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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Browsing Performance Adaptive Aeroeleastic Wing (PAAW) Program by Author "Schmidt, David"
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Item Flight-Dynamics, Flutter, and Active-Flutter-Suppression Analyses of a Flexible Flying-Wing Research Drone(As presented at the NASA Armstrong Flight Research Center Edwards AFB, CA, 2015-06-15) Schmidt, DavidItem Flight-Dynamics, Flutter, and Active-Flutter-Suppression Analysis of a Flexible Flying-Wing Research Drone(Aerospace Flutter and Dynamics Council (AFDC) Meeting, Spring 2015, 2015-04-16) Schmidt, DavidItem MATLAB-Based Flight-Dynamics and Flutter Modeling of a Flexible Flying-Wing Research Drone(2015-05-19) Schmidt, DavidA relatively low-order, linear dynamic model is developed for the longitudinal flight- dynamics analysis of a flexible, flying-wing research drone, and results are compared to previously published results. The model includes the dynamics of both the rigid-body and elastic degrees of freedom, and the subject vehicle is designed to flutter within its flight envelope. The vehicle of interest is a 12-pound unmanned, flying-wing aircraft with a wingspan of 10 ft. In the modeling, the rigid-body degrees of freedom (DOFs) are defined in terms of motion of a vehicle- fixed coordinate frame, as required for flight-dynamics analysis. As a result, the state variables corresponding to the rigid-body DOFs are identical to those used in modeling a rigid vehicle, and the additional states are associated with the elastic degrees of freedom. Both body-freedom and bending-torsion flutter conditions are indicated by the model, and it is shown that the flutter speeds, frequencies, and genesis modes suggested by this low-order model agree very well with the analytical predictions and flight-test results reported in the literature. The longitudinal dynamics of the vehicle are characterized by a slightly unstable Phugoid mode, a well-damped, pitch-dominated, elastic-short-period mode, and the stable or unstable aeroelastic modes. A classical, rigid-body, short-period mode does not exist.Item Stability Augmentation and Active Flutter Suppression of a Flexible Flying-Wing Drone(2015-05-19) Schmidt, DavidIntegrated control laws are developed for stability augmentation and active flutter suppression (AFS) of a flexible, flying-wing drone. The vehicle is a 12-pound unmanned, flying- wing research aircraft with a 10 ft wingspan. AFS is flight critical since the subject vehicle is designed to flutter within its flight envelope. The critical flutter condition involves aeroelastic interactions between the rigid-body and elastic degrees of freedom; hence the control laws must simultaneously address both rigid-body stability augmentation and flutter suppression. The control-synthesis approach is motivated by the concept of Identically Located Force and Acceleration (ILAF), successfully applied on some previous operational aircraft. Based on the flutter characteristics and on conventional stability-augmentation concepts, two simple loop closures are suggested. It is shown that this control architecture robustly stabilizes the body- freedom-flutter condition, increases the damping of the second aeroelastic mode (which becomes a second flutter mode at higher velocity), and provides reasonably conventional vehicle pitch- attitude response. The critical factors limiting the performance of the feedback system are identified to be the bandwidth of the surface actuators and the pitch effectiveness of the control surfaces.Item Survey of Existing Aeroservoelastic Models(2015-05-04) Danowsky, Brian; Schmidt, DavidThis working paper documents a survey of existing mathematical models of aeroservoelastic aircraft. For the purposes of this working paper, the primary purpose of such models is for control analysis and design. Enhanced validation and simulation (piloted and non-piloted) are also important.