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Morphing Lecture by Mark Drela |
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Date: July 12, 2005
Time: 9:30am
Location: NASA LaRC, Bldg 1209, Rm 180
ASWING: An Integrated Simulation Model for Preliminary Aerodynamic, Structural, and Control-Law Design of Aircraft
Mark Drela, MIT
A fully nonlinear model is developed for aerodynamic, structural, and control simulation of highly flexible aircraft. The structure consists of joined nonlinear beams. The aerodynamic model is a compressible vortex/source-lattice with wind-aligned trailing vorticity. Full unsteady terms with flight dynamics are included.
Model forcing is via gravity, engine forces, gusts, and control inputs.
The overall nonlinear equation set is solved by a full Newton method for steady-state or time-domain simulations. The Newton Jacobian matrix is available as a byproduct, and can be used for further Bode analysis of control and gust response, and for eigenmode analysis of flight stability and flutter.
The numerical problem is small enough for interactive computation, allowing rapid diagnosis of local aerodynamic stall, structural failure, or control system saturation for a wide range of flight conditions.
The overall approach allows quick generation of a robust multi-disciplinary preliminary design which can serve as a good basis for subsequent detailed design.
The talk will consist of a review of the material originally presented at the 1999 AIAA SDM conference (AIAA Paper 99-1394). Recent additions and extensions aimed at the Helios project will also be summarized.
These include sensors, advanced engine models, engine plume effects, structural damping, and sinusoidal gust field Bode response, and reduced-order model extraction for control law design.
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