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Technical Paper

Development of Variable Camber Continuous Trailing Edge Flap for Performance Adaptive Aeroelastic Wing

2015-09-15
2015-01-2565
This paper summarizes the recent development of an adaptive aeroelastic wing shaping control technology called variable camber continuous trailing edge flap (VCCTEF). As wing flexibility increases, aeroelastic interactions with aerodynamic forces and moments become an increasingly important consideration in aircraft design and aerodynamic performance. Furthermore, aeroelastic interactions with flight dynamics can result in issues with vehicle stability and control. The initial VCCTEF concept was developed in 2010 by NASA under a NASA Innovation Fund study entitled “Elastically Shaped Future Air Vehicle Concept,” which showed that highly flexible wing aerodynamic surfaces can be elastically shaped in-flight by active control of wing twist and bending deflection in order to optimize the spanwise lift distribution for drag reduction. A collaboration between NASA and Boeing Research & Technology was subsequently funded by NASA from 2012 to 2014 to further develop the VCCTEF concept.
Technical Paper

Hybrid Adaptive Flight Control with Self-Improving Plant Model for Stability and Control of Damaged Aircraft

2007-09-17
2007-01-3898
This paper presents a hybrid adaptive control method for maintaining stability and control of damaged aircraft. The hybrid method utilizes an adaptive parameter estimation scheme to improve a plant model in a flight control system. Two adaptive parameter estimation schemes are developed: 1) an indirect adaptive control law with normalization based on the Lyapunov direct method that uses tracking error for adaptation, and 2) a recursive least-squares law based on the optimal estimation method that uses plant model error for adaptation. Simulations show that the hybrid adaptive control can provide a significant improvement in the tracking performance of a flight control system.
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