Neurophysiological and Behavioral Studies of Chimpanzees Semiannual Report, 1 Jul. - 31 Dec. 1966
Computer program for control of chimpanzee discrimination test analysis and electroencephalographic response data
COMPUTER PROGRAM↗
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Results for “Test and analysis”
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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Day-night high resolution infrared radiometer employing two-stage radiant cooling. Part 1 - Two-stage radiant cooler Final report
Design, thermal analysis, testing, and breadboard integration of two-stage radiant cooler for high resolution radiometer
Annable, R. V.↗
The Apollo structural damping study - Determination of modal damping for launch vehicles using experimental data Final technical report
Dynamic test analysis on modal damping forces of Saturn 5 Apollo vehicle
Reed, R. R.↗
Post test inspection of three Brayton rotating units
Post test analysis of closed Brayton cycle space electric power conversion system for space
Dunn, J. H.↗
Motivational Correlations of Strategy Choices in the Prisoner's Dilemma Game
The purpose of the present study was to investigate the relationship between the motivational dimensions assessed by the Motivation Analysis Test and prisoner's dilemma game behavior as measured both by the number of competitive strategy choices and the two-stage stochastic variables labelled trustworthiness, forgiveness, repentance, and trust by Rapoport.
Williams, Carl D.↗
Gas-powered reentry body erection mechanism
The design, analysis, testing, and flight of the supersonic planetary entry decelerator 2 spacecraft are described. The vehicle was launched in a folded condition and deployed to its required configuration following exit from the atmosphere. This concept was selected primarily because it allows utilization of existing launch vehicle systems in the most economical manner possible.
Muraca, R. J.↗
Atmospheric Flight Mechanics Conference, 2nd, Palo Alto and Moffett Field, Calif., September 11-13, 1972, Informal Papers.
Limitations in the acquisition of nonlinear aerodynamic coefficients from free-oscillation data by means of the Chapman-Kirk technique, SAM-D control test vehicle trajectory plannning and flight test analysis, and determination of aerodynamic drag from radar data are among the topics covered in papers concerned with atmospheric flight mechanics. Other areas covered include fixed and rotary-wing aircraft, ordnance and reentry vehicles, and analysis and measurement techniques. Individual items are announced in this issue.
Source record↗
Flight test data for a Cessna Cardinal
The results of a flight test analysis of the performance of a standard Cessna 177B Cardinal airplane are presented. The airplane was fully instrumented to obtain steady state performance, stick-fixed dynamic stability characteristics, and roll response data. Results obtained include graphs of C sub L versus alpha, C sub D versus C sub L, and speed-power relationships. Dynamic data include Phugoid and Dutch characteristics, and roll response characteristics.
Kohlman, D. L.↗
In-line task 57: Component evaluation
Design analysis tests were performed on selected power switching components to determine the possible applicability of off-the-shelf hardware to space shuttles. Various characteristics were also evaluated in those devices to determine the most desirable properties for the space shuttle.
Boykin, J. C.↗
Shuttle filter study. Volume 2: Contaminant generation and sensitivity studies
Contaminant generation studies were conducted at the component level using two different methods, radioactive tracer technique and gravimetric analysis test procedure. Both of these were reduced to practice during this program. In the first of these methods, radioactively tagged components typical of those used in spacecraft were studied to determine their contaminant generation characteristics under simulated operating conditions. Because the purpose of the work was: (1) to determine the types and quantities of contaminants generated; and (2) to evaluate improved monitoring and detection schemes, no attempt was made to evaluate or qualify specific components. The components used in this test program were therefore not flight hardware items. Some of them had been used in previous tests; some were obsolete; one was an experimental device. In addition to the component tests, various materials of interest to contaminant and filtration studies were irradiated and evaluated for use as autotracer materials. These included test dusts, plastics, valve seat materials, and bearing cage materials.
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Airborne Visible Laser Optical Communications (AVLOC) experiment
A series of optical communication experiments between a high altitude aircraft at 18.3 km (60,000 ft) and a ground station were conducted by NASA from summer 1972 through winter 1973. The basic system was an optical tracker and transmitter located in each terminal. The aircraft transceiver consisted of a 5-mW HeNe laser transmitter with a 30-megabit modulator. The ground station beacon was an argon laser operating at 488 nm. A separate pulsed laser radar was used for initial acquisition. The objective of the experiment was to obtain engineering data on the precision tracking and communication system performance at both terminals. Atmospheric effects on the system performance was also an experiment objective. The system description, engineering analysis, testing, and flight results are discussed.
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The synergistic effects of slip ring-brush design and materials
The design, fabrication, and subsequent testing of four power slip rings for synchronous orbit application are described. The synergistic effects of contact materials and slip ring-brush design are studied by means of frequent and simultaneous recording of friction, wear, and electrical noise. Data generated during the test period are presented along with post test analysis data.
Lewis, N. E.↗
Thrust vector control by liquid injection for solid propellant rockets
In liquid injection thrust vector control, a rocket jet is deflected for steering purposed by injecting a liquid into the nozzle exit cone. The liquid is preferably both dense and reactive so that it adds mass and energy and generates shocks in the supersonic exhaust. This behavior increases thrust in the affected part of the jet producing not only a side force for steering but an addition to axial thrust. This paper presents a summary of current liquid injection thrust vector control technology, including procedures for design, development, analysis, testing and evaluation, together with supporting data and references.
Zeamer, R. J.↗
Viking 1975 orbiter development test model/Lander dynamic test model, dynamic environmental testing
A series of dynamic environmental tests on the Viking 1975 Orbiter/Lander model provided information regarding damping and linearity. The quality of mode isolation was made with orthogonality checks. A pretest criterion established for orthogonality provided good correlation with test results. Part of the post-test analysis was dedicated to a review of instrumentation selection for control and/or response limiting. Limited load values were also examined.
Milder, G.↗
The 1976 Goddard Space Flight Center Battery Workshop
The latest results of testing, analysis and development of sealed nickel cadmium cells and batteries and developments in the nickel-hydrogen system are discussed.
Source record↗
Fabrication and verification testing of ETM 30 cm diameter ion thrusters
Engineering model designs and acceptance tests are described for the 800 and 900 series 30 cm electron bombardment thrustors. Modifications to the test console for a 1000 hr verification test were made. The 10,000 hr endurance test of the S/N 701 thruster is described, and post test analysis results are included.
Collett, C.↗
Orbiter Thermal Protection System Development
The development of the Space Shuttle Orbiter Thermal Protection System (TPS) is traced from concept definition, through technical development, to final design and qualification for manned flight. A sufficiently detailed description of the TPS design is presented to support an indepth discussion of the key issues encountered in conceptual design, materials development, and structural integration. Emphasis is placed on the unique combination of requirements which resulted in the use not only of revolutionary design concepts and materials, but also of unique design criteria, newly developed analysis, testing and manufacturing methods, and finally of an unconventional approach to system certification for operational flight. The conclusion is drawn that a significant advance in all areas of thermal protection system development has been achieved which results in a highly efficient, flexible, and cost-effective thermal protection system for the Orbiter of the Space Shuttle System.
Greenshields, D. H.↗
Dynamic test techniques - Concepts and practices
An initial investigation of dynamic flight test analysis techniques indicated that a strict, comprehensive force-moment accounting system would be necessary. An implementation of the longitudinal force-moment accounting system provided excellent results in accounting for small lift/drag and tail deflection changes. Attention is given to gross thrust calculation, instrumentation, maneuvers, and aspects of data correlation. The results of the studies demonstrate that it is possible to generate a lift/drag model which is capable of predicting performance from nearly any maneuver.
Rawlings, K., III↗