摘要 :
This history of the Flight Research Center (FRC) Simulation Laboratory (FSL)describes the development of experimental flight-test simulators and the rapid evolution of the computers that made them run. (The FRC was a predecessor o...
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This history of the Flight Research Center (FRC) Simulation Laboratory (FSL)describes the development of experimental flight-test simulators and the rapid evolution of the computers that made them run. (The FRC was a predecessor of NASA's Dryden Flight Research Center, Edwards, California.) This publication describes the development of the Flight Research Center Simulation Laboratory during the period from 1955 to 1975. These are the years in which analog computers were used as a major component of every flight simulation that was mechanized in support of the many different flight research projects at the High-Speed Flight Station (HSFS-redesignated the Flight Research Center (FRC) in 1959 and the Dryden Flight Research Center (DFRC) in 1976). Initially, analog computers were used along with a ground-based cockpit for these simulators. This started in 1955. In 1964 a small scientific digital computer was bought and added to the X-15 simulator. This was the start of the hybrid (combined analog and digital) computer period of flight simulators. Both of these periods are covered in this document.
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摘要 :
After a brief historical review of the evolution of flight simulation techniques, the present lecture notes first deal with the main areas of flight simulator applications. Next, they describe the main components of a piloted flig...
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After a brief historical review of the evolution of flight simulation techniques, the present lecture notes first deal with the main areas of flight simulator applications. Next, they describe the main components of a piloted flight simulator. Because of the presence of the pilot-in-the-loop, the digital computer driving the simulator must solve the aircraft equations of motion in 'real-time.' Solutions to meet the high required computer power of today's modern flight simulator are elaborated. The physical similarity between aircraft and simulator in cockpit layout, flight instruments, flying controls, etc., is discussed, based on the equipment and environmental cue fidelity, required for training and research simulators.
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The TurbSim stochastic inflow turbulence code was developed to provide a numerical simulation of a full-field flow that contains coherent turbulence structures that reflect the proper spatiotemporal turbulent velocity field relati...
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The TurbSim stochastic inflow turbulence code was developed to provide a numerical simulation of a full-field flow that contains coherent turbulence structures that reflect the proper spatiotemporal turbulent velocity field relationships seen in instabilities associated with nocturnal boundary layer flows that are not represented well by the IEC Normal Turbulence Models (NTM). Its purpose is to provide the wind turbine designer with the ability to drive design code (FAST or MSC.ADAMS) simulations of advanced turbine designs with simulated inflow turbulence environments that incorporate many of the important fluid dynamic features known to adversely affect turbine aeroelastic response and loading.
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摘要 :
The TurbSim stochastic inflow turbulence code was developed to provide a numerical simulation of a full-field flow that contains coherent turbulence structures that reflect the proper spatiotemporal turbulent velocity field relati...
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The TurbSim stochastic inflow turbulence code was developed to provide a numerical simulation of a full-field flow that contains coherent turbulence structures that reflect the proper spatiotemporal turbulent velocity field relationships seen in instabilities associated with nocturnal boundary layer flows that are not represented well by the IEC Normal Turbulence Models (NTM). Its purpose is to provide the wind turbine designer with the ability to drive design code (FAST or MSC.ADAMS) simulations of advanced turbine designs with simulated inflow turbulence environments that incorporate many of the important fluid dynamic features known to adversely affect turbine aeroelastic response and loading.
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摘要 :
In motion simulation the inertial information generated by the motion platform is most of the times different from the visual information in the simulator displays. This occurs due to the physical limits of the motion platform. Ho...
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In motion simulation the inertial information generated by the motion platform is most of the times different from the visual information in the simulator displays. This occurs due to the physical limits of the motion platform. However, for small motions that are within the physical limits of the motion platform, one-to-one motion, i.e. visual information equal to inertial information, is possible. It has been shown in previous studies that one-to-one motion is often judged as too strong, causing researchers to lower the inertial amplitude. When trying to measure the optimal inertial gain for a visual amplitude, we found a zone of optimal gains instead of a single value. Such result seems related with the coherence zones that have been measured in flight simulation studies. However, the optimal gain results were never directly related with the coherence zones. In this study we investigated whether the optimal gain measurements are the same as the coherence zone measurements. We also try to infer if the results obtained from the two measurements can be used to differentiate between simulators with different configurations. An experiment was conducted at the NASA Langley Research Center which used both the Cockpit Motion Facility and the Visual Motion Simulator. The results show that the inertial gains obtained with the optimal gain are different than the ones obtained with the coherence zone measurements. The optimal gain is within the coherence zone.The point of mean optimal gain was lower and further away from the one-to-one line than the point of mean coherence. The zone width obtained for the coherence zone measurements was dependent on the visual amplitude and frequency. For the optimal gain, the zone width remained constant when the visual amplitude and frequency were varied. We found no effect of the simulator configuration in both the coherence zone and optimal gain measurements.
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