Aeroservoelastic Modelling and Analysis of a Missile Control Surface with a Nonlinear Electromechanical Actuator

Mehmet Ozan, Nalcı
Kayran, Altan
In this study, aeroservoelastic modeling and analysis of a missile control surface which is operated and controlled by a power limited, nonlinear electromechanical actuator is performed. Linear models of the control fin structure and aerodynamics together with the nonlinear servo-actuation system are built and integrated. The resulting aeroservoelastic system is analyzed both in time and frequency domain. Structural model of the control fin is based on the finite element model of the fin. Aerodynamic model of the control fin is based on the Generalized Aerodynamic Force (GAF) Matrix model which is generated in accordance with the finite element model of the fin. In order to be able to represent the aerodynamic forces in the continuous frequency domain, and the time domain, a rational function approximation formulation of the GAF matrices is utilized. Both the elastic and the rigid body motion of the missile control fin are modeled through modal discretization, so that the interaction between the aeroelastic system and the control system dynamics can be treated appropriately. A PD controller synthesis is carried out using the Root Locus Method, by neglecting the flexibility of the fin and unsteady aerodynamic effects on the fin, as if the fin is rigid and the aerodynamics is steady. The shortcomings of these assumptions are discussed under the effect of aeroelastic loading. A third order servoactuation system together with the PD controller is integrated to the aeroelastic system, so that the limit cycle oscillations of the aeroservoelastic system due to power limit saturation could be studied. Two alternative, common position feedback paths for the PD controller are used and the resulting aeroservoelastic systems are simulated in response to various control commands. It is shown that the stability and dynamic performance of the aeroservoelastic system also depends on the selection of the feedback path, when aeroelastic dynamics is present.
IAA AVIATION 2014 -AIAA Atmospheric Flight Mechanics Conference 2014


Numerical and experimantal analysis of flapping motion
Sarıgöl, Ebru; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2007)
The aerodynamics of two-dimensional and three-dimensional flapping motion in hover is analyzed in incompressible, laminar flow at low Reynolds number regime. The aim of this study is to understand the physics and the underlying mechanisms of the flapping motion using both numerical tools (Direct Numerical Simulation) and experimental tools (Particle Image Velocimetry PIV technique). Numerical analyses cover both two-dimensional and three-dimensional configurations for different parameters using two differen...
Aerodynamic parameter estimation using flight test data
Kutluay, Ümit; Platin, Bülent Emre; Mahmutyazıcıoğlu, Gökmen; Department of Mechanical Engineering (2011)
This doctoral study aims to develop a methodology for use in determining aerodynamic models and parameters from actual flight test data for different types of autonomous flight vehicles. The stepwise regression method and equation error method are utilized for the aerodynamic model identification and parameter estimation. A closed loop aerodynamic parameter estimation approach is also applied in this study which can be used to fine tune the model parameters. Genetic algorithm is used as the optimization ker...
Aerodynamic parameter estimation of a supersonic missile with rapid speed variation by using kalman filtering
Bayoğlu, Tuğba; Kutay, Ali Türker; Department of Aerospace Engineering (2016)
This study aims to develop an approach for the aerodynamic parameter estimation problem for supersonic air to air missile with rapid speed variation, as well as large variation of aerodynamic parameters with respect to Mach number. In literature, most of the estimation techniques require that estimator is time independent. Therefore, most of the aerodynamic parameter estimation methods are applied for air vehicles which have control over their speed or which can operate at relatively constant Mach number so...
Aeroservoelastic analysis and robust controller synthesis for flutter suppression of air vehicle control actuation systems
Akmeşe, Alper; Platin, Bülent Emre; Department of Mechanical Engineering (2006)
Flutter is one of the most important phenomena in which aerodynamic surfaces become unstable in certain flight conditions. Since the 1930’s many studies were conducted in the areas of flutter prediction in design stage, research of design methods for flutter prevention, derivation and confirmation of flutter flight envelopes via tests, and in similar subjects for aircraft wings. With the use of controllers in 1960’s, studies on the active flutter suppression began. First the classical controllers were used....
Aeroservoelastic modeling of a missile control
Nalcı, Mehmet Ozan; Kayran, Altan; Department of Aerospace Engineering (2013)
In this thesis, aeroservoelastic modeling of a typical Missile Control Fin was performed. MSC®PATRAN, MSC®NASTRAN, MSC®FlightLoads and Dynamics, MATLAB® and MATLAB®Simulink were used for technical computing, modeling and simulation throughout the study. Linear models of the control fin structure, aerodynamics and servo-actuator system were developed, so as to be able to analyze the aeroservoelastic system in frequency and time domains. The flutter characteristics of the missile control fin for different fli...
Citation Formats
N. Mehmet Ozan and A. Kayran, “Aeroservoelastic Modelling and Analysis of a Missile Control Surface with a Nonlinear Electromechanical Actuator,” presented at the IAA AVIATION 2014 -AIAA Atmospheric Flight Mechanics Conference 2014, Atlanta, GA; United States, 2014, Accessed: 00, 2021. [Online]. Available: