| タイトル | Guidance and Control Design for High-Speed Rollout and Turnoff (ROTO) |
| 本文（外部サイト） | http://hdl.handle.net/2060/19970001349 |
| 著者（英） | McBee, L. S.; Shannon, J. H.; Summers, L. G.; Dangaran, R. D.; Norman, R. M.; Dwyer, J. P.; Goldthorpe, S. H. |
| 著者所属（英） | McDonnell-Douglas Aerospace |
| 発行日 | 1996-08-01 |
| 言語 | eng |
| 内容記述 | A ROTO architecture, braking and steering control law and display designs for a research high speed Rollout and Turnoff (ROTO) system applicable to transport class aircraft are described herein. Minimum surface friction and FMS database requirements are also documented. The control law designs were developed with the aid of a non-real time simulation program incorporating airframe and gear dynamics as well as steering and braking guidance algorithms. An attainable objective of this ROTO system, as seen from the results of this study, is to assure that the studied aircraft can land with runway occupancy times less then 53 seconds. Runway occupancy time is measured from the time the aircraft crosses the runway threshold until its wing tip clears the near side of the runway. Turnoff ground speeds of 70 knots onto 30 degree exits are allowed with dry and wet surface conditions. Simulation time history and statistical data are documented herein. Parameters which were treated as variables in the simulation study include aircraft touchdown weight/speed/location, aircraft CG, runway friction, sensor noise and winds. After further design and development of the ROTO control system beyond the system developed earlier, aft CG MD-11 aircraft no longer require auto-asymmetric braking (steering) and fly-by-wire nose gear steering. However, the auto ROTO nose gear hysteresis must be less than 2 degrees. The 2 sigma dispersion certified for MD-11 CATIIIB is acceptable. Using this longitudinal dispersion, three ROTO exits are recommended at 3300, 4950 and 6750 feet past the runway threshold. The 3300 foot exit is required for MD-81 class aircraft. Designs documented in this report are valid for the assumptions/models used in this simulation. It is believed that the results will apply to the general class of transport aircraft; however further effort is required to validate this assumption for the general case. |
| NASA分類 | Aircraft Stability and Control |
| レポートNO | 97N11167
NASA-CR-201602
NAS 1.26:201602
CRAD-9206-TR-1659 |
| 権利 | No Copyright |
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