AFTI (Advanced Fighter Technology Integration)/F-111 Mission Adaptive Wing Briefing to Industry PDF Download
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Author: Publisher: ISBN: Category : Languages : en Pages : 424
Book Description
The AFTI/F-111 (Advanced Fighter Technology Integration/F-111) Mission Adaptive Wing is a joint USAF and NASA program which is developing and flight demonstrating a smooth variable camber wing and flight control system capable of adjusting the wing's shape in response to flight condition and pilot input in order to maximize aerodynamic efficiency. The program objective is to produce flight substantiated design criteria for a practical wing system that maintains peak aerodynamic efficiency and versatility throughout the broad flight envelopes and diverse mission requirements of future military and civilian aircraft. This document contains illustrations presented at the second AFTI/F-111 Mission Adaptive Wing Briefing to Industry on 21-22 July 1988 in Dayton OH. The presentations covered the analysis, design, ground test, and flight test phases of the development of the automatic flight control system for the AFTI/F-111. Flight testing of the AFTI/F-111 Mission Adaptive Wing system was only partially complete at the time these illustrations were prepared for presentation. Data and findings should be considered preliminary. Keywords: Jet fighters; Variable leading edges; Variable trailing edges; Smooth variable camber wing; Automatic flight controls.
Author: Publisher: ISBN: Category : Languages : en Pages : 424
Book Description
The AFTI/F-111 (Advanced Fighter Technology Integration/F-111) Mission Adaptive Wing is a joint USAF and NASA program which is developing and flight demonstrating a smooth variable camber wing and flight control system capable of adjusting the wing's shape in response to flight condition and pilot input in order to maximize aerodynamic efficiency. The program objective is to produce flight substantiated design criteria for a practical wing system that maintains peak aerodynamic efficiency and versatility throughout the broad flight envelopes and diverse mission requirements of future military and civilian aircraft. This document contains illustrations presented at the second AFTI/F-111 Mission Adaptive Wing Briefing to Industry on 21-22 July 1988 in Dayton OH. The presentations covered the analysis, design, ground test, and flight test phases of the development of the automatic flight control system for the AFTI/F-111. Flight testing of the AFTI/F-111 Mission Adaptive Wing system was only partially complete at the time these illustrations were prepared for presentation. Data and findings should be considered preliminary. Keywords: Jet fighters; Variable leading edges; Variable trailing edges; Smooth variable camber wing; Automatic flight controls.
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722726409 Category : Languages : en Pages : 38
Book Description
A transonic fighter-bomber aircraft, having a swept supercritical wing with smooth variable-camber flaps was fitted with a maneuver load control (MLC) system that implements a technique to reduce the inboard bending moments in the wing by shifting the spanwise load distribution inboard as load factor increases. The technique modifies the spanwise camber distribution by automatically commanding flap position as a function of flap position, true airspeed, Mach number, dynamic pressure, normal acceleration, and wing sweep position. Flight test structural loads data were obtained for loads in both the wing box and the wing root. Data from uniformly deflected flaps were compared with data from flaps in the MLC configuration where the outboard segment of three flap segments was deflected downward less than the two inboard segments. The changes in the shear loads in the forward wing spar and at the roots of the stabilators also are presented. The camber control system automatically reconfigures the flaps through varied flight conditions. Configurations having both moderate and full trailing-edge flap deflection were tested. Flight test data were collected at Mach numbers of 0.6, 0.7, 0.8, and 0.9 and dynamic pressures of 300, 450, 600, and 800 lb/sq ft. The Reynolds numbers for these flight conditions ranged from 26 x 10(exp 6) to 54 x 10(exp 6) at the mean aerodynamic chord. Load factor increases of up to 1.0 g achieved with no increase in wing root bending moment with the MLC flap configuration. Thornton, Stephen V. Armstrong Flight Research Center RTOP 505-63-50...
Author: Sergio Ricci Publisher: Butterworth-Heinemann ISBN: 0081009690 Category : Technology & Engineering Languages : en Pages : 970
Book Description
Morphing Wings Technologies: Large Commercial Aircraft and Civil Helicopters offers a fresh look at current research on morphing aircraft, including industry design, real manufactured prototypes and certification. This is an invaluable reference for students in the aeronautics and aerospace fields who need an introduction to the morphing discipline, as well as senior professionals seeking exposure to morphing potentialities. Practical applications of morphing devices are presented—from the challenge of conceptual design incorporating both structural and aerodynamic studies, to the most promising and potentially flyable solutions aimed at improving the performance of commercial aircraft and UAVs. Morphing aircraft are multi-role aircraft that change their external shape substantially to adapt to a changing mission environment during flight. The book consists of eight sections as well as an appendix which contains both updates on main systems evolution (skin, structure, actuator, sensor, and control systems) and a survey on the most significant achievements of integrated systems for large commercial aircraft. - Provides current worldwide status of morphing technologies, the industrial development expectations, and what is already available in terms of flying systems - Offers new perspectives on wing structure design and a new approach to general structural design - Discusses hot topics such as multifunctional materials and auxetic materials - Presents practical applications of morphing devices
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Author: Stephen V. Thornton
Author: National Aeronautics and Space Administration (NASA)
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Author: Sergio Ricci
Author: Lannie D. Webb
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