Institute of Vibration Engineering Research

MOE, China

Institute of Vibration Engineering Research

MOE, China
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Huang R.,Nanjing University of Aeronautics and Astronautics | Huang R.,Institute of Vibration Engineering Research | Hu H.,Nanjing University of Aeronautics and Astronautics | Hu H.,Institute of Vibration Engineering Research | And 2 more authors.
AIAA Journal | Year: 2014

The paper presents a novel nonlinear reduced-order modeling approach for multi-input/multi-output aerodynamic systems. The nonlinear reduced-order model for an aerodynamic system includes a finite sum of Wiener-type cascade models. The nonlinear reduced-order model approach starts with fitting a Wiener-type cascade path between the inputs and outputs of the aerodynamic system first. Then, the approach computes the outputs of the path and subtracts them from the measured outputs. The second path is then fitted between the inputs and the output residuals. This process is repeated until the residuals contain only noise. To obtain an optimal path at each stage, a novel nonlinear model, a linear dynamic state-space element followed by a single-layer neural network model, is selectedasthe Wiener-typecascade model. The Wiener-type cascademodel can be optimized by using the Levenberg-Marquadt algorithm. To demonstrate the performance of the proposed nonlinear reduced-order model in modeling the statically nonlinear and dynamically linearized behavior of a nonlinear aerodynamic system, the unsteady transonic compressible flow over a two-degree-of-freedom wing section with the NACA 64A010 airfoil is presented. The numerical results indicate that the proposed nonlinear reduced-order model can accurately identify the outputs of aerodynamic systems subject to a weak excitation. Then, the nonlinear reduced-order model is applied to the transonic flutter analysis of the Isogai wing model. Compared with the direct computational fluid dynamics and linear reduced-order model, the proposed nonlinear reduced-order model is accurate and efficient for transonic flutter prediction of nonlinear aeroelastic systems. Copyright © 2013 by the American Institute of Aeronautics and Astronautics, Inc.


Wang X.,Aerospace Dongfanghong Development Ltd. | Xu Q.,Aerospace Dongfanghong Development Ltd. | Wang T.,Aerospace Dongfanghong Development Ltd. | Wei F.,Aerospace Dongfanghong Development Ltd. | Wen H.,Institute of Vibration Engineering Research
Proceedings of the International Astronautical Congress, IAC | Year: 2013

As the developing of science, geomagnetic survey is applied quite widely. It's an exigent need to gain accurate results of geomagnetic survey. Geomagnetic is a vector field, which needs multidimensional observations to reduce the possibilities of the earth physics explanation. This paper design a constellation scheme, which is composed of five tethered formation units, one contains two satellites connected with a tether. One of the units local at the 550km equator circular orbit, the rest local at the 450km near-polar orbit. The geomagnetic survey payloads are fixed on the stretching structure on the two satellites in a formation by the super optical platform. The simulation shows that the scheme can gain accurate data of geomagnetic survey. The mode of the tethered formation keeps the payloads away from the electromagnetism disturbing of the satellite platform; further, it can achieve graduation information of the geomagnetic. In the geomagnetic survey from space, the use of constellation and tethered formation can greatly improve spatial resolution and separate the variation of time and space. Moreover, we can obtain the global geomagnetic information more quickly to separate the geomagnetic field of the interior and exterior source. ©2013 by the International Astronautical Federation. All rights reserved.


Huang R.,Nanjing University of Aeronautics and Astronautics | Huang R.,Institute of Vibration Engineering Research | Hu H.,Nanjing University of Aeronautics and Astronautics | Hu H.,Institute of Vibration Engineering Research | And 2 more authors.
Journal of Guidance, Control, and Dynamics | Year: 2012

An adaptive control scheme for linear output feedback was proposed to suppress aeroelastic vibrations on a three dimensional aeroelastic wing with unknown parameters, an external disturbance, and measurement noise. The control strategy was implemented through a trailing-edge control surface. Compared with the LQG (linear quadratic Gaussian) algorithm with residualization techniques, the proposed scheme resulted in a robust controller of reduced order. The numerical results demonstrated that the proposed control scheme suppressed the flutter of the aeroelastic model more effectively. In an ongoing research, the BGF (bounded-gain forgetting) estimator will be used in the discrete-time domain, and the proposed scheme will be testified in a low-speed wind tunnel.


Huang R.,Nanjing University of Aeronautics and Astronautics | Huang R.,Institute of Vibration Engineering Research | Zhao Y.,Nanjing University of Aeronautics and Astronautics | Zhao Y.,Institute of Vibration Engineering Research | And 2 more authors.
AIAA Journal | Year: 2016

In this study, active flutter control and closed-loop flutter identification were experimentally studied for a lowaspect-ratio wing model in an Nanhang-2 subsonic wind tunnel. To actively suppress the flutter of the wing model in wind-tunnel tests, a real-time digital control system was developed so as to complete the data acquisition, digital signal processing, computation of the control strategy, and servo control of the actuator. Using the digital control system, wind-tunnel tests were conducted to examine the flutter control of the wing model. The experimental results showed that the linear feedback controller designed via the optimization of pole assignment can effectively suppress the flutter instability. Moreover, for the high-dimensional aeroservoelastic system, the online estimation of closed-loop flutter modes is a challenging problem because the flutter identification from closed-loop measurements may lead to biased estimates, and the identification efficiency must be improved. Therefore, as the second task of this study, the online closed-loop flutter identification of the wing model was explored. To efficiently identify the flutter modes, a fast recursive subspace identification method was used. The experimental results show that the natural frequencies and modal damping ratios of the closed-loop flutter modes could be accurately tracked over a wide range of flow speeds. © 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.


Huang R.,Nanjing University of Aeronautics and Astronautics | Huang R.,Institute of Vibration Engineering Research | Qian W.M.,Nanjing University of Aeronautics and Astronautics | Qian W.M.,Institute of Vibration Engineering Research | And 4 more authors.
Journal of Aircraft | Year: 2010

A study on the flutter analysis using piecewise quadratic interpolation (PQI) with mode tracking and wind tunnel tests was conducted. As the first step of the study, the modal analysis of the wing model was made through the conventional finite-element method and the ground vibration test. In the ground vibration test, the plastic foam covering the wing model makes it difficult to measure the dynamic response of the wing model via accelerometers fixed on the foam or excite the wing model through a hammer impacting on the foam. A laser interferometer was used to measure the dynamic responses, subject to a hammer impact, at different locations on the wing model. Two ground vibration tests were performed. The wind-tunnel tests performed by the authors for a flexible wing model verify the efficacy of the revised PQI method. The experimental results show that the proposed method provides accurate predictions of flutter velocity and frequency of the wing model.


Qian W.,Nanjing University of Aeronautics and Astronautics | Qian W.,Institute of Vibration Engineering Research | Huang R.,Nanjing University of Aeronautics and Astronautics | Huang R.,Institute of Vibration Engineering Research | And 4 more authors.
Journal of Aircraft | Year: 2013

A study was conducted to present a new scheme to model the state-space LFT system of a multiple-actuated wing (MAW) with airspeed and air-density uncertainties so as to reduce the dimension of the resulting uncertainty block. The mathematical model of the robust aeroservoelastic (ASE) system was established and the linear fractional transformation (LFT) model of the ASE system with airspeed uncertainty was derived by using Moulin's method and new scheme. The LFT model of the ASE system with airspeed and air-density variations was also presented. Two kinds of μ controllers, such as a single-input/single-output (SISO) controller and a multi-input/multi-output (MIMO) controller, were presented to suppress the flutter instability of the MAW model incorporating airspeed and air-density variations.

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