|Statement||by W. D. T. Hicks.|
|Series||Aeronautical Research Council. Current papers, no. 1045, Current papers (Aeronautical Research Council (Great Britain)) ;, no. 1045.|
|LC Classifications||TL507 .G77 no. 1045|
|The Physical Object|
|Pagination||, 18 p., 8 plates.|
|Number of Pages||18|
|LC Control Number||78512277|
The active control of aeroelastic systems, sometimes known as aeroservoelasticity, has as its objective the modification of the aeroelastic behavior of the system by the introduction of deliberate control forces. Aeroelastic control is in fact an intersection of aeroelasticity and of controlled structures technology (Figure ). Therefore, the reduced-order model is required by synthesis for avoidance of large computation cost and high-order controller. This paper proposes a new procedure for generation of accurate reduced-order linear time-invariant (LTI) models by using system identification from flutter testing data. The proposed approach is in two by: Global Robust Control of Aeroelastic System Using Output Feedback Article in Journal of Guidance Control and Dynamics January with 10 Reads How we measure 'reads'. Afterwards, with the identified online aeroelastic model and its uncertainty, a robust generalized predictive control (GPC) is applied to alleviate the wing tip acceleration at all test conditions.
AIRCRAFT AEROELASTIC DESIGN AND ANALYSIS An introduction to fundamental concepts of static and dynamic aeroelasticity - with simple idealized models and mathematics to describe the essential features of aeroelastic problems. These notes are intended for the use of Purdue University students enrolled in AAE Several examples of experimental model designs, wind tunnel tests and correlation with new theory are presented in this paper. The goal is not only to evaluate a new theory, new computational method or new aeroelastic phonomenon, but also to provide new insights into nonlinear aeroelastic phenomena, flutter, limit cycle oscillation (LCO) and gust by: 5. The system is subject to a modal convergence flutter response above a critical wind speed and then oscillates in a limit cycle at higher wind speeds. A linearized analytical model of the device is derived to include the effects of the three-way coupling between the structural, unsteady aerodynamic, and electrical aspects of the by: A sketch of the aeroelastic model representation is shown in Figure 1. In this work, the soft-ware Nastran  is used to represent the dynamic model (stiffness and mass distribution) and the software ZAERO  is used to represent the aerodynamic model and the splines. The aerody-namic model of ZAERO employed in this work is the Zona6 method.
A variety of model order reduction techniques have been developed to reduce high-order aeroelastic model into a reduced-order state-space model while dominant behavior of the system is retained. 8 The effort in this field includes balanced realization and truncation 9, Krylov-based projection 10 and hybrid SVD-Krylov appro and proper Cited by: Model-free adaptive optimal controller design for aeroelastic system with input constraints 26 December | International Journal of Advanced Robotic Systems, Vol. 14, No. 1 Active flutter suppression using UDE based sliding mode controlCited by: Identification and Control of Limit Cycle Oscillations in Aeroelastic Systems. 8 August | Journal of Dynamic Systems, Measurement, and Control, Vol. , No. 6. Transonic Aeroelastic Instability Suppression for a Swept Wing by Targeted Energy by: Hygiena's™ SystemSURE Plus is the world's best-selling ATP Sanitation Monitoring System. With improved functionality, new software, and increased memory, the SystemSURE Plus meets the demands of the largest and smallest companies around the world. The SystemSURE line of ATP monitoring systems has been used for over 10 years.