Yunhai Wang1 , Jinglong Han2 , Zhang Bin3
1, 2State Key Lab of Mechanics and Control for Mechanical Structures Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, P. R. China
3School of Mechanical and Automotive Engineering Hefei University of Technology, Anhui, 230009, P. R. China
Journal of Vibroengineering, Vol. 16, Issue 3, 2014, p. 1564-1573.
Received 31 January 2014; received in revised form 21 April 2014; accepted 6 May 2014; published 15 May 2014
Copyright © 2014 JVE International Ltd. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
Volterra series is one of the powerful system identification methods for representing the nonlinear dynamic system behavior. The methods of step response and impulse response are commonly applied to a discrete aerodynamic Computational Fluid Dynamic (CFD) to identify the first- and second-order Volterra kernels. A critical problem, however, is the difficulty of identifying the second-order Volterra kernels correctly in CFD-based method. In this paper the second-order Volterra kernel function is expanded in terms of Chebyshev functions to reduce the size of the problem and the accuracy of the identification is also improved based on a third-order reduced model of Volterra series.
Keywords: system identification, Chebyshev expansion method, Volterra series.
Nowadays, the most powerful and sophisticated tools for predicting nonlinear unsteady aerodynamic characteristics are being developed in the field of computational fluid dynamics (CFD). The application of CFD codes involves, in general, the application of the discretized Navier-Stokes (NS) equations. For the case where flow-induced nonlinearities at transonic flight conditions are significant in the aerodynamic response, time integration of the nonlinear equations is necessary. Using CFD codes the computational costs become prohibitively expensive, both in terms of CPU costs and turnaround time. This can be on the order of hours or days, depending on the user’s computer, the complexity of the structure model and the condition of flow field. This disadvantage really restricts its applications combining with other disciplines; especially in the design of aircraft control systems and aeroelastic systems.
Attempts to address this problem include the development of transonic indicial responses and impulse responses. Another approach to reduce the computational cost of CFD codes is to linearize the response about a nonlinear steady-state condition, obtain a linear state-space representation of the system of interest. If a linearized aerodynamic model from a CFD model is preferred, the method of the step or pulse input can be applied. In the identification fields, other methods or manners can also be employed. For examples: wavelet approximation and scale transformation, POD method, Volterra variational approach, neural network, incremental harmonic balance methods for airfoil flutter, etc [1-5].
The discrete impulse input was first suggested by Silva  in his dissertation to identify the Volterra kernels of nonlinear aerodynamic systems using the CFL3D code. Three conditions should be satisfied that 1) the kernels, input function, and subsequently, the output function are real-valued functions; 2) the system is causal; 3) the system is time invariant. Continuing on the work of Silva, Raveh generated a reduced-order model (ROM) by using step responses as the ROM’s kernels, for evaluation of generalized aerodynamic force (GAF) matrices. Raveh’s work  showed a better accuracy as compared to the Volterra ROM based on impulse response. CFD analysis shows that a step response, in contrast with an impulse method, is less prone to numerical problem and the identification of step-type kernels is less sensitive to such error. Raveh’s work also showed that it was difficult to identify the second-order Volterra kernels correctly for a particular aerodynamic problem.
There are mainly two reasons listed below:
a) The numerical limitations restrict the impulse/step maximum input amplitude and the minimum time step which can be accurately handled by the CFD numerical scheme. Whichever a pulse-response or a step-response method is used, the data needed for the identification of second-order kernel function is huge.
b) Based on the second-order ROM the second-order kernel function is difficult to be identified correctly.
In this paper, we first set up a third-order Volterra ROM to improve the accuracy of identification and then try to identify the second-order kernel function by using an alternative method, called Chebyshev expansion method. This identification technique does not strongly rely on the entire input and output data produced by CFD simulation. That means a colossal waste of time can be saved.
In Section 2, we briefly introduce the conceptions of Chebyshev polynomials, Volterra series and discrete impulse input. Next, we introduce first- and second-order ROM respectively. In Section 3, we put forward to the third-order ROM. Finally, we propose the identification method of Chebyshev polynomials. A CFD numerical scheme is employed to compute the aerodynamic forces of NACA0012 airfoil as the data for identification in transonic flow.
Chebyshev polynomial method is not new; however fewer authors investigated and attempted to apply it into identification in aerodynamics . This method can be classified as parameter identification. Using it needs two steps to fulfill the identification of second-order kernels of a nonlinear system. The first step is called second-kernels decomposition. The second-order kernels can be represented in two orthogonal Chebyshev polynomials’ product and then sum up.
Chebyshev polynomials can be expressed in the form below:
All the Chebyshev polynomials form a complete orthogonal set on the interval with respect to the weighting function. It can be show below:
The second-order kernels can be expressed in term of the orthogonal basis set as:
where are coefficients need to be identified.
In 1887, Volterra first studied some nonlinear problems by employing series. The Volterra theory was developed in 1930. The concepts of the identification of linear or nonlinear systems were definitely proposed by Wiener in 1958. Consequently, Volterra series has been applied into various fields, such as system identification, aerodynamic systems, signal and image processing system, adaptive control systems, defect diagnosis, noise suppressing, predictive modeling, etc.
Volterra series can be applied into modeling a time-variant or time-invariant system in time domain or frequent domain. In this paper, we focus on the time-domain Volterra theory because CFD analyses are typically performed in the time domain. We only study on time-invariant nonlinear aerodynamic systems [9-13].
If a time-invariant nonlinear system can be modeled by Volterra series, it has the continuous time form below:
where is the response of the nonlinear system to the input , an arbitrary input; is a steady value which can be computed by executing CFD code; is the nth kernel of the nonlinear system.
Using the impulse response method to kernels’ identification, the so-called unit impulse input in a continuous or discrete system is defined by:
Based on the Volterra theory the first-order ROM [14-16] in a continuous or discrete system has the form below:
where is called the linear kernel function.
By employing the impulse input , the linear kernel can be identified in a continuous or discrete form below:
Similarly, the second-order ROM can be modeled in a continuous form below:
where , are called first- and second-order kernels respectively.
In a continuous or discrete form, by employing impulse input , one can obtain:
Similarly, employing impulse input , one can obtain:
For simplicity, in the following sections, only discrete expression will be shown.
Then, the first-kernels in a discrete form is represented by:
In order to identify the second-order kernels of a discrete nonlinear system, the so-called double impulse function is defined as:
where is a constant, an arbitrary real number; represents the numbers of time interval between the two pulses in a discrete system.
Feeding Eq. (13) into the counterpart of Eq. (8), namely equation in a discrete form, one can obtain:
where is the response to the input , .
Under the time-invariant hypothesis, by using Eqs. (9) and (11), Eq. (14) can be represented as:
Hence, the second-order kernel's function has the form below:
In a summary, in the first-order ROM of a nonlinear system of interest, there is only a linear kernel function which needs to be identified. In the second-order ROM, the first-order kernels’ function is quite different from the linear kernels' function in the first-order ROM. One can see it from Eqs. (7) and (12). That implies the kernels identified from the higher-order ROM is more near to the true kernels of nonlinear systems.
As mentioned in the section of introduction, the second-order kernels sometimes can’t be identified correctly. In order to improve it, the higher-order ROM is proposed here. In a discrete system, it has the form below:
Similarly to the process of identification of second-order ROM, firstly let:
Next, feed them into Eq. (17). It follows:
where , .
The first-order kernels and the components of the second-order kernels obtained by solving Eq. (19) have the forms below:
Feeding into Eq. (17), it follows:
where those third-order kernels’ terms are omitted since they are very smaller.
One can obtain the second-order kernels in the form as following:
where , are defined by Eqs. (20) and (21) respectively; can be evacuated by a time shift of according to the time-invariant hypothesis.
In the study of aerodynamics, the common methods include impulse-response method and step-response method. All the data for identification come from executing CFD numerical scheme. Before executing CFD code, the amplitude of an input must be chosen carefully whatever using an impulse-or step-response method since it may arise in different nonlinearities.
In order to identify the second-order kernels correctly, the third-order ROM is introduced here rather than the low-order ROMs studied by many other authors. One of them, Raveh , ever claimed in his paper that the problem to correctly identify the second-order kernels of nonlinear systems was quite difficult to a particular application.
For a simple nonlinear circuit system [1, 18], the governing equation is given below:
where is an input of voltage; is the output of the current around the circuit.
This nonlinear system can be remodeled by the second-order ROM as seen in Eq. (8). Using Eqs. (12) and (16), the first- and second-order kernels can be evacuated in an impulse-response method. They are presented in Figs. 1 and 2. As can be seen, the second-order kernel function is quite small in magnitude as compared to the first-order kernel function and goes to zero very quickly as well as the first-order kernel. Figs. 1 and 2 indicate that nonlinear effects are quite small.
Fig. 1. First-kernel function of Riccati equation
Fig. 2. Second-kernel curve of Riccati equation
Using Chebyshev polynomials method for identification of the second kernel mentioned as in Eq. (3), the first thing is that we have to determine how many basis functions are properly chosen? Here, by testing after several times we find out that the number of basis functions is between 10 and 12. Hence, there are fifty-five coefficients need to be identified if we choose the number 10. Based on the orthogonal properties of Chebyshev polynomials, see in Eq. (2), all the coefficients can be evacuated. Substituting them into Eq. (3), one can obtain the second-order kernel function which is presented in Fig. 3.
Let –1, the second-order kernels identified respectively by using an impulse-response method and Chebyshev polynomials method are presented in Fig. 4.
This example illustrates Chebyshev polynomials method can be used for deification of the second-order kernel function fully accurate in contrast to that identified by using an impulse-response method.
Fig. 3. Second-kernel by Chebyshev polynomial
Fig. 4. Comparison of second-kernels respectively by Chebyshev method and impulse method
During the last several decades there has been considerable interest in the accurate prediction of steady and unsteady transonic flows. Since transonic flow is inherently nonlinear and involves the formation of shock waves, accurate simulation of transonic flow requires the use of a nonlinear field equation, and for unsteady phenomena the solution needs to be time accurate. This paper employs a CFD (Computational Fluid Dynamics) code which is based on the Euler equation.
The two-dimensional Euler equations in Cartesian coordinates (, ) can be written in non-dimensional conservative from as following :
where is the vector; and are the Cartesian components of the convective fluxes.
In the above is the fluid density, and are the and components of the fluid velocity, the total energy and is the pressure which is obtained from:
where is the ratio of specific heats of the fluid.
The contravariant velocities and are defined by:
where , are the grid speeds in the and directions respectively.
The Eq. (25) are discretized using a cell-centered finite volume method that transforms the partial differential equations into a set of ordinary differential equations that can be written as:
where is the flux residual for the cell (, ) that contains all the terms arising from the spatial discretization.
For the solution of the unsteady Euler equations, an implicit dual-time method can be employed. The initial conditions are chosen as the steady flow before the object moves. The boundary condition at the body is subject to the kinematic condition requiring the body to be impenetrable to the flow. Namely, the flow remains tangent to the body surface. The far-field boundary conditions are treated by the characteristic boundary method based on the Riemann invariants.
Fig. 5 is an O-type grid with 181×48 grid points for NACA0012. The steady inviscid comprssible flows about this airfoil is computed at Mach number and angle of attack deg. The model has a NACA0012 airfoil secontion and a rectangular planform with a span of 0.8128 m and a chord of 0.2032 m. The rigid-body plunge mode consists only of vertical translation and the rigid-body pitch mode consists onlyof rotation about the mid-chord .
In aerodynamics, using Chebyshev polynomial method for the identification of kernels of the aerodynamic forces is seldom seen. Much more of its application can be found in theoretical research. The popular identification methods to a nonlinear system, say pulse- and step-type methods, highly rely on the entire data produced by executing CFD code again and again. As mentioned in the section of introduction, the cost of time-consumption is prohibitively expensive.
If the second-order kernels can not be identified correctly, the result of the aerodynamic forces of predicting can not be accurate and even badly wrong. Therefore, the third-order ROM is first suggested to be used here. The process of identification is presented in the section of third-order ROM above. The mainly advantages here are a) the first- and second-order kernels are steadily to be evacuated by Eqs. (20) and (23); b) Since the third-order kernels are not necessary to be identified, this model is appropriate to be applied; c) The high-order ROM helps to improve the identification accuracy of second-order kernels of nonlinear systems of interest.
Fig. 5. Naca0012 airfoil and aerodynamic grid
In order to investigate the kernels' accuracy from the two models of ROMS of the second-order and the third-order, the first- and second-order kernels have been computed out respectively from Eqs. (20) and (23) in the third-order ROM and from Eqs. (12) and (16) in the second-order ROM, here is chosen and impulse-response method is employed.
The second-order kernels can also be computed out from Eq. (3) by Chebyshev Polynomials method based on the coefficients identification which needs use the least squares estimation to a number of data produced by executing CFD code. For simplicity, we call the kernels identification of 2-ROM Silva Method and call the Chebyshev Polynomials identification of 3-ROM our New Method.
Fig. 6 shows the difference of the two first-kernels identified by using New Method and Silva Method respectively. Fig. 7 shows the prediction of aerodynamic forces by using CFD directly computational method and using convolution techniques to the same sinusoid input with the first-kernels of 2-ROM and 3-ROM respectively. It illustrates that the higher of the ROM is used the more accuracy the kernels are.
Fig. 6. First kernels obtained in Silva Method and New Method
Fig. 7. Lift predicted by using CFD method and convolution techniques respectively with first-kernels of 2-ROM and 3-ROM to the same sinusoid input
Note that the accuracy of the prediction of aerodynamic forces using CFD directly computational method is dependent on the choice of the time step. Fig. 8 shows the difference of the accuracy when executing CFD code with the step time 0.001 and 0.0001 respectively. The input is given by . However, it does not a matter to consider the selection of time step size in the view of identification which is merely concerned about data of inputs and outputs.
Fig. 8. CFD Results based on time step 0.001, 0.0001
Using CFD method, impulse-response method (Silva method based on 2-ROM) and Chebyshev polynomials method (our new method based on 3-ROM), the response curves is given respectively in Fig. 9.
Fig. 9. Response curves computed by CFD, Chebyshev method and Silva method respectively
In order to improve the accuracy of identification, the third-order ROM is first proposed to model the nonlinear and unsteady aerodynamic forces. The second example shows the kernels of third-order ROM are much more accurate than those of a second-order ROM.
In order to overcome the prohibitively expensive time-consumptions by executing CFD code to get the fully data for identification in an impulse- or step-response method, Chebyshev polynomials method is suggested and investigated in details. This method of identification is classified as a parameter method. Since only parts of the data are used for identification, the number of executing CFD code can be reduced at least one order of magnitude. That is extremely time-saving.