Gust load prediction and alleviation on a fighter aircraft

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    Our highly experienced staff provide complete test and analysis services and bring extensive troubleshooting experience to the process, reducing risk, cost, and schedule. All rights reserved. Legal Notices. Flutter Analysis ATA has performed aeroelastic analyses for many aerospace systems ranging from individual lifting surface components to full aircraft with closed-loop control systems. Aircraft Loads Analysis ATA provides aircraft loads analysis services including aeroelastic loads prediction and loads-driven aircraft design optimization.

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    Model Correlation and Updating A test-correlated finite element model FEM is needed to confidently predict the aeroelastic stability of an aircraft and demonstrate that flight envelopes are free of flutter instabilities and vehicles are safe for flight testing. Flutter Flight Test Support ATA provides flight test planning, instrumentation, and data analysis during flutter flight tests—streaming and reviewing data live during the test.

    Related Technical Papers Whitney, M. Seitz, and E. Blades, E. Ruth, and H. Louis, Missouri, April Reston: AIAA; Dynamic response of highly flexible flying wings. AIAA J ;49 2 Rapid prediction of worst case gust loads. Rapid prediction ofworst case gust loads following structural modification. McLean D. Gust load alleviation control systems for aircraft. Proceed IEEE ; 7 Gust load alleviation control for very flexible aircraft.

    Gust response sensitivity characteristics of very flexible aircraft. Gust response for flexibly suspended high-aspect ratio wings. AIAA J ;48 10 Investigation of optimal control allocation for gust load alleviation in flight control. Robust gust alleviation and stabilization of very flexible aircraft. AIAA J ;51 2 Model-predictive gust load alleviation controller for a highly flexible aircraft.

    J Guidance, Control, Dyn ;35 6 Design gust alleviation controller for highly flexible solar UAV. In: Third international conference on measuring technology and mechatronics automation; , vol. Effect of adaptive material properties on static aeroelastic control. Reston: AIAA. Report No. Static aeroelastic control of an adaptive lifting surface. J Aircraft ;30 4 Lift efficient composite flexible wing for rolling maneuver without ailerons. Flexible composite wing internal actuation for roll maneuver.

    J Aircraft ;39 4 Modeling of high aspect ratio active flexible wings for roll control. Controlling panel flutter using adaptive materials. Hajela P, Glowasky R. Application of piezoelectric element in supersonic panel flutter suppression. Heeg J. Analytical and experimental investigation of flutter suppression by piezoelectric actuation. Washington, D.

    Open and closed loop results of a strain actuated active aeroelastic wing.

    Publications

    J Aircraft ;33 5 Multivariable active lifting surface control using strain actuation: analytical and experimental results. J Aircraft ;34 3 An active smart material system for buffet load alleviation. Florida state Orlando. Distribution of measuring points and piezoelectric actuators in flutter suppression.

    Chin J Aeronaut ;15 1 Flutter suppression using distributed piezoelectric actuators. Active flutter suppression for wing using distributed piezoelectric actuator under thermal circumstances. J Astronaut ;31 12 [Chinese]. Active aeroelastic wing design for gust load alleviation and flutter suppression. Heinze S, Karpel M. Analysis and wind tunnel testing of a piezoelectric tab for aeroelastic control applications. J Aircraft ;43 6 Tsushima N, Su WH. Active piezoelectric actuation and control of highly flexible multifunctional wings. Effect of piezoelectric damping layers on the dynamic stability of plate under a thrust.

    J Sound Vib ; Control of beam vibrations by means of piezoelectric devices: theory and experiments. Compos Struct ;50 4 Electromechanical modeling and normal form analysis of an aeroelastic micro-power generator. J Intell Mater Syst Struct ;22 6 Energy harvesting from limit cycle oscillation of a cantilever plate in low subsonic flow by ionic polymer metal composite.

    J Aerosp Eng ; 5 J Smart Mater Struct ;20 5 Li FM. Active aeroelastic flutter suppression of a supersonic plate with piezoelectric material. Int J Eng Sci ;51 2 Albano E, Rodden WP. A doublet-lattice method for calculating lift distributions on oscillating surfaces in subsonic flows. AIAA J ;7 2 Karpel M. Design for active and passive flutter suppression and gust alleviation. Flow field analysis and experimental investigation on gust generator. Bi Ying is a Ph. Her area of research includes aeroelasticity, gust responses, gust alleviation, and active control.

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    His major research interests are aeroelasticity and flight dynamics of flexible aircraft, aerodynamics, and structure dynamics. An Chao is a Ph. His main research areas are aeroelasticity and flight dynamics of flexible aircraft. Yang Chao is a professor and Ph. His current research interests are aeroelasticity and active control. Gust load alleviation wind tunnel tests of a large-aspect-ratio flexible wing with piezoelectric control Academic research paper on " Mechanical engineering ".

    Abstract of research paper on Mechanical engineering, author of scientific article — Ying Bi, Changchuan Xie, Chao An, Chao Yang Abstract An active control technique utilizing piezoelectric actuators to alleviate gust-response loads of a large-aspect-ratio flexible wing is investigated. Similar topics of scientific paper in Mechanical engineering , author of scholarly article — Ying Bi, Changchuan Xie, Chao An, Chao Yang Gust response analysis and wind tunnel test for a high-aspect ratio wing.

    High-altitude long-endurance unmanned aerial vehicles 21 com C. In order to satisfy the requirement of long endurance, large- 24 aspect-ratio wings are commonly used because of their high 25 lift-drag ratio and low structural weight, for example, the Glo- 26 bal Hawk, the Helios, and the Sensorcraft with a flying wing 27 configuration. CJA 26 December 2 Y. Bi et al.

    Among them, 35 Su and Cesnik2 investigated gust response coupling with flight 36 dynamics of a flexible flying wing. They studied the effects of 37 flexibility, loading distribution, and gust disturbance and 38 found that finite gust disturbances could bring the flying wing 39 to a strong unstable divergence response.

    Khodaparast et al. In comparison to gust anal- 44 ysis methods, there have been more studies in the literature 45 addressing gust load alleviation GLA control problems. Several control methods have shown a positive effect 50 on reducing gust-response loads. Dillsaver et al.

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    Tang et al. Frost 60 et al. Cook et al. They com- 64 pared closed-loop responses with open-loop dynamics for both 65 linearized and nonlinear systems to discrete gust distributions 66 and showed that the robust controller could give a good per- 67 formance in different cases.

    Haghighat and Liu11 completed 68 gust load alleviation of flexible aircraft adopting a model pre- 69 diction technique and demonstrated the load alleviation effec- 70 tiveness of the controller for an aircraft encountering discrete 71 and continuous atmospheric disturbances. Wang et al. Under certain circumstances, 79 flexible aircraft exhibit large root bending moments which 80 could shorten the strength and fatigue life of the structure sig- 81 nificantly.

    Hence, gust load alleviation control which can 82 accomplish multi-objective alleviation including reducing 83 accelerations and root bending moments for flexible aircraft 84 is needed. In addition, there has been little research in different 85 sorts of control actuating methods. A conventional control 86 surface has its own limitations such as limited deflection angles 87 and low frequency band, besides they are mainly used in flight 88 stability and maneuver load control, so there is not enough 89 space for the limits of control authority applied on gust load alleviation.

    Exploration of new control actuation techniques 90 is one key research aspect in this paper. More- 94 over, piezoelectric materials have shown a great application 95 value in aeroelastic control because of their low weight, fast 96 responsibility, simple driving device, high energy efficiency, 97 and flexible distribution.