Support Interference Computations of Forced Oscillation Test for a Flying-Wing Dynamic Model

Wu, Jianbo; Feng, Shuai; Wang, Yanling; Shen, Yanjie; Bu, Chen

doi:10.1007/978-981-13-3305-7_28

Cited by 1 publication

(2 citation statements)

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“…Some of the studies only focus on the theoretical analyses of the BFF [9,10,13,14]. The experimental studies on flying wings such as the ground vibration test (GVT) [15], wind tunnel test [16,17], and flight test [18,19] have made significant signs of progress recently. Zhao et al [15] introduced an optimization method for composite flying-wing finite element model (FEM) updating based on subcomponent test data.…”

Section: Introductionmentioning

confidence: 99%

“…Liu et al [17] pointed out that for the flying wing with two-points elastic support, the flutter characteristics obtained from the BFF wind tunnel test will be affected by the support stiffness of spring. Zhang et al [18] and Wu et al [19], respectively, using numerical simulation and wind tunnel tests, proved that the support system will interfere with the wind tunnel test results and cannot accurately simulate the actual flight state. Therefore, it is necessary to carry out a flight test to study the BFF of flying wings.…”

Section: Introductionmentioning

confidence: 99%

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The Development of a Flight Test Platform to Study the Body Freedom Flutter of BWB Flying Wings

Shi

Liu

et al. 2021

Aerospace

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A flight test platform is designed to conduct an experimental study on the body freedom flutter of a BWB flying wing, and a flight test is performed by using the proposed platform. A finite element model of structural dynamics is built, and unsteady aerodynamics and aeroelastic characteristics of the flying wing are analyzed by the doublet lattice method and g-method, respectively. Based on the foregoing analyses, a low-cost and low-risk flying-wing test platform is designed and manufactured. Then, the ground vibration test is implemented, and according to its results, the structural dynamics model is updated. The flight test campaign shows that the body freedom flutter occurs at low flight speed, which is consistent with the updated analytical result. Finally, an active flutter suppression controller is designed using a genetic algorithm for the developed flying wing for future tests, considering the gains and sensor location as design parameters. The open- and closed-loop analyses in time- and frequency-domain analyses demonstrate that the designed controller can improve the instability boundary of the closed-loop system effectively.

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