System identification methods for aircraft flight control development and validation

Tischler, Mark B.

doi:10.1201/9781315136820-2

Cited by 34 publications

(21 citation statements)

References 13 publications

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“…Modeling of industrial systems such as robot manipulators has an important role in designing modelreference controllers and model-reference fault indicators. Tischler [11] introduced various system identification techniques to control aircraft. A review of various techniques for nonlinear system identification methods is proposed in [12].…”

Section: Related Workmentioning

confidence: 99%

Adaptive Finite-Time Convergence Fuzzy ARXLaguerre System Estimation

Piltan¹,

TayebiHaghighi²,

Sahamijoo³

et al. 2019

IJISA

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Convergence speed for system identification and estimation is a popular topic for determining the kinematics and dynamic identification/estimation of the parameters of robot manipulators. In this paper, adaptive fuzzy inverse dynamic system estimation is used to improve robust modeling, especially for a serial links robot manipulator. The Lyapunov technique is used to analyze the convergence rate of the tracking error and increase the accuracy response of the parameter estimation. Performance of robot estimation is conducted, and the results show fast convergence of the proposed finite time technique for a 6-DOF robot manipulator.Index Terms-Finite-time, robot manipulator, fuzzy logic inverse dynamic modeling, parameter estimation, unknown dynamic parameters.

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Section: Related Workmentioning

confidence: 99%

Adaptive Finite-Time Convergence Fuzzy ARXLaguerre System Estimation

Piltan¹,

TayebiHaghighi²,

Sahamijoo³

et al. 2019

IJISA

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“…The concepts of "maximum unnoticed added dynamics" (MUAD) [1][2][3] or "maximum allowable errors" (AE) 4 are traditionally used in studies of aircraft handling qualities, [5][6][7][8][9][10][11][12][13] to formalize the human pilot's sensitivity to the specific dynamics of his controlled aircraft. This sensitivity is generally expressed as a frequency-domain (MUAD or AE) envelope within which any added dynamics (e.g., augmented systems, system failures) to the original aircraft dynamics will remain unnoticed by the pilot.…”

Section: Introductionmentioning

confidence: 99%

Manual Control Adaptation to Variations in Short-Period Natural Frequency and Damping

Fasiello

Lü

Pool

et al. 2019

AIAA Scitech 2019 Forum

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This paper presents the results of a human-in-the-loop experiment performed to investigate the effects of variations in aircraft short-period mode characteristics on human operators' manual control behavior. In the experiment, 15 participants performed a tracking task for a factorial variation in both short-period mode natural frequency (five settings) and damping ratio (three settings). The baseline aircraft dynamics were those of a Cessna Citation aircraft, as used in a number of previous experiments, and the variations in short-period dynamics were chosen to span a range of interest with respect to available handling qualities criteria and Maximum Unnoticed Added Dynamics (MUAD) envelopes. To objectively quantify the induced adaptation of manual control behavior, human operator models were fitted to the collected tracking data. In addition to these control behavior measures also subjective ratings of the noticeability of differences with respect to the baseline aircraft were collected. Overall, the results show consistent adaptation of manual control behavior to variations in both short-period parameters and a worsening of task performance with decreased short-period natural frequency and decreased damping ratio settings. In spite of inconsistencies in the subjective rating data, the overall objective adaptation of manual control dynamics correlates with the subjective noticeability ratings, as well as correspondence of the tested configurations with available MUAD envelopes.

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“…Results showed that the maximum stress occurs at distance of 0-15% from the edge of wing by using software program (ANSYS11). it used pressure distribution on the wing to know the distribution of tension and displacement of the structure of the wing (Marqués, 2017, Tischler, 2018.…”

Section: Introductionmentioning

confidence: 99%

Pseudorandom Noise Impulsive Response Analysis and Aerodynamic Forces of Unmanned Aerial Vehicle Structure

Salman¹,

Mohsen²,

Abttan³

2019

ujme

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This paper concentrated about the effect of both the pseudorandom or random vibration (wind waves) and aerodynamic forces on the wing of unmanned aerial vehicle, which brought the attention of specialists in this field during last years, the performance of wing is improved on a definitive solution for the vibration problems which cause failure in the wings of UAV. The distribution of stresses and distortions with aerodynamic loads is studied. Factors such as tension, pressure and shear stress showed on wing of UAVs due to vibration which caused the structure of wing to break down and then failure. The experimental study was carried out by using wing made of composite material (foam and cover by lamination plate), where airfoil type (NACA Clark y) installed inside wind tunnel of low velocity. It is found that the vibration acceleration at constant wind velocity with variation of attack angle of the wing, it is obtained the relationship between the acceleration and the frequency using the LABVEIW program which analyzed and identified the distribution of forces on the wing. The stress concentration areas is created and found under failure occurs, the aerodynamic force, torsion torque and magnitude of deformation is calculated. It is concluded that the close areas from the root wing (fixed end) is most likely to collapse or break.

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System identification methods for aircraft flight control development and validation

Cited by 34 publications

References 13 publications

Adaptive Finite-Time Convergence Fuzzy ARXLaguerre System Estimation

Adaptive Finite-Time Convergence Fuzzy ARXLaguerre System Estimation

Manual Control Adaptation to Variations in Short-Period Natural Frequency and Damping

Pseudorandom Noise Impulsive Response Analysis and Aerodynamic Forces of Unmanned Aerial Vehicle Structure

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