Nimbus HRIR equipment diagnostic test program
Computer program for checking and maintaining high resolution infrared equipment in Nimbus digitizing system
COMPUTER PROGRAM↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Integration of automatic calibration system for vehicle instrumentation Final report
Automatic Calibration Technique /ACT/ for active and passive checkout of remote systems
SPACECRAFT INSTRUMENTATION↗
Environmental Testing of Satellite-borne Instruments
Environmental testing by Argo D-4 high altitude rocket used in fixed-frequency topside sounding to simulate conditions encountered by satellite-borne instruments
ENVIRONMENTAL TESTING↗
The NASA biosatellite program.
NASA biosatellite program, describing missions, experiments, instrumentation and spacecraft systems
Hall, B. B.↗
Spacecraft thermal vacuum testing
An approach for developing a general thermal vacuum test program philosophy is discussed. Guidelines are established that will assist the project engineer in relating the risk associated with flying any spacecraft to its test program. Computerized techniques can be used to help ascertain these guidelines, which relate the risk to the level of test (component, subsystem, etc), as well as to the type of test (development, qualification, etc). The interrelationship between the test program and the analytical effort is also discussed. The Skylab Apollo telescope mount general thermal vacuum test program, including test schedules, instrumentation, and test results is also discussed.
Elam, B. F.↗
Experimental investigation of combustor effects on rocket thrust chamber performance
A design and experimental program to develop special instrumentation systems, design engine hardware, and conduct tests using LOX/GH2 propellants in which the propellant flow stratification was controlled is described. The mixture ratio was varied from 4.6 to 6 overall. The mixture ratios in the core and outer zone were varied from 3.5 to 6 and 5 to 8, respectively. The range in boundary layer coolant was from 0 to 10 percent of the fuel. The nominal chamber pressure and thrust were 225 psia and 7000 pounds, respectively. Pressure and heat flux profiles as well as gas sampling of the exhaust products were obtained. Specific impulse efficiencies of approximately 94 percent and characteristic velocity efficiencies of approximately 97 percent were obtained during the experiments.
Source record↗
Detection of non-protein amino acids in the presence of protein amino acids. II.
Studies conducted with the JEOL 5AH amino acid analyzer are described. This instrument makes possible the programming of the chromatographic process. Data are presented showing the separations of seventeen non-protein amino acids in the presence of eighteen protein amino acids. It is pointed out that distinct separations could be obtained in the case of a number of chemically similar compounds, such as ornithine and lysine, N-amidino alanine and arginine, and iminodiacetic acid and S-carboxymethyl cysteine and aspartic acid.
Shapshak, P.↗
Use of Skylab EREP data in a sea surface temperature experiment
The author has identified the following significant results. This report discusses an experiment to be performed on each of the three manned Skylab missions, the results of which will assess the ability of spaceborne infrared multispectral sensing to function as a means of providing improved estimates of sea surface temperature over that obtainable with a single channel radiometric instrument. The overall investigative program is outlined, the effort performed during the prelaunch phase is detailed, and pertinent results are presented.
Anding, D. C.↗
The 1973 report and recommendations of the NASA Science Advisory Committee on Comets and Asteroids
The present day knowledge is reported of comets and asteroids and recommendations for a development program needed to provide instruments to achieve certain scientific objectives are also presented. Discussions include reports on the primary experiments and instruments, the instruments of potential applicability, mission classes and parameters, mission opportunities, and vehicular technology. An annotated bibliography and recommendations for flight projects, propulsion systems, and experiment development are included.
Atkins, K.↗
Addendum report to atmospheric science facility pallet-only mode space transportation system payload feasibility study, volume 3, revision A
The feasibility of accomplishing selected atmospheric science mission using a pallet-only mode was studied. Certain unresolved issues were identified. The first issue was that of assuring that the on-board computer facility was adequate to process scientific data, control subsystems such as instrument pointing, provide mission operational program capability, and accomplish display and control. The second issue evolved from an investigation of the availability of existing substitute instruments that could be used instead of the prime instrumentation where the development tests and schedules are incompatible with the realistic budgets and shuttle vehicle schedules. Some effort was expended on identifying candidate substitute instruments, and the performance, cost, and development schedule trade-offs found during that effort were significant enough to warrant a follow-on investigation. This addendum documents the results of that follow-on effort, as it applies to the Atmospheric Sciences Facility.
Source record↗
National geodetic satellite program, part 1
Equipment and techniques were evaluated operationally, by the Department of Defense, during the National Geodetic Satellite Program (NGSP). The theory, instrumentation, and data reduction methods used are described. Results obtained during the NGSP are given.
Anderle, R.↗
Use of sensitivity analysis to predict pilot performance as a function of different displays
A technique for objectively evaluating different displays by sensitivity analysis is described. First, the mathematical model used to analyze static displays is developed. The technique is based on formulating functional relationships between the state variables and the variables observable in the display. The matrix of the partial derivatives of the display variables with respect to the state variables, together with the observer's acuity function, is used to calculate expected errors in the state vector estimation. The technique is expanded by the use of Kalman filtering to process a time series of observation vectors. This provides a tool for analyzing displays of dynamic processes by means of a dynamic display evaluation computer program. Results are reported using this program to simulate an Instrument Landing System approach.
Mout, M. L.↗
Preliminary design package for solar heating and hot water system
Two prototype solar heating and hot water systems for use in single-family dwellings or commercial buildings were designed. Subsystems included are: collector, storage, transport, hot water, auxiliary energy, and government-furnished site data acquisition. The systems are designed for Yosemite, California, and Pueblo, Colorado. The necessary information to evaluate the preliminary design for these solar heating and hot water systems is presented. Included are a proposed instrumentation plan, a training program, hazard analysis, preliminary design drawings, and other information about the design of the system.
Source record↗
Definition study for variable cycle engine testbed engine and associated test program
The product/study double bypass variable cycle engine (VCE) was updated to incorporate recent improvements. The effect of these improvements on mission range and noise levels was determined. This engine design was then compared with current existing high-technology core engines in order to define a subscale testbed configuration that simulated many of the critical technology features of the product/study VCE. Detailed preliminary program plans were then developed for the design, fabrication, and static test of the selected testbed engine configuration. These plans included estimated costs and schedules for the detail design, fabrication and test of the testbed engine and the definition of a test program, test plan, schedule, instrumentation, and test stand requirements.
Vdoviak, J. W.↗
A portable hypergolic oxidizer vapor sensor for NASA's Space Shuttle program
The design and performance characteristics of an electrochemical NO2 sensor selected by NASA for the space shuttle program is described. The instrument consists of a sample pump, an electrochemical cell, and control and display electronics. The pump pushes the sample through the electrochemical cell where the vapors are analyzed and an output proportional to the NO2 concentration is produced. The output is displayed on a panel meter, and is also available at a recorder jack. The electrochemical cell is made up of a polypropylene chamber covered with teflon membrane faceplates. Plantinum electrodes are bonded to the faceplates, and the sensing and counter electrodes are potentiostatically controlled at -200 mV with respect to the reference electrode. The cell is filled with electrolyte, consisting of 13.5 cc of 23% solution of KOH.
Helms, W. R.↗
Preliminary flight and wind tunnel comparisons of the inlet/airframe interaction of the F-15 airplane
Preliminary flight and wind tunnel comparison data are presented for the F-15 inlet/airframe interactions program. Test conditions and instrumentation for both the model and the aircraft are described. Flight and wind tunnel inlet drag data (for a 0-deg angle of attack and Mach numbers of 0.6, 0.9, and 1.2), derived by using nearly identical pressure integration equations, are compared. The effects of a movable cowl, movable ramps, and other system components on pressure flow fields along the airframe are discussed. Excellent agreement between wind tunnel and flight pressure-integrated drags is found at all three Mach numbers. The wind tunnel data show good agreement for pressure-integrated and force-balance-measured inlet drag, except at Mach 0.6. Flight-measured pressure-integrated inlet lift is lower than that measured in the wind tunnel.
Webb, L. D.↗
The search and rescue satellite mission - A basis for international cooperation
The use of geostationary and polar-orbiting satellites to monitor and locate signals of the Emergency Locator Transmitter (ELT) and Emergency Position Indicating Radio Beacon (EPIB) of general aviation aircraft and inspected marine vessels respectively is described. The joint U.S. Canada/France SARSAT demonstration program will require a minimum of four minutes of mutual visibility of distress transmitter, local user terminal and satellite to obtain a location by Doppler tracking. The program consisting of placing instrumentation on-board three of the Tiros-N series of NOAA operational satellites is attracting interest also from other countries including the USSR, Norway, Australia, and Japan.
Redisch, W. N.↗
Dynamics Explorer launch
Simultaneously launched from the WSMC, two satellites are to be placed into polar, copolar orbit in order to acquire data on the coupling phenomena between Earth's lower thermosphere and the magnetosphere, as part of the Solar-Terrestrial Program. The mission sequence, instruments, and science data processing system are described as well as the characteristics of the Delta 3913 launch vehicle, and payload separation staging.
Source record↗