Numerical Simulation of a Flexible X-Wing Flapping-Wing Micro Air Vehicle

Deng, Shuanghou; Perçin, Mustafa; Oudheusden, B.W. van; Bijl, H.; Remes, B. D. W.; Xiao, Tianhang

doi:10.2514/1.j054816

Cited by 27 publications

(27 citation statements)

References 26 publications

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“…The number of islands is equal to 10 in the Multi-Islands GA algorithm, since there are ten locally optimal solutions. But the globally optimal solution has only one, the value of F (X ) equal to 35.8 dBm 2 . The values of x and z are equal to 640.2 mm and 0.6 mm, respectively.…”

Section: Resultsmentioning

confidence: 99%

“…Unfortunately, while allowing scientists more flexibility to study the phenomena under controlled conditions, computer simulations require a substantial investment on computation time. One simulation may take many minutes, hours, days or even weeks, quickly rendering parameter studies impractical (1)(2)(3) . To meet the challenge of increasing model complexity, the process of building approximate models, or surrogate model, has gained wide acceptance from the design community (4)(5)(6) .…”

Section: Introductionmentioning

confidence: 99%

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Cruise missile head shape optimisation using an adaptive sampling surrogate model

et al. 2018

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High-precision response of the surrogate model is desired in the process of optimisation. An excessive number of sampling points will increase the cost of the calculation. The appropriate number of sampling points cannot only guarantee the accuracy of the surrogate model but also save the calculation cost. The purpose of this research is to demonstrate the eventuality of using an adaptive surrogate model for optimisation problems. The adaptive surrogate model is built on an adaptive sampling approach and an extended radial basis function (ERBF). The adaptive sampling is an approach that new sampling points are placed in the blank area and all the sampling points are uniformly distributed in the design region using Multi-Island GA. The precision of the ERBF surrogate model is checked using standard error measure to determine whether the surrogate model should be updated or not. This adaptive surrogate model is used to optimise a cruise missile head shape. Aerodynamic and stealthy performance of the cruise missile head shape are considered in this research. Different global objective function and different weight factor are used to research the aerodynamic and stealthy performance in this optimisation process. The results show that the drag is reduced with a slender head shape and the radar-cross section (RCS) value is reduced with a short head shape.

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Cruise missile head shape optimisation using an adaptive sampling surrogate model

et al. 2018

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“…The PIV system consists of a high-speed laser and two high-speed cameras which acquired images (1024 px Â 1024 px) at a rate of 5 kHz. Based on our prior experience in similar experiments with a clamped FWMAV, 18,44 we have opted for performing measurements in the wake behind the DelFly in order to avoid problems associated with laser reflections on the shiny surfaces of the wing and that of the wings blocking the camera view. The measurement plane was set normal to the free flow, behind the DelFly tail and an advective approach ('Taylor's hypothesis') was applied to reconstruct an estimate of the three-dimensional (3D) wake configuration.…”

Section: Methodsmentioning

confidence: 99%

Accurate position control of a flapping-wing robot enabling free-flight flow visualisation in a wind tunnel

Karásek

Perçin

Cunis

et al. 2019

International Journal of Micro Air Vehicles

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Flow visualisations are essential to better understand the unsteady aerodynamics of flapping wing flight. The issues inherent to animal experiments, such as poor controllability and unnatural flapping when tethered, can be avoided by using robotic flyers that promise for a more systematic and repeatable methodology. Here, we present a new flapping-wing micro air vehicle (FWMAV)-specific control approach that, by employing an external motion tracking system, achieved autonomous wind tunnel flight with a maximum root-mean-square position error of 28 mm at low speeds (0.8-1.2 m/s) and 75 mm at high speeds (2-2.4 m/s). This allowed the first free-flight flow visualisation experiments to be conducted with an FWMAV. Time-resolved stereoscopic particle image velocimetry was used to reconstruct the three-dimensional flow patterns of the FWMAV wake. A good qualitative match was found in comparison to a tethered configuration at similar conditions, suggesting that the obtained free-flight measurements are reliable and meaningful.

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“…The harmonic vibration as sine waves and random vibration as excitations are used to research the time-domain characteristic. Since the number of helicopter blades is equal to 2, the 2th order harmonic phase is half a cycle longer than the 1th order harmonic [18,19]. The th order resonant excitation is defined as follows:…”

Section: Time-domain Analysis Of Strapdown Inertial Navigation Systemmentioning

confidence: 99%

Structure modal optimization of a strapdown inertial navigation system for an electric helicopter using an adaptive surrogate model

Guo¹,

Zheng²,

Ang³

2017

J. vibroeng.

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The purpose of this research is to prove the eventuality of using a novel adaptive surrogate model for optimization problems. The adaptive surrogate model is based on iteration sampling and extended radial basis function (ERBF). This method improves the precision by a means that new sample points is placed in the blank area and all the sample points is uniformly distributed in the design region. The precision of the surrogate model is checked using standard error measure to determine whether updating the surrogate model or not. Since the prediction of modal frequencies require structure modal simulations. In order to decrease the number of computer simulations, a Multi-Island GA approach is combined with the adaptive surrogate model to find the optimum modal frequencies of a strapdown inertial navigation system for electric helicopters. The strapdown inertial navigation system is comprised of damping material, counterweight material and inertial navigation sensor. This is a multi-objective functions optimization problem since the modal frequencies are considered from mode 1 to mode 6 in this paper. Several weights of multi-objective functions are utilized to research the modal frequencies. The whole number of 15 sampling points is picked to build the primary surrogate model using Latin hypercube sampling (LHS). The results of adaptive surrogate model show that two new sampling points are needed to reform the precision of the surrogate model under the condition of 2 % confidence bounds. The structure modal optimization results show that the choice of the weights for the multi-objective functions has a major effect on the final optimum modal frequencies. Time-and frequency-domain analysis indicated that the optimum modal frequencies are far away from the excitation frequencies to avoid strapdown inertial navigation system resonance as far as possible.

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Numerical Simulation of a Flexible X-Wing Flapping-Wing Micro Air Vehicle

Abstract: 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 Popstprint of AIAA Journal, Vol. 55, No. 7 (2017), pp. 2295-2306

Cited by 27 publications

References 26 publications

Cruise missile head shape optimisation using an adaptive sampling surrogate model

Cruise missile head shape optimisation using an adaptive sampling surrogate model

Accurate position control of a flapping-wing robot enabling free-flight flow visualisation in a wind tunnel

Structure modal optimization of a strapdown inertial navigation system for an electric helicopter using an adaptive surrogate model

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