The strength, aeroelasticity, and fatigue life of such a prototype are analyzed. The feasibility of fitting a rotating oblique wing on an F-8 aircraft to produce a full scale manned prototype capable of operating in the transonic and supersonic speed range was investigated. 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.į-8 oblique wing structural feasibility study The measured servoactuator frequency responses are presented along with analytical predictions derived from the integrated characteristics of the control elements. The wing camber and control system are described. The camber was positioned and controlled by flexing the upper skins through rotary actuators and linkages driven by power drive units.
The 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. Variable-camber systems integration and operational performance of the AFTI/ F- 111 mission adaptive wing
