The X-53 Active Aeroelastic Wing (AAW) development program is a completed research project that was undertaken jointly by the Air Force Research Laboratory (AFRL), Boeing Phantom Works and NASA Dryden Flight Research Center, where the technology was flight tested on a modified F/A-18 Hornet. The program was led by a cadre of people from these organizations including Edmund W. Pendleton and Dr Ken Griffin from the Air Force, Denis Bessette and Dave Voracek from NASA Dryden, and Pete Field, Dr Jim Guffey, and Eric Reichenbach from Boeing St Louis. Gerry Miller of North American Aviation (later part of Boeing) and Jan Tulinius led the development of the initial concept during wind tunnel testing in the mid 1980s under Air Force contract.[1] The designation "X-52" was skipped in sequence to avoid confusion with the B-52 bomber.
Design and development
Time lapsed film of Active Aeroelastic Wing (AAW) Wing loads test
AAW combines aerodynamics, active controls and advanced structures to make more efficient use of the wing platform during high-speed maneuvers. This is achieved through the use of multiple leading and trailing edge control surfaces, which are controlled by a digital flight control system to take advantage of the wings' natural tendency to twist under air load. At high speeds, these control surfaces are able to achieve high levels of control power while minimizing structural loads. When applied correctly, the wing will twist less and in an opposite direction to a conventional wing during maneuvering.[2]
The modified F/A-18 first flew in November, 2002.[3] It was redesignated X-53 on August 16, 2006, per memo by USAF Deputy Chief of Staff, Strategic Plans and Programs.[1]
Specification
F/A-18A (now X-53) Active Aeroelastic Wing (AAW) flight test, March, 2005
See also
Related development
References
External links
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