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O k l a h a m S t a t e U l i v e r s i t y S t i l l w a t e r , Oklahana Abstract A review is given o f some o f the major advancements of the past t h i r t y years i n the design of flight control systems for elastic aircraft. The early research programs leading t o the current Active Control Technology (ACT) and Control Configured Vehicles (C CV) applications are highlighted.The ACT/CCV functions include (1) lmproved ride qualities, (2) lmproved handling qualities, (3) Relaxed static stability, (4) Flutter suppression, (5) Structural loads reduction,Structural fatigue l i f e improvement.A selective, but extensive, reference list is included. lntroduct ion This paper is intended as a limited survey of the advancements of about the past t h i r t y years in the design of flight control systems for elastic aircraft; During atmospheric flight, static and dynamic aeroelastic deflections of aircraft and launch vehicle structures modify the aerodynamic pressure distributions which result in changes t o the stability derivatives used i n the vehicle small perturbation equations of motion. Such equations are required for an accurate and complete plant dynamics mathematical model used i n the synthesis of attitude and stability augmentation, ride control, f l u t t e r suppression, structural mode control, and load alleviation systems. Early attempts t o account for aeroelastic effects on aircraft stability and control took the approach of making static aeroelastic corrections t o the rigid body aerodynamic stability derivatives. References 1-4 are representative of this research.When the dynamic effects of flexibility are sufficiently important that they must be included as additional degrees of freedom, a common approach has been t o approximate the dynamics by a truncated set of orthogonal normal vibration modes. In this case, Associate Dean, College of Engineering, Architecture and Technology Associate Fellow AlAA
O k l a h a m S t a t e U l i v e r s i t y S t i l l w a t e r , Oklahana Abstract A review is given o f some o f the major advancements of the past t h i r t y years i n the design of flight control systems for elastic aircraft. The early research programs leading t o the current Active Control Technology (ACT) and Control Configured Vehicles (C CV) applications are highlighted.The ACT/CCV functions include (1) lmproved ride qualities, (2) lmproved handling qualities, (3) Relaxed static stability, (4) Flutter suppression, (5) Structural loads reduction,Structural fatigue l i f e improvement.A selective, but extensive, reference list is included. lntroduct ion This paper is intended as a limited survey of the advancements of about the past t h i r t y years in the design of flight control systems for elastic aircraft; During atmospheric flight, static and dynamic aeroelastic deflections of aircraft and launch vehicle structures modify the aerodynamic pressure distributions which result in changes t o the stability derivatives used i n the vehicle small perturbation equations of motion. Such equations are required for an accurate and complete plant dynamics mathematical model used i n the synthesis of attitude and stability augmentation, ride control, f l u t t e r suppression, structural mode control, and load alleviation systems. Early attempts t o account for aeroelastic effects on aircraft stability and control took the approach of making static aeroelastic corrections t o the rigid body aerodynamic stability derivatives. References 1-4 are representative of this research.When the dynamic effects of flexibility are sufficiently important that they must be included as additional degrees of freedom, a common approach has been t o approximate the dynamics by a truncated set of orthogonal normal vibration modes. In this case, Associate Dean, College of Engineering, Architecture and Technology Associate Fellow AlAA
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