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Variable-camber systems integration and operational performance of the AFTI/F-111 mission adaptive wingThe advanced fighter technology integration, the AFTI/F-111 aircraft, is a preproduction F-111A testbed research airplane that was fitted with a smooth variable-camber mission adaptive wing. The camber was positioned and controlled by flexing the upper skins through rotary actuators and linkages driven by power drive units. The wing camber and control system are described. The measured servoactuator frequency responses are presented along with analytical predictions derived from the integrated characteristics of the control elements. A mission adaptive wing system chronology is used to illustrate and assess the reliability and dependability of the servoactuator system during 1524 hours of ground tests and 145 hours of flight testing.
Document ID
19920012951
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Smith, John W. (PRC Systems Services Co. Edwards, CA., United States)
Lock, Wilton P. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Payne, Gordon A. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1992
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-TM-4370
H-1748
NAS 1.15:4370
Accession Number
92N22194
Funding Number(s)
PROJECT: RTOP 533-02-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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