Influence of vestibular stimulation and display luminance on the performance of a compensatory tracking task
Vestibular nystagmus and display luminance effects on hand-eye coordination in compensatory tracking of aircraft instrument
Benson, A. J.↗
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Results for “tasks”
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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OSSA's R and D tasks toward seventies stress satellites for serving man
Ossa R and D program noting budget allocations, satellite programs and international projects
Naugle, J. E.↗
Biowaste resistojet propellant system, biological and functional analysis, task 1 and 2
The influence of chemical contaminants in potential biowaste sources upon the design and interface requirements of a biowaste resistojet propulsion system for a space station and/or base are evaluated. Chemical contaminants are defined as all compounds present in biowaste other than carbon dioxide, water, and methane. The latter are the nominal effluent candidates for the biowaste resistojet.
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Remote detection of trailing vortices, task 3, modification 3
The operation of a frequency tracker for use with the laser Doppler velocimeter (LDV) is reported. Topics discussed include: laser beam profile, lens matching, and LDV resolution data. It is concluded that the LDV provides good ground wind signals. The loss in sensitivity of the cavity system at high frequencies is partly compensated by an increase in the scattering cross section of the atmosphere due to dust.
Fridman, J.↗
Experiment module concepts study. Volume 5 book 1, appendix A: Shuttle only task
Results of a preliminary investigation of the effect on the candidate experiment program implementation of experiment module operations in the absence of an orbiting space station and with the availability of the space shuttle orbiter vehicle only are presented. The fundamental hardware elements for shuttle-only operation of the program are: (1) integrated common experiment modules CM-1, CM-3, and CM-4, together with the propulsion slice; (2) support modules capable of supplying on-orbit crew life support, power, data management, and other services normally provided by a space station; (3) dormancy kits to enable normally attached modules to remain in orbit while shuttle returns to earth; and (4) shuttle orbiter. Preliminary cost estimates for 30 day on-orbit and 5 day on-orbit capabilities for a four year implementation period are $4.2 billion and $2.1 billion, respectively.
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The Varestraint test for refractory metals, task 2
The principles of the Varestraint test were applied to the evaluation of refractory metal alloys. This required development of a special test apparatus employing a modest specimen size for improved economy and compatible with the high purity inert atmosphere required for welding these alloys. Minimum specimen size is desirable because of the high cost of these alloys and also to permit timely testing of limited production developmental alloys. The Varestraint apparatus satisfies these requirements by providing a timely and economic test for hot crack sensitivity. This test can be used both for alloy development and production surveillance. The test apparatus was designed for use in vacuum purged dry boxes and is completely compatible with high purity inert atmosphere. Augmented strain can be varied continuously from 1/4% thru 4%. In addition to varying the augmented strain, the primary Varestraint variable, the effect on hot cracking of varying other weld parameters such as unit weld length heat input have also been studied. Test reproducibility, in terms of bending or strain rate, was demonstrated using high speed photography.
Lessmann, G. G.↗
A modular approach for assessing the effect of radiation environments on man in operational systems. The radiobiological vulnerability of man during task performance
A modular approach for assessing the affects of radiation environments on man in operational systems has been developed. The feasibility of the model has been proved and the practicality has been assessed. It has been applied to one operational system to date and information obtained has been submitted to systems analysts and mission planners for the assessment of man's vulnerability and impact on systems survivability. In addition, the model has been developed so that the radiobiological data can be input to a sophisticated man-machine interface model to properly relate the radiobiological stress with other mission stresses including the effects of a degraded system.
Ewing, D. E.↗
Task 1, Design Analysis Report: Pulsed plasma solid propellant microthruster for the synchronous meteorological satellite
Thermal vacuum design supporting thruster tests indicate no problems under the worst case conditions of sink temperature and spin rate. The reliability of the system was calculated to be 0.92 for a five-year mission. Minus the main energy storage capacitor it is 0.98.
Guman, W. J.↗
Monopropellant hydrazine resistojet preliminary design task
The design effort for the electrothermal hydrazine thruster (ETH) is summarized. The EHT decomposes hydrazine thermally and expands the decomposition products through a nozzle to provide the impulse necessary to fulfill spacecraft propulsive requirements. The thruster is capable of operation at pulse widths from 0.050 second to steady state and delivers specific impulse values from 175 to greater than 225 seconds, depending upon the duty cycle. The design of the EHT is the result of an analytical effort combined with a series of design verification tests. The design requirements, design philosophy and detailed design methods are outlined. A discussion of the rationale behind the selection of materials for the EHT is included. The results of the design verification tests are also presented.
Murch, C. K.↗
A study of pilot modeling in multi-controller tasks
A modeling approach, which utilizes a matrix of transfer functions to describe the human pilot in multiple input, multiple output control situations, is studied. The approach used was to extend a well established scalar Wiener-Hopf minimization technique to the matrix case and then study, via a series of experiments, the data requirements when only finite record lengths are available. One of these experiments was a two-controller roll tracking experiment designed to force the pilot to use rudder in order to coordinate and reduce the effects of aileron yaw. One model was computed for the case where the signals used to generate the spectral matrix are error and bank angle while another model was computed for the case where error and yaw angle are the inputs. Several anomalies were observed to be present in the experimental data. These are defined by the descriptive terms roll up, break up, and roll down. Due to these algorithm induced anomalies, the frequency band over which reliable estimates of power spectra can be achieved is considerably less than predicted by the sampling theorem.
Whitbeck, R. F.↗
Evaluation of range and distortion tolerance for high Mach number transonic fan stages. Task 2: Performance of a 1500-foot-per-second tip speed transonic fan stage with variable geometry inlet guide vanes and stator
A 0.5 hub/tip radius ratio compressor stage consisting of a 1500 ft/sec tip speed rotor, a variable camber inlet guide vane and a variable stagger stator was designed and tested with undistorted inlet flow, flow with tip radial distortion, and flow with 90 degrees, one-per-rev, circumferential distortion. At the design speed and design IGV and stator setting the design stage pressure ratio was achieved at a weight within 1% of the design flow. Analytical results on rotor tip shock structure, deviation angle and part-span shroud losses at different operating conditions are presented. The variable geometry blading enabled efficient operation with adequate stall margin at the design condition and at 70% speed. Closing the inlet guide vanes to 40 degrees changed the speed-versus-weight flow relationship along the stall line and thus provided the flexibility of operation at off-design conditions. Inlet flow distortion caused considerable losses in peak efficiency, efficiency on a constant throttle line through design pressure ratio at design speed, stall pressure ratio, and stall margin at the 0 degrees IGV setting and high rotative speeds. The use of the 40 degrees inlet guide vane setting enabled partial recovery of the stall margin over the standard constant throttle line.
Bilwakesh, K. R.↗
Development of flight experiment task requirements. Volume 1: Summary
A study was conducted to develop the means to identify skills required of scientist passengers on advanced missions related to the space shuttle and RAM programs. The scope of the study was defined to include only the activities of on-orbit personnel which are directly related to, or required by, on-orbit experimentation and scientific investigations conducted on or supported by the shuttle orbiter. A program summary is presented which provides a description of the methodology developed, an overview of the activities performed during the study, and the results obtained through application of the methodology.
Hatterick, G. R.↗
Biowaste resistojet propellant system biological and functional analysis, task 3
Exhaust flow contamination aspects of the biowaste resistojet are studied by evaluating effects of operating pressure, temperature and composition. Biowaste propellant mixtures considered are comprised of: (1) The Sabatier reactor effluent; (2) the effluent of the cabin carbon dioxide molecular sieve; and (3) water and water vapor from various sources. Results show that plume shapes of resistojet thrusters in the 25 to 100 mlb range exhibit greater apex angles for a given density contour than a scaled inviscid jet. Operation at low thrust, low pressure and high temperature accentuates this pluming due to viscous effects in the nozzle flow. Since the biowaste resistojet effluent is traveling at high velocity in the plume away from the aircraft it is found to be a superior method of damping than the ambient venting.
Source record↗
Microfog lubricant application system for advanced turbine engine components, phase 2. Tasks 3, 4 and 5: Wettability and heat transfer of microfog jets impinging on a heated rotating disc, and evaluation of reclassifying nozzles and a vortex mist generator
The wettabilities and heat transfer rates of microfog jets (oil-mist nozzle flows) impinging on a heated rotating disc were determined under an inert atmosphere of nitrogen at temperatures ranging from 600 to 800 F. The results are discussed in relation to the various factors involved in the microfog lubricant application systems. Two novel reclassifying nozzles and a vortex mist generator were also studied.
Shim, J.↗
Orbital Astronomy Support Facility (OASF) study. Volume 3: Task B, instruments for orbital astronomy, book 1
Explore the source record for details and available documents.
Wechsler, J. W.↗
Kansas environmental and resource study: A Great Plains model, tasks 1-6
There are no author identified significant results in this report. Environmental and resources investigations in Kansas utilizing ERTS-1 imagery are summarized for the following areas: (1) use of feature extraction techniqued for texture context information in ERTS imagery; (2) interpretation and automatic image enhancement; (3) water use, production, and disease detection and predictions for wheat; (4) ERTS-1 agricultural statistics; (5) monitoring fresh water resources; and (6) ground pattern analysis in the Great Plains.
Haralick, R. M.↗
Use of ERTS imagery in air pollution and marine biology studies, tasks 1 through 3
There are no author-identified significant results in this report. The general suitability of ERTS imagery in detecting ground originated air pollution has proved to be excellent. The quality and resolution exceeded expectations and has permitted in some instances location of point sources to within a thousand feet. Suitable techniques have not yet been developed for determining or measuring area and line sources of air pollution. A major problem has been cloud cover that has persisted over the area of primary interest, the Chesapeake Bay. Work has been completed on mounting the shipboard transmissometer which will be used for investigations to relate the chlorophyll and suspended sediment content in the waters of the Lower Chesapeake Bay to ERTS-1 imagery. Water sampling, plankton analysis, and preparations for sea collection of water truth along the eastern continental shelf of the U.S. have been completed for use in comparisons with ERTS-1 data.
Copeland, G. E.↗
Pulsed plasma solid propellant microthruster for the synchronous meteorological satellite. Task 4: Engineering model fabrication and test report
Two flight prototype solid propellant pulsed plasma microthruster propulsion systems for the SMS satellite were fabricated, assembled and tested. The propulsion system is a completely self contained system requiring only three electrical inputs to operate: a 29.4 volt power source, a 28 volt enable signal and a 50 millsec long command fire signal that can be applied at any rate from 50 ppm to 110 ppm. The thrust level can be varied over a range 2.2 to 1 at constant impulse bit amplitude. By controlling the duration of the 28 volt enable either steady state thrust or a series of discrete impulse bits can be generated. A new technique of capacitor charging was implemented to reduce high voltage stress on energy storage capacitors.
Guman, W. J.↗