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Challenges and lessons learned from resurrecting a legacy research flight controller

Challenges and lessons learned from resurrecting a legacy re...

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作者： Moua, Cheng M. Dees, Ray A. Controls and Dynamics Branch NASA Dryden Flight Research Center MS 4840D P.O. Box 273 Edwards CA 93523-0273 United States Simulation Engineering Branch NASA Dryden Flight Research Center MS 4840D P.O. Box 273 Edwards CA 93523-0273 United States

ISBN: (纸本)9781600867392

Resurrecting the legacy Inner Loop Thrust Vectoring research flight controller to investigate the tail shock region brought unique challenges. This report documents these challenges and lessons learned from a stability and controls perspective. The flight test approach for flight envelope expansion and probing tests, as well as limited flight test results, are presented. Recent advances in sonic boom reduction technology have contributed to a resurgent interest in civilian supersonic cruise flight. These advances have focused only on fore body shaping, however, and little, if any, experimental flight data are available to develop and validate design tools for the tail shock region. In January of 2009, the NASA Dryden flight Research Center completed research flights to investigate the tail shock region of a highly modified F-15 aircraft by probing the shock waves around it, using another F-15 aircraft. To adjust the lift distribution and plume shape, a decade-old research flight controller from the Inner Loop Thrust Vectoring project was required. To investigate the tail shock region, the lift distribution was changed by adjusting the canard position, and the plume shape was changed by adjusting the nozzle area and thrust vectoring.

关键词： flight envelopes

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Determination of helicopter simulator time delay and its effects on air vehicle development

Determination of helicopter simulator time delay and its eff...

引用

flight Simualtion Technologies Conference, 1988

作者： Woltkamp, John Ramachandran, S. Branson, Roger McDonnell Douglas Helicopter Company MesaAZ85205 United States Flight Dynamics and Controls Simulation United States

McDonnell Douglas Helicopter Company recently undertook a study to determine the actual simulator hardware time delay in all the simulators. It also investigated the effect of time delay on pilot performance and his aircraft evaluation in an engineering design environment. This paper describes the system architecture, techniques of measuring thruput delays, and initial study results. It was found that the average total system delay was about 87 milliseconds, well below values reported in open literature for most of the training and engineering simulators. The second phase of the study involved systematically varying the simulator delays so that data on the effect of time delay could be collected and used as a useful parameter in aircraft /simulator design. Pilot performance was recorded and subjective evaluations in the form of Cooper-Harper ratings were also obtained. Analysis of pilot performance did not provide any dramatic changes due to increased simulator delays but did show that the pilot control activity increased in the low speed, high gain tasks. It was found that with increased time delay the Cooper-Harper rating increased indicating degradation in perceived handling qualities. However, for the type of helicopter simulated, there was not a definite time delay at which the ratings changed abruptly. This indicates that for engineering design purposes while it is desirable to keep the delay to the absolute minimum, there may be sufficient flexibility in the design of the simulator to permit cost/ capability trade offs. However, this needs to be further validated by additional tests that introduce pilot distractions (such as gusts) and force the pilot to increase his closed loop gain. © 1988 by S. Ramachandran.

关键词： Time delay

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