This paper describes how aeroelastic tailoring, in concert with optimal composite material design, might be applied to a new generation of Unmanned Air Vehicles (UAV's) to increase range and improve lateral control effectiveness. UAV development provides a new venue for design because it encourages creativity by removing some design constraints. This paper reviews: 1) design opportunities provided by UAV missions; 2) and, aeroelastic tailoring features mat lend themselves to improved performance. The aeroelastic features discussed in this paper are: lateral control and, reduced induced drag. Our studies show that aeroelastic tailoring can increase the control reversal speed of swept wings and that different laminate designs are needed depending on whether leading edge or trailing edge controls are used. We also show that induced drag can be controlled by laminate tailoring and that in some cases drag can be reduced if the wing structural aspect ratio is low, about AR=3. PurposeUnmanned Air Vehicle (UAV) development has been identified as a future development area with potentially revolutionary outcomes. 1 Two highlighted areas for UAV's with special technological challenges are vehicles to suppress air defenses and improved high altitude observation and weapon carrying aircraft.The purposes of this paper are to • describe design opportunities provided by UAV missions and the need for increased performance• summarize the effects of controlled aeroelastic interaction with advanced composite aircraft wings that aeroelastically couple structural flexibility and wing control surfaces to improve airplane maneuverability and reduce induced drag. UAV benefits and attributesTechnological capability always runs far ahead of application to real aircraft because of the need to thoroughly consider the trade between system performance benefits from the technology and the cost of the technology. As a result, some technology can languish for years before it sees an application to a real air vehicle. Today we have few opportunities to test new technology on real flight vehicles; this situation is unlikely to change in the future. This means that worthwhile technology will take a long time to mature. On the other hand, UAV's offer low cost vehicles that can benefit from new technology.UAV literature (and that of their predecessors, the Remotely Piloted Vehicles or RPV's) is extensiveê xtending over the past few decades. 5 " It is not our purpose to review the history of UAV or RPV development since UAV's and RPV's have a long history; numerous regularly scheduled conferences have been held world-wide during the past few decades. Basic technology for RPV's is well-developed and manufacturers world-wide offer a variety of products.On the other hand, recent interest in military UAV's triggered by advances in computer information technology and navigation has opened up new possibilities.A review of the recent literature reveals many claimed UAV benefits. These include:1. Reduced human risk with increased capability for dangerous missi...
The present paper aims to develop a completely coupled thermo-piezoelectricmechanical theory, based on an improved layerwise displacement field and higher order electrical and temperature fields, to study dynamic response and control of smart composite shells. A variational principle, addressing the interaction between thermal, piezoelectric and mechanical fields, is used to derive the governing equations of equilibrium. Finite element technique is used to ensure application to practical geometry and boundary conditions. Numerical analysis is conducted for simply supported cylindrical shells with distributed selfsensing piezoelectric actuators. Control authority is investigated using Linear Quadratic Gaussian (LQG) theory. Parametric studies are conducted to investigate the effect of two-way coupling, placement of actuators, coupling and flexibility of the primary structure.
The purpose of this work is to design an active control system for flutter suppression of a laminated plate wing model using segmented piezo-actuators. We describe investigations pertaining to the optimal size, thickness and locations of piezo-actuators on a laminated plate-wing structure for flutter suppression. The analysis for the laminated composite wing model is conducted by the Ritz solution technique, which represents the displacement on the plate in terms of power series in spanwise and chordwise directions. The active control system design for flutter suppression requires the equation of motion to be expressed in a linear time-invariant state-space form. The doublet-lattice method is used to compute unsteady aerodynamic forces, which are approximated as the transfer functions of the Laplace variable by the minimum-state method combined with an optimization technique. To design the control system, linear quadratic regulator theory with output feedback is considered in this study. The feedback control gains are obtained by solving coupled nonlinear matrix equations via numerical optimization routines. The optimal geometry of piezo-actuators which minimizes the control performance index is determined by the optimization technique referred to as the sequential linear programming method. The numerical result shows a substantial saving in control effort compared with the initial model.
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