the beryllium INTEREGEN engine concept to meet the operational requirements of the space shuttle reaction control system.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-140308 , R-9557
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  • 97
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    Effect of inlet ingestion of a wing tip vortex on turbojet stall margin (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A two-dimensional inlet and a turbojet engine were investigated in a Mach 0.4 stream so as to ingest the tip vortex of a forward mounted wing. Results show that ingestion of a wing tip vortex by a turbojet engine can cause a large reduction in engine stall margin. The loss in stall compressor pressure ratio was primarily dependent on vortex location and rotational direction and not on total-pressure variations across the compressor face.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71610 , E-8091
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  • 98
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    Cold-flow performance of several variations of a ram-air-cooled plug nozzle for supersonic-cruise aircraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental data were obtained with a 21.59 cm (8.5 in.) diameter cold-flow model in a static altitude facility to determine the thrust and pumping characteristics of several variations of a ram-air-cooled plug nozzle. Tests were conducted over a range of nozzle pressure ratios simulating supersonic cruise and takeoff conditions. Primary throat area was also varied to simulate afterburner on and off. Effect of plug size, outer shroud length, primary nozzle geometry, and varying amounts of secondary flow were investigated. At a supersonic cruise pressure ratio of 27, nozzle efficiencies were 99.7 percent for the best configurations.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3110 , E-7975
    Format: application/pdf
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  • 99
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    Solar array technology evaluation program for SEPS (Solar Electrical Propulsion Stage) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An evaluation of the technology and the development of a preliminary design for a 25 kilowatt solar array system for solar electric propulsion are discussed. The solar array has a power to weight ratio of 65 watts per kilogram. The solar array system is composed of two wings. Each wing consists of a solar array blanket, a blanket launch storage container, an extension/retraction mast assembly, a blanket tensioning system, an array electrical harness, and hardware for supporting the system for launch and in the operating position. The technology evaluation was performed to assess the applicable solar array state-of-the-art and to define supporting research necessary to achieve technology readiness for meeting the solar electric propulsion system solar array design requirements.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-120483 , LMSC-D384250
    Format: application/pdf
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  • 100
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    On the inlet vortex system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The flow field of a jet engine with an inlet vortex, which can pick up heavy debris from the ground and damage the engine, was simulated in a small water tunnel by means of the hydrogen bubble technique. It was found that the known engine inlet vortex is accompained by a vortex system, consisting of two inlet vortices (the ground based and the trailing one), secondary vortices, and ground vortices. Simulation of the ground effect by an inlet image proved that the inlet vortex feeds on free stream vorticity and can exist without the presence of a ground boundary layer. The structural form of the inlet vortex system was explained by a simple potential flow model, which showed the number, location, and the importance of the stagnation points. A retractable horizontal screen or an up-tilt of the engine is suggested as countermeasure against debris ingestion.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-140182
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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