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F-106B Airplane Active Control Landing Gear Drop Test Performance
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English
Abstract
Aircraft dynamic loads and vibrations resulting from landing impact and from runway and taxiway unevenness are recognized as significant factors in causing fatigue damage, dynamic stress on the airframe, crew and passenger discomfort, and reduction of the pilot's ability to control the aircraft during ground operations. One potential method for improving operational characteristics of aircraft on the ground is the application of active-control technology to the landing gear to reduce ground loads applied to the airframe.
An experimental investigation was conducted on a series-hydraulic active control nose gear. The experiments involved testing the gear in both passive and active control modes. Results of this investigation show that a series-hydraulically controlled gear is feasible and that such a gear is effective in reducing the loads transmitted by the gear to the airframe during ground operations.
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Authors
Citation
Howell, W., McGehee, J., Daugherty, R., and Vogler, W., "F-106B Airplane Active Control Landing Gear Drop Test Performance," SAE Technical Paper 901911, 1990, https://doi.org/10.4271/901911.Also In
References
- Wignot, Jack E. Durup, Paul C. Gamon, Max A. Design Formulation and Analysis of an Active Landing Gear. Volume I, Analysis I U.S. Air Force August 1971
- Bender E. K. Berkman, E. F. Bieber, M. A Feasibility Study of Active Landing Gear Air Force July 1971
- McGehee, John R. Dreher, Robert C. Experimental Investigation of Active Loads Control for Aircraft Landing Gear NASA TP-2042 1982
- Morris, David L. Active Landing Gear Response Testing U.S. Air Force April 1982
- McGehee, John R. Morris, David L. active Control Landing Gear for Ground Load Alleviation 18-1 18-12 March 1985
- Morris, David L. F-4 Active Control Landing Gear Dynamic Response Testing Air Force August 1985