1–11 of 11 hits
|

    Identification of a non-linear F/A-18 model by the use of fuzzy logic and neural network methods

    Boely, N / Botez, R M / Kouba, G | SAGE Publications | 2011
    The aim of this article is to determine the mathematical model between control deflections and structural deflections in an F/A-18 modified ...

    Identification of structural surfaces' positions on an F/A-18 using the subspace identification method from flight flutter tests

    Beaulieu, M N / De Jesus Mota, S / Botez, R M | SAGE Publications | 2007
    aeroelastic deflections of specific structural parts of the NASA F/A-18 Active Aeroelastic Wing research aircraft. The flight flutter tests were ...

    On–off and proportional–integral controller for a morphing wing. Part 1: Actuation mechanism and control design

    Grigorie, T L / Popov, A V / Botez, R M et al. | SAGE Publications | 2012
    The main objective of this research work is the development of an actuation control concept for a new morphing actuation mechanism made of ...

    On–off and proportional–integral controller for a morphing wing. Part 2: Control validation – numerical simulations and experimental tests

    Grigorie, T L / Popov, A V / Botez, R M et al. | SAGE Publications | 2012
    The second part of this article describes the numerical simulation and experimental validations of actuators control system for a morphing ...

    Simulation and prediction of main rotor, tail rotor, and engine parameters from flight tests

    Beaulieu, M N / Botez, R M | SAGE Publications | 2008
    In the framework of this research project, the main rotor torque, tail rotor torque, engine torque, and main rotor speed of a helicopter in ...

    Micro-electromechanical systems gyro performance improvement through bias correction over temperature using an adaptive neural network-trained fuzzy inference system

    Grigorie, T L / Botez, R M / Lungu, M et al. | SAGE Publications | 2012
    realize an online correction of the error due to the gyro sensor’s bias variation with temperature. In the first phase, gyro experimental testing ...

    Stability derivatives for a delta-wing X-31 aircraft validated using wind tunnel test data

    Anton, N / Botez, R M / Popescu, D | SAGE Publications | 2011
    The calculation and validation of the aerodynamic coefficients and stability derivatives for the X-31 model aircraft are the focus of this ...

    Adaptive neuro-fuzzy controllers for an open-loop morphing wing system

    Grigorie, T L / Botez, R M / Popov, A V | SAGE Publications | 2009
    A new method for the realization of two neuro-fuzzy controllers for a morphing wing design application is presented here. The controllers ...

    Adaptive neuro-fuzzy inference system-based controllers for smart material actuator modelling

    Grigorie, T L / Botez, R M | SAGE Publications | 2009
    An intelligent approach for smart material actuator modelling of the actuation lines in a morphing wing system is presented, based on ...

    Flight dynamics helicopter model validation based on flight test data

    Hiliuta, A / Botez, R M | SAGE Publications | 2007
    x, y, and u of a real helicopter and in the absence of any seed matrices. The method is highly convergent, and ...

    Aerodynamic forces based on an error analytical formulation for aeroservoelasticity studies on an F/A-18 aircraft

    Biskri, D E / Botez, R M | SAGE Publications | 2006
    is presented, called the corrected minimum state (CMS), on the basis of the standard MS approximation method. This new CMS method uses an ...