Aileron endurance test rig design based on high fidelity mathematical modeling

Prasad, Mukesh; Gangadharan, K. V.

doi:10.1007/s13272-017-0267-y

Cited by 4 publications

(6 citation statements)

References 21 publications

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“…Figure 2-13 shows the CAD model developed to aid in the design and fabrication of the aileron endurance test rig. The aerodynamic load data was based on a typical flight spectrum obtained from an aircraft manufacturer [18].…”

Section: Wing Loadingmentioning

confidence: 99%

“…Figure 2-13: Aileron endurance test rig CAD model [18] The paper presents a method to apply a moment about the control surfaces axis of rotation, through a common lever arm. However, as the aileron is actuated, the angle between the moment arm and the applied load does not remain perpendicular.…”

Section: Wing Loadingmentioning

confidence: 99%

“…The following equations were used to study the kinematic model for the second iteration: Rt = r + s (Eq. [3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19] With the above relationships and the use of MATLAB, a graphical approach was used to iterate to a final model. By setting a constant y-ratio and iterating through various x-ratios, an improved R-R-P-R design was developed.…”

Section: Figure 3-10: Cant Angle Vs Slider Displacement/load Anglementioning

confidence: 99%

“…3- 21) and (Eq. [3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21][22], the actuator's stroke requirements to achieve a 10°− 80° motion becomes a function of the distance between R1 and P4. By using the provided moment arm of 20-inches, the plots in Figure 3-23 were obtained.…”

Section: Figure 3-21: R-p-r-p Kinematic Modelmentioning

confidence: 99%

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Design and Analysis of a Dynamic Loading System for a Morphing Winglet

Buchkazanian¹

2021

Preprint

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The following thesis paper investigates the possible methods to perform a dynamic load test on a morphing winglet. A morphing winglet design capable of deflecting in the cant direction was developed by a joint partnership between Ryerson University and Bombardier Aerospace. In order to validate the model and complete a proof of concept, a loading fixture was required to test the structural integrity of the winglet under a defined load. Upon completion of an enumeration study of planar four-bar linkages, a passive R-P-R-P mechanism was designed to apply a constant perpendicular load throughout the cant motion. A design of the half size loading fixture was developed, optimized and manufactured to integrate with an existing cant module. The dynamic loading model was validated by producing a positive correlation between the theoretical analysis and the experimental results, leading to a successful proof of concept for a full scale test.

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Section: Wing Loadingmentioning

confidence: 99%

Section: Wing Loadingmentioning

confidence: 99%

Section: Figure 3-10: Cant Angle Vs Slider Displacement/load Anglementioning

confidence: 99%

Section: Figure 3-21: R-p-r-p Kinematic Modelmentioning

confidence: 99%

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Design and Analysis of a Dynamic Loading System for a Morphing Winglet

Buchkazanian¹

2021

Preprint

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“…A by-pass valve improves the performance by reducing the gain in the servo valve null region and can be used for further tuning. An important aspect is also the structural stiffness; if too low, it can cause a delay in the measured force signal, resulting in an unstable system [20].…”

Section: Introductionmentioning

confidence: 99%

Design and Implementation of a Hardware-in-the-Loop Air Load Simulation System for Testing Aerospace Actuators

Dell’Amico

2024

Actuators

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This paper presents the design and implementation of the hardware and control strategies of an electrohydraulic air load simulation system for testing aerospace actuators. The system is part of an Iron Bird, which is an energy management research platform developed in collaboration between Saab AB and Linköping University. The purpose of the air load system is to provide realistic forces on the test object through the integration of a flight simulator for full mission evaluation. The challenge with electrohydraulic force control is tackled by increasing the hydraulic capacitance from increased load cylinder dead volumes, together with a feed-forward link based on accurate modelling of the test object and load system by adopting an optimisation routine to find model parameters. The system is implemented for both an electromechanical and servohydraulic actuator as test objects with different performance requirements. The control design is based on nonlinear and linear modelling of the system, and experimental test data are used to tune the models. Finally, test results of the air load system prove its force-tracking performance.

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