Some effects of radar antenna position on LM descent performance
Hybrid simulation study in comparing lunar module descent performance for three altitudes as function of guidance radar antenna position
Moore, T. E.↗
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Results for “simulator study”
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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Fixed-base visual simulation of obstacle avoidance during terminal descent of advanced Apollo spacecraft with an all-flexible parawing
Fixed-base visual simulation study for ability determination of onboard pilot during landing
Miller, G. K., Jr.↗
To what extent should space shuttle stability and control be provided through stability augmentation /ques/
Simulation studies to determine augmentation systems required for stability and control of space shuttles
Wawrzyniak, M. E.↗
Some alkali metal corrosion effects in a Rankine cycle test loop
Rankine cycle two loop Li boiling Ka facility for nuclear turboplant simulation, studying alkali metal corrosion for operation with and without hot traps
Phillips, W. M.↗
The supersonic transport and air traffic control
ATC and SST operations in terminal area simulation study involving airline crews and controllers in real time traffic situation
Sawyer, R. H.↗
Lunar surface engineering properties experiment definition. Volume 1 - Mechanics and stabilization of lunar soils Final report, 20 Jun. 1968 - 19 Jul. 1969
Studying simulated lunar soil for determining feasibility of proposed geotechnical tests for Apollo missions
Houston, W. N.↗
The aerodynamics of high lift illustrated by augmentor-wing research
Augmentor wing high-lift aerodynamics, discussing results of wind tunnel tests and simulation studies
Whittley, D. C.↗
Techniques for generation of control and guidance signals derived from optical fields, part 2
The development is reported of a high resolution technique for the detection and identification of landmarks from spacecraft optical fields. By making use of nonlinear regression analysis, a method is presented whereby a sequence of synthetic images produced by a digital computer can be automatically adjusted to provide a least squares approximation to a real image. The convergence of the method is demonstrated by means of a computer simulation for both elliptical and rectangular patterns. Statistical simulation studies with elliptical and rectangular patterns show that the computational techniques developed are able to at least match human pattern recognition capabilities, even in the presence of large amounts of noise. Unlike most pattern recognition techniques, this ability is unaffected by arbitrary pattern rotation, translation, and scale change. Further development of the basic approach may eventually allow a spacecraft or robot vehicle to be provided with an ability to very accurately determine its spatial relationship to arbitrary known objects within its optical field of view.
Hemami, H.↗
A shuttle and space station manipulator system for assembly, docking, maintenance cargo handling and spacecraft retrieval (preliminary design). Volume 1: Management summary
A preliminary design is established for a general purpose manipulator system which can be used interchangeably on the shuttle and station and can be transferred back and forth between them. Control of the manipulator is accomplished by hard wiring from internal control stations in the shuttle or station. A variety of shuttle and station manipulator operations are considered including servicing the Large Space Telescope; however, emphasis is placed on unloading modules from the shuttle and assembling the space station. Simulation studies on foveal stereoscopic viewing and manipulator supervisory computer control have been accomplished to investigate the feasibility of their use in the manipulator system. The basic manipulator system consists of a single 18.3 m long, 7 degree of freedom (DOF), electrically acutated main boom with an auxiliary 3 DOF electrically actuated, extendible 18.3 m maximum length, lighting, and viewing boom. A 3 DOF orientor assembly is located at the tip of the viewing boom to provide camera pan, tilt, and roll.
Source record↗
Global winds from Nimbus temperature data for July 1970
Simulation studies to determine the best techniques for making use of vertical sounding temperature data are reported. An atmospheric model was developed to accept real SIRS radiance data from Nimbus 4 for June and July 1970. The results were compared to real observations. It was found that the model accepts real temperature data on a continuing basis, and real temperature data determine winds to a useful degree of accuracy.
Hogan, J. S.↗
Induction torches and low frequency tests
Three induction-coupled plasma torches were operated at 9600 Hz to determine specific operating parameters and supply data for gas core nuclear rocket simulation studies. Two air-cooled torches, one 16 cm in diameter and one 30 cm in diameter, and a water-cooled torch 14 cm in diameter, were tested. Complete energy balances for the operating systems were obtained during operation. A series of operating points, including pressures from 30 torr to 1 atmosphere, power levels up to 343 kw, and gas flows from 1.1 to 35 g/sec, were documented. Complete operating data for approximately thirty runs are presented, along with graphs of significant operating parameters.
Poole, J. W.↗
User's manual for the Simulated Life Analysis of Vehicle Elements (SLAVE) model
The simulated life analysis of vehicle elements model was designed to perform statistical simulation studies for any constant loss rate. The outputs of the model consist of the total number of stages required, stages successfully completing their lifetime, and average stage flight life. This report contains a complete description of the model. Users' instructions and interpretation of input and output data are presented such that a user with little or no prior programming knowledge can successfully implement the program.
Paul, D. D., Jr.↗
Effect of stabilization on VTOL aircraft in hovering flight
A motion simulator study was conducted to determine the effects of roll and pitch stabilization on the handling qualities and control power requirements of VTOL aircraft during hover and short-distance maneuvering flight. Three levels of stabilization complexity were compared: (1) no stabilization, (2) rate stabilization, and (3) attitude stabilization. Control sensitivities and stabilization gains were optimized prior to comparison. Results are presented to show how the optimum systems were determined and how they compared with each other at different levels of control power. Comparisons were made both in calm air and in the presence of roll disturbances. Results indicate the attitude-stabilized system provides the best handling qualities for the least amount of control power.
Greif, R. K.↗
Recent NASA handling qualities research
A comprehensive review of NASA research results documented since the mid-1960's and some recently completed programs on aircraft handling qualities are presented. In addition to handling qualities research pertaining to vehicle stability and control characteristics, investigations related to specialized piloting tasks, cockpit displays, and environmental factors are summarized. The background leading to NASA's handling qualities research activities is discussed, and programs that have received major emphasis are indicated. For general aviation aircraft, the survey includes investigations aimed at improving handling qualities by incorporating increasingly sophisticated stability augmentation and display systems, simplifying the approach and landing task for relatively inexperienced pilots, and establishing the basic effects of turbulence. Research on the specialized piloting problem of steeper instrument approaches for noise abatement and investigations with a representative first generation aircraft are reviewed in the section on subsonic jet transports. Supersonic cruise aircraft programs include a variety of simulation studies related to supersonic transport designs and flight tests with the XB-70 aircraft. Investigations of high angle of attack loss of control problems and a flight study of direct lift control utilization for formation flying and aerial refueling are discussed in the review of tactical military aircraft research.
Wasicko, R. J.↗
The 136 MHZ/400 MHz earth station antenna-noise temperature prediction program for RAE-B
A simulation study was undertaken to determine the 136 MHz and 400 MHz noise temperature of the ground network antennas which will track the RAE-B satellite during data transmission periods. Since the noise temperature of the antenna effectively sets the signal-to-noise ratio of the received signal, a knowledge of SNR will be helpful in locating the optimum time windows for data transmission during low noise periods. Antenna noise temperatures will be predicted for selected earth-based ground stations which will support RAE-B. Telemetry data acquisition will be at 400 MHz; tracking support at 136 MHz will be provided by the Goddard Range and Range Rate (RARR) stations. The antenna-noise temperature predictions will include the effects of galactic-brightness temperature, the sun, and the brightest radio stars. Predictions will cover the ten-month period from March 1, 1973 to December 31, 1973.
Taylor, R. E.↗
Effect of pictorial display configuration on the frequency of control reversals during aircraft landing approaches
A fixed-base simulator study to determine the effect of increased pictorial display realism on the frequency of control reversals made with an inside-out landing display was conducted. Display conditions included the effects of collimation and scale (head-up versus head-down presentation), horizon symbology (simple line versus white-black sky-ground surfaces), and ground plane realism (computer generated perspective versus a TV picture of a realistic model). The number of control reversals was moderately high on all displays. Control reversals to roll disturbances occurred nearly twice as frequently as reversals to either pitch or lateral rate disturbances. Though there were no significant differences among the numbers of small control reversals for the different displays, there was some evidence that this conclusion may not apply to large control reversals.
Lincoln, R.↗
The 136 MHz/400 MHz earth station antenna-noise temperature prediction program documentation for RAE-B
A simulation study to determine the 136 MHz and 400 MHz noise temperature of the ground network antennas which will track the RAE-B satellite during data transmission periods is described. Since the noise temperature of the antenna effectively sets the signal-to-noise ratio (SNR) of the received signal, a knowledge of SNR will be helpful in locating the optimum time windows for data transmission during low-noise periods. Antenna-noise temperatures at 136 MHz and 400 MHz will be predicted for selected earth-based ground stations which will support RAE-B. The antenna-noise temperature predictions will include the effects of galactic-brightness temperature, the sun, and the brightest radio stars. Predictions will cover the ten-month period from March 1, 1973 to December 31, 1973. The RAE-B mission will be expecially susceptible to SNR degradation during the two eclipses of the Sun occurring in this period.
Chin, M.↗
A progress report on the development of an augmentor wing jet STOL research aircraft.
The development of the aircraft has progressed to the point where the design of the modifications to the de Havilland C-8A Buffalo is complete and the engines are being tested. The predicted performance shows that the aircraft will be able to take off and land in less than 1500 ft. Simulation studies indicate that the handling qualities of the aircraft, with stability augmentation, will be acceptable for STOL research missions. Special techniques were required, however, for flight path control and transition from cruise to landing configuration .
Quigley, H. C.↗