Hypersonic flight simulation - Aerodynamics
Aerodynamic characteristics of hypersonic flight simulation
Potter, J. L.↗
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Motion drive signals for piloted flight simulators
Motion drive signals for piloted flight simulators
Conrad, B.↗
Recent ground-based and in-flight simulator studies of low-speed handling characteristics of supersonic cruise transport aircraft
Several advanced arrow-wing concepts have evolved from NASA's Supersonic Cruise Aircraft Research (SCAR) Program. Evaluations of the low-speed handling characteristics of these configurations have been conducted at Langley Research Center using a fixed-base ground simulator with a visual landing scene. A brief in-flight simulation program was also conducted using Calspan's Total In-Flight Simulator (TIFS) in order to provide: (1) points of reference for interpretation of the ground-simulator results, (2) data for control-system design tradeoffs, and (3) data on effects of real-world visual height cues and cockpit-motion cues not available in the fixed-base simulation. The more significant results of these studies are presented.
Grantham, W. D.↗
The use of piloted flight simulators in take-off and landing research
Piloted flight simulators for takeoff and landing research
FLIGHT SIMULATOR↗
Comparison of Different Methods of Grading a Level Turn Task on a Flight Simulator
With the advancements in the computing power of personal computers, pc-based flight simulators and trainers have opened new avenues in the training of airplane pilots. It may be desirable to have the flight simulator make a quantitative evaluation of the progress of a pilot's training thereby reducing the physical requirement of the flight instructor who must, in turn, watch every flight. In an experiment, University students conducted six different flights, each consisting of two level turns. The flights were three minutes in duration. By evaluating videotapes, two certified flight instructors provided separate letter grades for each turn. These level turns were also evaluated using two other computer based grading methods. One method determined automated grades based on prescribed tolerances in bank angle, airspeed and altitude. The other method used was deviations in altitude and bank angle for performance index and performance grades.
Heath, Bruce E.↗
A Laboratory Glass-Cockpit Flight Simulator for Automation and Communications Research
A laboratory glass-cockpit flight simulator supporting research on advanced commercial flight deck and Air Traffic Control (ATC) automation and communication interfaces has been developed at the Aviation Operations Branch at the NASA Ames Research Center. This system provides independent and integrated flight and ATC simulator stations, party line voice and datalink communications, along with video and audio monitoring and recording capabilities. Over the last several years, it has been used to support the investigation of flight human factors research issues involving: communication modality; message content and length; graphical versus textual presentation of information, and human accountability for automation. This paper updates the status of this simulator, describing new functionality in the areas of flight management system, EICAS display, and electronic checklist integration. It also provides an overview of several experiments performed using this simulator, including their application areas and results. Finally future enhancements to its ATC (integration of CTAS software) and flight deck (full crew operations) functionality are described.
Pisanich, Gregory M.↗
Results of a Flight Simulation Software Methods Survey
A ten-page questionnaire was mailed to members of the AIAA Flight Simulation Technical Committee in the spring of 1994. The survey inquired about various aspects of developing and maintaining flight simulation software, as well as a few questions dealing with characterization of each facility. As of this report, 19 completed surveys (out of 74 sent out) have been received. This paper summarizes those responses.
Jackson, E. Bruce↗
Julia Programming Language Benchmark Using a Flight Simulation
Julia is a relatively new computer language that aims to reduce the challenge for mathmodelers to develop fast computer tools and simulations. It potentially combines the ease-of-coding feature of scripting languages (like Python) with the performance of compiled languages (like C++). A key question for Julia application to the simulation domain is, “Can Julia, with its obvious coding simplicity, provide runtime speeds comparable to conventional compiled languages for flight simulation?” A unique combination of existing elements can be employed to address the previous question: Extensively documented object-oriented simulation architecture, Industry standard rocket flight simulation, Separate versions (C++, Java, and Python) already benchmarked.
Sells, Ray↗
A review of recent programs and future plans for rotorcraft in-flight simulation at Ames Research Center
A new flight research vehicle, the Rotorcraft-Aircrew Systems Concepts Airborne Laboratory (RASCAL), is being developed by the U.S. Army and NASA at Ames Research Center. The requirements for this new facility stem from a perception of rotorcraft system technology requirements for the next decade together with operational experience with the CH-47B research helicopter that was operated as an in-flight simulator at Ames during the past 10 years. Accordingly, both the principal design features of the CH-47B variable-stability system and the flight-control and cockpit-display programs that were conducted using this aircraft at Ames are reviewed. Another U.S. Army helicopter, a UH-60A Black Hawk, has been selected as the baseline vehicle for the RASCAL. The research programs that influence the design of the RASCAL are summarized, and the resultant requirements for the RASCAL research system are described. These research programs include investigations of advanced, integrated control concepts for achieving high levels of agility and maneuverability, and guidance technologies, employing computer/sensor-aiding, designed to assist the pilot during low-altitude flight in conditions of limited visibility. The approach to the development of the new facility is presented and selected plans for the preliminary design of the RASCAL are described.
Eshow, Michelle M.↗
X-15 flight simulation studies
This paper describes briefly the flight-simulation studies carried out on the X-15 since the 1956 conference, the capabilities of current simulations, and some of the significant results of these studies. The scope of these simulations has been expanded to cover the entire flight regime so that it is now possible to fly the entire mission from launch to landing approach.
Merrick, George B↗
High performance processors for real-time flight simulation
In order to meet the requirements of the NASA Langley Research Center for simulating the increased complexity and higher performance of modern aircraft, a flight simulation computing system with very high scalar performance is needed. The requirements and proposed response, probable areas of difficulty, planned implementation, and current status and plans are reviewed. A solution utilizing centralized minisupercomputers coupled with a proven real-time network technology will provide engineers and research scientists with the tools required for high-performance flight simulation. Subsequent to testing and verification of the initial simulation, general-purpose configuration management software with a nonconfiguration dependent serial highway driver software will be integrated to support any arbitrary combination of simulation sites.
Cleveland, Jeff I., II↗
Real-time aerodynamic heating and surface temperature calculations for hypersonic flight simulation
A real-time heating algorithm was derived and installed on the Ames Research Center Dryden Flight Research Facility real-time flight simulator. This program can calculate two- and three-dimensional stagnation point surface heating rates and surface temperatures. The two-dimensional calculations can be made with or without leading-edge sweep. In addition, upper and lower surface heating rates and surface temperatures for flat plates, wedges, and cones can be calculated. Laminar or turbulent heating can be calculated, with boundary-layer transition made a function of free-stream Reynolds number and free-stream Mach number. Real-time heating rates and surface temperatures calculated for a generic hypersonic vehicle are presented and compared with more exact values computed by a batch aeroheating program. As these comparisons show, the heating algorithm used on the flight simulator calculates surface heating rates and temperatures well within the accuracy required to evaluate flight profiles for acceptable heating trajectories.
Quinn, Robert D.↗
Virtual image display for flight simulation
Plastic lenses providing virtual image of flight scene for use in flight simulator with Schmidt projection system or television monitor
Ganzler, B. C.↗
Sidelooking laser altimeter for a flight simulator
An improved laser altimeter for a flight simulator which allows measurement of the height of the simulator probe above the terrain directly below the probe tip is described. A laser beam is directed from the probe at an angle theta to the horizontal to produce a beam spot on the terrain. The angle theta that the laser beam makes with the horizontal is varied so as to bring the beam spot into coincidence with a plumb line coaxial with the longitudinal axis of the probe. A television altimeter camera observes the beam spot and has a raster line aligned with the plumb line. Spot detector circuit coupled to the output of the TV camera monitors the position of the beam spot relative to the plumb line.
Webster, L. D.↗
User's Guide for Flight Simulation Data Visualization Workstation
Today's modern flight simulation research produces vast amounts of time sensitive data. The meaning of this data can be difficult to assess while in its raw format. Therefore, a method of breaking the data down and presenting it to the user in a graphical format is necessary. Simulation Graphics (SimGraph) is intended as a data visualization software package that will incorporate simulation data into a variety of animated graphical displays for easy interpretation by the simulation researcher. This document is intended as an end user's guide.
Kaplan, Joseph A.↗
Experimental investigation of shock-cell noise reduction for dual-stream nozzles in simulated flight
Six scale-model nozzles were tested in an anechoic facility to evauate the effectiveness of convergent-divergent (C-D) terminations in reducing shock-cell noise of unsuppressed and mechanically suppressed coannular plug nozzles. One hundred fifty-three acoustic test points with inverted velocity profiles were conducted under static and simulated flight conditions. Diagnostic flow visualization with a shadowgraph and velocity measurements with a laser velocimeter were performed on selected plumes. Shock-cells were identified on the plug and downstream of the plug of the unsuppressed convergent coannular nozzle with truncated plug. Broadband peak frequencies predicted with the two shock-cell structures were correlated with the observed spectra using the measured shock-cell spacings. Relative to a convergent circular nozzle, the perceived noise level (PNL) data at an observer angle of 60 deg relative to inlet, indicated a reduction of (1) 6.5 dB and 9.2 dB with unsuppressed C-D coannular nozzle with truncated plug and (2) 7.7 dB and 8.3 dB with suppressed C-D coannular nozzle under static and simulated flight conditions, espectively. The unsuppressed C-D coannular nozzle with truncated plug, operating at the C-D design condition, had shock-cells downstream of the plug with no shock-cells on the plug. The downstream shock-cells were eliminated by replacing the truncated plug with a smooth extension to obtain an additional 2.4 dB and 3 dB front quadrant PNL reduction, under static and simulated flight conditions, respectively. Other results are discussed.
Janardan, B. A.↗
Flight simulation for wind shear encounter
A real-time piloted flight simulator is under development in the Laboratory for Control and Automation at Princeton University. This facility will be used to study piloted flight through a simulated wind shear. It will also provide a testbed for real-time flight guidance laws. The hardware configuration and aerodynamic model used are discussed. The microburst model to be incorporated into the simulation is introduced, and some proposed cockpit display concepts are described.
Mulgund, Sandeep S.↗
Flight simulator fidelity assessment in a rotorcraft lateral translation maneuver
A model-based methodology for assessing flight simulator fidelity in closed-loop fashion is exercised in analyzing a rotorcraft low-altitude maneuver for which flight test and simulation results were available. The addition of a handling qualities sensitivity function to a previously developed model-based assessment criteria allows an analytical comparison of both performance and handling qualities between simulation and flight test. Model predictions regarding the existence of simulator fidelity problems are corroborated by experiment. The modeling approach is used to assess analytically the effects of modifying simulator characteristics on simulator fidelity.
Hess, R. A.↗