Performance Adaptive Aeroeleastic Wing (PAAW) Program
Persistent link for this communityhttps://hdl.handle.net/11299/167170
The goal of the Performance Adaptive Aeroelastic Wing (PAAW) Program is to research and develop a future commercial aircraft wing that continuously optimizes its shape for current flight conditions and aircraft configuration. This approach could maximize lift for takeoff, minimize fuel consumption in cruise, or maximize lift and drag for landing. All data, models, and software developed as part of this program will be available open-source.
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Item Application of MIDAAS to BFF Models(2014-11-23) Danowsky, BrianModal Isolation and Damping for Adaptive Aeroservoelastic Suppression (MIDAAS) was applied to the BFF model at various flight conditions. All available control surfaces were used with nine sensors. MIDAAS synthesis produces a gain matrix feeding back all outputs to all inputs. Using these inputs and outputs, the resulting gain matrix is 9 by 8. Solutions were obtained for 3 different flight conditions (42, 44, and 50 knots). For each flight condition, a solution was obtained for two models, 1) bare airframe dynamics and 2) full system dynamics including bare airframe, actuator and sensor dynamics.Item BFF Wind Tunnel Model Design Files(2014-11) Skelton, MatthewItem Center of Gravity Testing and Results(2014-07-24) Taylor, BrianItem CFD/CSD-based IOROM Construction for mAEWing1 initial design(2015-09-15) Danowsky, BrianThis working paper summarizes the construction of the Input to Output Reduced Order Model (IOROM) for mAEWing1. The linear time invariant (LTI) IOROM is based on a fixed trimmed flight condition and is represented as a state space system with the traditional four matrix quadruple: [A, B; C, D]. These IOROMs are entirely software-based models that start with a detailed Computational Fluid Dynamic / Computational Structural Dynamic (CFD/CSD)-based model built in the CMSoft, Inc. AERO software suite. The nonlinear full order AERO model (NFOM) is millions of degrees of freedom and is unsuitable for open loop dynamic analysis and control system design. From this model, a linear time invariant reduced order aeroelastic model (ROM) is built describing the modal structural dynamics coupled with the unsteady aerodynamic forces. This model is represented in an inertial frame since that is the frame for the finite element model (FEM). This ROM is sent to the STI ASETool software where the structural rigid body states are cast into the traditional body-fixed frame, and the input and output effect is added with user defined descriptions of actuation and sensor nodes resulting in the IOROM. The IOROM is a linear model of significantly reduced order that is in the ideal form for dynamic analysis and control system design. It includes all rigid body states, structural modal states, and unsteady aerodynamic states. The 12 rigid body states include the translational and rotational displacements and velocities and are represented in their traditional body-fixed frame of reference, making this model in an ideal form for complete control system design that includes primary flight control and flutter suppression. Stability and control derivatives can be directly extracted from the IOROM for direct comparison to experimental test data or other analytical models. These models are also used for novel system analysis using phasor diagrams where rigid body and flexible dynamic coupling can be clearly characterized. Approximate linear parameter varying models can also be created from the IOROMs that are dependent on a variable trim velocity. These models can be used for traditional flutter analysis (e.g., V-G diagrams, etc.) and LPV control design.Item Classical Control Design Feasibility Study with BFF Models(2014-11-18) Lee, Dongchan; Danowsky, BrianThis working paper documents an initial control feasibility study to determine if classical control techniques could be utilized to favorably augment the stability of the BFF vehicle. This study focused on the lower speed models which have stable, or slightly unstable aeroelastic dynamics. Future studies will explore the higher speed models with highly unstable aeroelastic modes. The final control solution will incorporate stability augmentation with aeroelastic suppression, including flutter suppression to stabilize the vehicle beyond the flutter boundary. The principal goal is a defined strategy, process and supporting software tools to develop a full envelope controller for flexible aeroelastic vehicles with significant rigid body and flexible coupling. Focus will be on blended wing-body vehicle designs like the BFF and X-56A. The purpose of this study is a background feasibility investigation.Item Fenrir Flight 04(2014-09-02) Taylor, BrianItem Fenrir Flight 05(2014-09-02) Taylor, BrianItem Fenrir Flight 06(2014-09-02) Taylor, BrianItem Fenrir Flight 07(2014-09-02) Taylor, BrianItem Fenrir Flight 08(2014-09-02) Taylor, BrianItem Fenrir Flight 09(2014-10-10) Taylor, BrianItem Fenrir Flight 10(2014-10-10) Taylor, BrianItem Fenrir Flight 11(2014-10-10) Taylor, BrianItem Fenrir Flight 12(2014-10-11) Taylor, BrianItem Fenrir Flight 13(2014-10-11) Taylor, BrianItem Fenrir Flight 14(2014-10-11) Taylor, BrianItem Fenrir Flight 15(2014-10-11) Taylor, BrianItem Fenrir Flight 16(2015-01-30) Singh, ParulItem Fenrir Flight 17(2015-02-09) Taylor, BrianItem Fenrir Flight 18(2015-05-21) Taylor, Brian