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Subsonic Maneuvering Effectiveness of High Performance Aircraft Which Employ Quasi-Static Shape Change Devices

Author
Weston, Robert P.
Published
1998.
Physical Description
1 electronic document
Additional Creators
Montgomery, Raymond C. and Scott, Michael A. (Michael Andrew), 1978-
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
This paper represents an initial study on the use of quasi-static shape change devices in aircraft maneuvering. The macroscopic effects and requirements for these devices in flight control are the focus of this study. Groups of devices are postulated to replace the conventional leading-edge flap (LEF) and the all-moving wing tip (AMT) on the tailless LMTAS-ICE (Lockheed Martin Tactical Aircraft Systems - Innovative Control Effectors) configuration. The maximum quasi-static shape changes are 13.8% and 7.7% of the wing section thickness for the LEF and AMT replacement devices, respectively. A Computational Fluid Dynamics (CFD) panel code is used to determine the control effectiveness of groups of these devices. A preliminary design of a wings-leveler autopilot is presented. Initial evaluation at 0.6 Mach at 15,000 ft. altitude is made through batch simulation. Results show small disturbance stability is achieved, however, an increase in maximum distortion is needed to statically offset five degrees of sideslip. This only applies to the specific device groups studied, encouraging future research on optimal device placement.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19980032587.
NASA/TM-1998-207570.
NAS 1.15:207570.
Smart Structures and Materials; 1-6 Mar. 1998; San Diego, CA; United States.
5th Annual International Symposium on Smart Structures and Materials; 1-6 Mar. 1998; San Diego, CA; United States.
Terms of Use and Reproduction
No Copyright.
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