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At least 145 records · Page 8

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NASA NTRS1984

The Shuttle Mission Simulator computer generated imagery

Equipment available in the primary training facility for the Space Transportation System (STS) flight crews includes the Fixed Base Simulator, the Motion Base Simulator, the Spacelab Simulator, and the Guidance and Navigation Simulator. The Shuttle Mission Simulator (SMS) consists of the Fixed Base Simulator and the Motion Base Simulator. The SMS utilizes four visual Computer Generated Image (CGI) systems. The Motion Base Simulator has a forward crew station with six-degrees of freedom motion simulation. Operation of the Spacelab Simulator is planned for the spring of 1983. The Guidance and Navigation Simulator went into operation in 1982. Aspects of orbital visual simulation are discussed, taking into account the earth scene, payload simulation, the generation and display of 1079 stars, the simulation of sun glare, and Reaction Control System jet firing plumes. Attention is also given to landing site visual simulation, and night launch and landing simulation.

Henderson, T. H.↗

NASA NTRS1975

Redundant actuator development program

Two concepts of redundant secondary actuator mechanization, applicable to future advanced flight control systems, were studied to quantitatively assess their design applicability to an AST. The two actuator concepts, a four-channel, force summed system and a three-channel, active/standby system have been developed and evaluated through analysis, analog computer simulation, and piloted motion simulation. The quantitative comparison of the two concepts indicates that the force summed concept better meet performance requirements, although the active/standby is superior in other respects. Both concepts are viable candidates for advanced control application dependent on the specific performance requirements.

Chenoweth, C. C.↗

NASA NTRS1982

Research through simulation

The design of the computer operating system at Langley Research Center allows for concurrent support of time-critical simulations and background analytical computing on the same machine. Signal path interconnections between computing hardware and flight simulation hardware is provided to allow up to six simulation programs to be in operation at one time. Capabilities and research applications are discussed for the: (1) differential maneuvering simulator; (2) visual motion simulator; (3) terminal configured vehicle simulator; (4) general aviation aircraft simulator; (5) general purpose fixed based simulator; (6) transport simulator; (7) digital fly by wire simulator; (8) general purpose fighter simulator; and (9) the roll-up cockpit. The visual landing display system and graphics display system are described and their simulator support applications are listed.

Copeland, J. L.↗

NASA NTRS1979

Optimal washout for control of a moving base simulator

A general form of an optimal washout filter is derived using state-space linear optimal control theory, and this is applied to the design of washout filters of various types of moving base motion simulators, including the NASA's vertical motion simulator. Attention is given to the linear elements of a washout filter. One of the nonlinearities considered is braking which may be required near the end of the simulator excursion to prevent a crash. Although the general form of the optimal washout filter is applicable to time-variant system, the applications analyzed in the study are restricted to time-invariant cases.

Kurosaki, M.↗

NASA NTRS1987

Measuring pilot workload in a motion base simulator. III - Synchronous secondary task

This experiment continues earlier research of Kantowitz et al. (1983) conducted in a GAT-1 motion-base trainer to evaluate choice-reaction secondary tasks as measures of pilot work load. The earlier work used an asynchronous secondary task presented every 22 sec regardless of flying performance. The present experiment uses a synchronous task presented only when a critical event occurred on the flying task. Both two- and four-choice visual secondary tasks were investigated. Analysis of primary flying-task results showed no decrement in error for altitude, indicating that the key assumption necessary for using a choice secondary task was satisfied. Reaction times showed significant differences between 'easy' and 'hard' flight scenarios as well as the ability to discriminate among flight tasks.

Kantowitz, Barry H.↗

NASA NTRS1984

Oculometric indices of simulator and aircraft motion

The effects on eye scan behavior of both simulator and aircraft motion and sensitivity of an oculometric measure to motion effects was demonstrated. It was found that fixation time is sensitive to motion effects. Differences between simulator motion and no motion conditions during a series of simulated ILS approaches were studied. The mean fixation time for the no motion condition was found to be significantly longer than for the motion conditions. Eye scan parameters based on data collected in flight, and in fixed base simulation were investigated. Motion effects were evident when the subject was viewing a display supplying attitude and flight path information. The nature of the information provided by motion was examined. The mean fixation times for the no motion condition were significantly longer than for either motion condition, while the two motion conditions did not differ. It is shown that motion serves an alerting function, providing a cue or clue to the pilot that something happened. It is suggested that simulation without motion cues may represent an understatement of the true capacity of the pilot.

Comstock, J. R.↗

NASA NTRS1972

Initial operating experience with an aircraft simulator having extensive lateral motion

The flight simulation facility features an extensive cockpit motion system, emphasizing lateral motion for the simulation of lateral-directional control tasks. The motion capabilities of the simulator are briefly described, and the logic with which the motion drives are controlled to provide the most effective approximations of the motions of flight is discussed. Preliminary assessments of the effectiveness of these motions, in the simulation of large transport aircraft, are discussed.

Bray, R. S.↗

NASA NTRSDate not supplied

High Fidelity Aerospace Simulations at NASA Ames SimLabs

An overview of the simulation facilities at SimLabs at NASA Ames. Main focus is on the Vertical Motion Simulator or VMS, also brief descriptions of other simulators. Discussion of the history and general specifications of the VMS. Also, provide an overview of past research and training conducted on the simulators, and some future developments with a focus on AR/VR technologies.

flight simulators↗

NASA NTRS1993

Computational Control Workstation: Users' perspectives

A Workstation has been designed and constructed for rapidly simulating motions of rigid and elastic multibody systems. We examine the Workstation from the point of view of analysts who use the machine in an industrial setting. Two aspects of the device distinguish it from other simulation programs. First, one uses a series of windows and menus on a computer terminal, together with a keyboard and mouse, to provide a mathematical and geometrical description of the system under consideration. The second hallmark is a facility for animating simulation results. An assessment of the amount of effort required to numerically describe a system to the Workstation is made by comparing the process to that used with other multibody software. The apparatus for displaying results as a motion picture is critiqued as well. In an effort to establish confidence in the algorithms that derive, encode, and solve equations of motion, simulation results from the Workstation are compared to answers obtained with other multibody programs. Our study includes measurements of computational speed.

Roithmayr, Carlos M.↗

NASA NTRS1992

Does a motion base prevent simulator sickness?

The use of high-fidelity motion cues to reduce the discrepancy between visually implied motion and actual motion is tested experimentally using the NASA Vertical Motion Simulator (VMS). Ten pilot subjects use the VMS to fly simulated S-turns and sawtooths which generate a high incidence of motion sickness. The subjects fly the maneuvers on separate days both with and without use of a motion base provided by the VMS, and data are collected regarding symptoms, dark focus, and postural equilibrium. The motion-base condition is shown to be practically irrelevant with respect to the incidence and severity of motion sickness. It is suggested that the data-collection procedure cannot detect differences in sickness levels, and the false cues of the motion condition are theorized to have an adverse impact approximately equivalent to the absence of cues in a fixed-base condition.

Sharkey, Thomas J.↗

NASA NTRS2013

Boundary Avoidance Tracking for Instigating Pilot Induced Oscillations

In order to advance research in the area of pilot induced oscillations, a reliable method to create PIOs in a simulated environment is necessary. Using a boundary avoidance tracking task, researchers performing an evaluation of control systems were able to create PIO events in 42% of cases using a nominal aircraft, and 91% of cases using an aircraft with reduced actuator rate limits. The simulator evaluation took place in the NASA Ames Vertical Motion Simulator, a high-fidelity motion-based simulation facility.

pilot induced oscillation↗

NASA NTRS1985

Simulation world moves up to V/STOL

NASA-Ames' Vertical Motion Simulator (VMS) is a large motion amplitude manned simulator designed for investigation of landing, takeoff, and general handling qualities and control system development for STOL and VTOL aircraft. The VMS incorporates six degrees of freedom, a four-window computer-generated imagery (CGI) system, and interchangeable cabs. The CGI generates day and night scenes that can include moving objects on the ground and in flight. A project is now underway to upgrade the VMS for research on rotorcraft engaged in nap-of-the-earth flight missions.

Cook, A. M.↗

NASA NTRS1975

Motion-base simulator study of control of an externally blown flap STOL transport aircraft after failure of an outboard engine during landing approach

A moving-base simulator investigation of the problems of recovery and landing of a STOL aircraft after failure of an outboard engine during final approach was made. The approaches were made at 75 knots along a 6 deg glide slope. The engine was failed at low altitude and the option to go around was not allowed. The aircraft was simulated with each of three control systems, and it had four high-bypass-ratio fan-jet engines exhausting against large triple-slotted wing flaps to produce additional lift. A virtual-image out-the-window television display of a simulated STOL airport was operating during part of the investigation. Also, a simple heads-up flight director display superimposed on the airport landing scene was used by the pilots to make some of the recoveries following an engine failure. The results of the study indicated that the variation in visual cues and/or motion cues had little effect on the outcome of a recovery, but they did have some effect on the pilot's response and control patterns.

Middleton, D. B.↗

NASA NTRS2009

Pharmacokinetics of Intranasal Scopolamine Gel Formulation (Inscop)

Space Motion Sickness (SMS) is commonly experienced by astronauts and often requires treatment with medications during early flight days of space missions. Orally administered scopolamine is commonly used by astronauts to prevent SMS. Bioavailability of oral (PO) SMS medications is often low and highly variable. Intranasal (IN) administration of medications achieves higher and more reliable bioavailability than from an equivalent PO dose. Methods: To test the safety and reliability of INSCOP, two clinical studies were performed, a dose escalation study and a comparison study administering INSCOP during normal ambulation and head down tilt bedrest. Efficacy was evaluated by testing INSCOP with two, different motion sickness inducing paradigms. Results: Preliminary results indicate that INSCOP demonstrates linear pharmacokinetics and a low side effect profile. In head down tilt bedrest, relative bioavailability of INSCOP was increased for females at both doses (0.2 and 0.4 mg) and for males at the higher dose (0.4 mg) but is reduced at the lower dose (0.2 mg) compared to normal ambulation. INSCOP displays gender specific differences during ABR. One of the treatment efficacy trials conducted at Dartmouth Hitchcock Medical Center demonstrated that INSCOP is efficacious at both doses (0.2 and 0.4 mg) in suppressing motion sickness symptoms as indicated by longer chair ride times with INSCOP administration than with placebo, and efficacy increases with dose. Similar results were seen using another motion sickness simulator, the motion simulator dome, at the Naval Aerospace Medical Research Laboratory, with significantly increased time in the dome in motion-susceptible subjects when using INSCOP compared to untreated controls. Conclusion: Higher bioavailability, linear pharmacokinetics, a low incidence of side effects, and a favorable efficacy profile make INSCOP a desirable formulation for prophylactic and rescue treatment of astronauts in space and military personnel on duty.

Boyd, Jason L.↗

NASA NTRS1995

Computer Simulation of Motion of Heliospheric Termination Shock

A time-dependent computer model is used to study a non-equilibrium structure of the heliosphere, resulting from the interaction between the solar wind and the interstellar plasma. An interaction of the heliospheric termination shock with various disturbances such as density or velocity jumps or interplanetary shocks in upstream solar wind as well as pressure jumps in local interstellar medium is investigated. Consequences of latitudinal variation in dynamic pressure are also discussed. The initial boundary conditions of unsteady calculations are given by the solar wind parameters as functions of time and/or latitude on an inner boundary, and/or by the local interstellar pressure as a function of time (roughly simulating the effect of the local interstellar medium) on an outer boundary.

Ratkiewicz, R. E.↗

NASA NTRS1975

Psychological aspects of aeronautical flight simulation

Attention is given to the class of ground based devices which have been used by scientists, engineers, and test pilots to evaluate current or future aircraft systems. The characteristics of a flight simulator and its major subsystems are considered, taking into account simulator cockpits, visual scene attachments, aspects of visual attachment fidelity, simulator motion systems, motion system fidelity, and simulation computer systems. Questions related to psychological research and simulation are examined. Simulator validity criteria are discussed along with problems of subsystem fidelity.

Huff, E. M.↗

NASA NTRS1984

Accuracy of System Step Response Roll Magnitude Estimation from Central and Peripheral Visual Displays and Simulator Cockpit Motion

An experiment to investigate visual roll attitude and roll rate perception is described. The experiment was also designed to assess the improvements of perception due to cockpit motion. After the onset of the motion, subjects were to make accurate and quick estimates of the final magnitude of the roll angle step response by pressing the appropriate button of a keyboard device. The differing time-histories of roll angle, roll rate and roll acceleration caused by a step response stimulate the different perception processes related the central visual field, peripheral visual field and vestibular organs in different, yet exactly known ways. Experiments with either of the visual displays or cockpit motion and some combinations of these were run to asses the roles of the different perception processes. Results show that the differences in response time are much more pronounced than the differences in perception accuracy.

Hosman, R. J. A. W.↗

NASA NTRS1991

High performance computing system for flight simulation at NASA Langley

The computer architecture and components used in the NASA Langley Advanced Real-Time Simulation System (ARTSS) are briefly described and illustrated with diagrams and graphs. Particular attention is given to the advanced Convex C220 processing units, the UNIX-based operating system, the software interface to the fiber-optic-linked Computer Automated Measurement and Control system, configuration-management and real-time supervisor software, ARTSS hardware modifications, and the current implementation status. Simulation applications considered include the Transport Systems Research Vehicle, the Differential Maneuvering Simulator, the General Aviation Simulator, and the Visual Motion Simulator.

Cleveland, Jeff I., II↗