A comparative study of timemarching schemes for fluidstructure interactions
Jianyao Yao^{1} , Tao Lin^{2} , G. R. Liu^{3} , C.L. Chen^{4}
^{1}College of Aerospace Engineering, Chongqing University, Chongqing, P. R. China
^{1, 2, 3}Department of Aerospace Engineering and Engineering Mechanics, University of Cincinnati, Cincinnati, United States
^{4}Department of Mechanical and Aerospace Engineering, University of Missouri, Columbia, United States
^{1}Corresponding author
Vibroengineering PROCEDIA, Vol. 4, 2014, p. 170175.
Accepted 8 September 2014; published 3 November 2014
Four types of partitioned timemarching schemes, namely the iterative staggered serial (ISS) scheme, the conventional serial staggered serial (CSS) scheme, the generalized serial staggered scheme (GSS), and the serial staggered scheme with fluid loads predictions (FPSS), are presented for accuracy comparisons of nonlinear fluidstructure interactions (FSI). A 2DOF aeroelastic model for an airfoil is used as an example to illustrate the effects of different control parameters of the schemes. Some modifications are made to the schemes to improve the FSI simulation accuracy. The numerical results show that the GSS and FPSS are accurate and robust if the default parameters are adopted. Moreover, the accuracy of FPSS can be further improved by simply tuning the control parameters.
Keywords: fluidstructure interaction, partitioned schemes, timemarching, aeroelastic.
1. Introduction
Fluidstructure interaction (FSI) is a typical multifield problem, where the simulations of fluid field, structural field and mesh movement are involved. The FSI simulation is always a challenging problem due to the huge computational effort and the data exchange accuracy between different domains. The numerical simulations of FSI problems can be generally divided into three groups, namely the monolithic schemes, the stronglycoupled schemes and the looselycoupled schemes [13]. The monolithic methods are more accurate but much less efficient than the coupled methods.
To improve the computational efficiency of FSI problems, some partitioned schemes are devised. In the partitioned schemes, the fluid and structural part are discretized and solved separately, and data exchanges are necessary at the FSI interfaces at each time step. For the stronglycoupled schemes, several iterations may be required to enforce the equilibrium of interaction force and boundary movement at the FSI interface [34]. The computational efficiency can be further improved using the looselycoupled schemes, where the iterations in each time step are removed by properly design the timemarching schemes [2]. The timemarching schemes must be carefully designed since they are crucial to accuracy, robustness and stability of the looselycoupled methods. In this paper, we summarize and compare the available timemarching schemes, and make some modifications to improve the accuracy. The purpose of this research is to find proper highlyefficient timemarching schemes for a newly developed FSI simulation platform for rotarycraft, which combines the CFD solver based on gradient smoothing method [58] and traditional finite element structural solver.
There are three more sections in this paper. In Section 2, the algorithms of strongly and looselycoupled timemarching schemes are introduced and discussed. In Section 3, the 2DOF nonlinear aeroelastic model is used as the numerical example to show the properties of different timemarching schemes, and the effects of tunable parameters are also discussed. Some conclusions are drawn in the last section.
2. Timemarching schemes for FSI problems
In this section, four kinds of partitioned schemes are introduced. These algorithms are designed for timemarching schemes of general FSI problems, and the CFD and structural solver can be any available ones.
2.1. Iterative serial staggered (ISS) schemes
In the ISS schemes, the equilibrium of force and velocity (and/or displacement) on the fluidstructure interface is enforced by some iterations in each time step. The basic steps for modified iterative serial staggered (ISS) scheme equipped with load and displacement relaxations can be written as following:
(1) Start from the solutions of previous step, ${\mathbf{x}}^{n}$, ${\mathbf{v}}^{n}$ and ${\mathbf{a}}^{n}$are vectors of the structural solutions for displacement, velocity and acceleration, and ${\mathbf{F}}_{f}^{n}$ is the unsteady fluid loads.
(2) Iteration steps from ${t}^{n}$ to ${t}^{n+1}$. Set initial condition for iteration as:
(3) If not converged, repeat (4)(7):
(4) Update iterative structural results:
(5) Structural results relaxation:
(6) Update fluid loads:
(7) Fluid loads relaxation:
(8) Prepare data for next step:
The ISS schemes are accurate and can be slightly tuned to improve the computational efficiency. However, the iterative execution of both fluid and structural solvers can be extremely timeconsuming, especially for large scale engineering problems. Thus, the looselycoupled schemes, where no iteration is involved, are designed to reduce the computational difficulties of FSI problems.
2.2. Conventional serial staggered (CSS) schemes
The CSS scheme is the simplest and most straightforward looselycoupled method for FSI computation [2, 9]. In this paper, the CSS schemes are also slightly modified to add the relaxation steps for fluids and structural results. The relaxation patterns will be introduced in GSS and FPSS schemes.
2.3. Generalized serial staggered (GSS) schemes
It is stated in [2, 10] that the temporal accuracy of the staggered partitioned schemes can be greatly improved by adding a prediction step of the structural part. This kind of schemes is named as the GSS schemes. The structural prediction is realized by extrapolation based on the kinetic equations using the high order derivatives of displacement. By adding the structural predictor, GSS schemes provide a new configuration to calculate the fluid loads. The basic steps of GSS schemes can be summarized as following:
(1) Start from the structural solutions of previous one or two steps, ${\mathbf{X}}^{n1}$ and ${\mathbf{X}}^{n}$, and the fluid loads from the previous step ${\mathbf{F}}_{f}^{n}$.
(2) Structural predictor for displacements:
(3) Update the fluid loads using the predicted configuration:
(4) Relaxation of fluid loads:
(5) Correct structural solutions using the structural solver:
(6) Update data for next step:
There are two types of structural predictors: the first one predicts the structural configuration at ${t}^{n+1}$ (denoted as GSS here) and the second one at ${t}^{n+1/2}$ (denoted as GSS0.5 here). For each type, the first or secondorder accuracy can be achieved by choosing ${\alpha}_{1}$ and ${\alpha}_{2}$ [2, 10].
2.4. Serial staggered scheme with fluid force prediction (FPSS)
In the previous subsection, the structural predictors are used to improve stability and accuracy of the timemarching schemes for FSI problems. More recently, Dettmer and Peric [11] proposed a new staggered scheme for fluidstructure interaction based on fluid load predictor. In this paper, we modify this scheme by adding structural relaxation as in the CSS and GSS schemes to improve the flexibility and accuracy of FPSS. The algorithm of the serial staggered scheme with fluid force prediction can be summarized as following:
(1) Start from the fluid solutions of two previous steps, ${\mathbf{F}}_{f}^{n1}$ and ${\mathbf{F}}_{f}^{n}$, and the structural solution ${\mathbf{X}}^{n}$ from the previous step.
(2) Fluid loads predictor based on linear extrapolation:
(3) Update the structural solution using the predicted loads:
(4) Relaxation of structural results:
(5) Fluid force correction using the fluid solver:
(6) Update data for next step:
3. Numerical examples
3.1. 2DOF aerodynamic model
In this paper, a 2DOF aeroelastic problem shown as Fig. 1 is used to compare the presented timemarching schemes. All the definitions of structural parameters and flow conditions can be found in [12]. The equations of motion for this aerodynamic model can be written as:
where $h$ denotes the plunging DOF and $\alpha $ the pitching DOF. The nonlinear torsional stiffness is considered. In this example, the Theodorsen’s model is used to calculate the unsteady aerodynamic loads due to the plunging and pitching movements of the airfoil, and the conventional Newmark method is used as the structural solver. Here, we only focus on the coupling process, i.e., the accuracy comparisons of the timemarching schemes and the influences of the tunable parameters. The amplitude and phase accuracy are evaluated as:
where ${A}_{N}$, ${A}_{R}$, ${t}_{N}$ and ${t}_{R}$ denote the amplitude and peak time of the numerical and reference solutions of the limit cycle oscillations (LCO), and ${T}_{R}$ denotes the period of the reference solutions of LCO.
Fig. 1. 2DOF aeroelastic model [12]
3.2. Influence of relaxation parameters
As introduced previously, the relaxation parameters can be tuned for the structural solutions or the fluid loads. These parameters should be properly tuned to obtain the correct and accurate results. The numerical results of the 2DOF aeroelastic system obtained using various schemes with different relaxation parameters are summarized in Table 1.
Table 1. Relative errors with different relaxation parameters
Schemes

Parameters

$\mathrm{\Delta}t=\text{5.0\xd71}{\text{0}}^{\text{3}}$ s

$\mathrm{\Delta}t=\text{1.0\xd71}{\text{0}}^{\text{2}}$ s


${\alpha}_{1}$

${\alpha}_{2}$

$\beta $

${\epsilon}_{h}$ (%)

${\epsilon}_{\alpha}$ (%)

${\epsilon}_{\mathrm{\Phi}}$ (%)

${\epsilon}_{h}$ (%)

${\epsilon}_{\alpha}$ (%)

${\epsilon}_{\mathrm{\Phi}}$(%)


ISS

0

0

–0.2227

–0.1048

5.456

–0.9870

–0.8223

24.22


ISS

0

0.5

0.1418

0.0830

8.342


ISS

0.5

0.5

–0.1767

–0.0765

8.343


CSS

0

0

63.79

34.99

–40.73


CSS

0

–1

2.013

2.162

6.900

9.414

10.39

35.77


CSS

0.013

–1

0.1159

0.8527

N/A


GSS

1.0

0.5

0

–0.4281

–0.2785

5.456

–2.177

–2.047

12.67

GSS

1.0

0

0

0.3859

–0.1253

5.456

2.005

–0.1105

24.22

GSS

1.0

0.5

0.5

34.44

19.37

–42.81


GSS0.5

0.5

0.125

0

34.81

19.37

–42.81


GSS0.5

0.5

0.125

–0.5

0.5145

0.6045

5.465

2.175

2.264

21.33

GSS0.5

0.5

0

–0.5

0.6984

0.6294

5.546

3.282

3.118

24.22

FPSS

0

0

2.004

2.149

6.900

9.421

10.38

36.81


FPSS

–0.02

0

0.06704

1.242

–0.288


FPSS

–0.05

0

2.181

4.862

1.126


FPSS

–0.065

0

0.054

3.427

–10.42

According to the numerical results, we can have the following comments:
(1) For ISS schemes, the LCO results are not sensitive to the relaxation parameters, but the number of iterations in each step can be greatly influenced by changing these two parameters.
(2) For CSS schemes, load relaxation is necessary to obtain the correct response results of the aeroelastic system. We have ${\mathbf{F}}_{f}={\mathbf{F}}_{f}^{n+1}+\left({\mathbf{F}}_{f}^{n+1}{\mathbf{F}}_{f}^{n}\right)$ when $\beta =\mathrm{}$–1, which means a load prediction based on linear extrapolation is applied to approximate the loads at the end of the current step. When the structural relaxation parameters are slightly changed, better amplitude accuracy can be achieved, but the frequency is not correct, which is absolutely unacceptable for dynamic analysis.
(3) For GSS schemes, no load relaxation is needed, i.e., $\beta =0$ can produce the correct results. However, for the GSS0.5 schemes, $\beta =\text{0.5}$ is needed to achieve the correct response results. Compared the CSS, GSS and GSS0.5 schemes, we can see that when the structural loads are extrapolated (CSS) or calculated using a predicted structural configuration (GSS and GSS0.5) at the end of the current time step, correct response results can be obtained, but with different accuracy. Moreover, the first and secondorder structural predictors achieve similar response accuracy for both GSS and GSS0.5 schemes.
(4) For FPSS schemes, the applied loads are also extrapolated at the end of the current time step same as the CSS scheme with $\beta =$–1, and thus the two schemes have similar accuracy when the default parameters are adopted. However, different from the CSS scheme, the structural relaxation provides a new configuration to correct the fluid loads for next step. Therefore, the accuracy of FPSS can be improved by slightly tuning the structural relaxation parameter.
(5) When the time step becomes two times larger, the errors of all the schemes also become several times larger. However, the FPSS can also be tuned to achieve better accuracy for amplitudes or phase.
4. Conclusions
In this paper, four types of partitioned timemarching schemes for general fluidstructure interaction problems are presented. Although the iterative serial staggered (ISS) has the best accuracy and robustness of all the four present kinds of schemes, it is not our first choice for practical engineering due to the huge computational burden. The conventional serial staggered (CSS) schemes, the general serial staggered schemes without and with half time offset (GSS and GSS0.5) and the serial staggered schemes with fluid loads prediction (FPSS) are looselycoupled methods, where no iterations are involved. Therefore, these three kinds are preferred for large scale problems. According to the numerical results of the 2DOF aeroelastic model, we can see that the GSS and GSS0.5 are accurate and quite robust. However, the FPSS schemes can be tuned via changing the structural relaxation parameter to achieve better accuracy, especially the phase accuracy.
It should be noted that the phase errors are significant for all the schemes, even for the iterative schemes. This could possibly be alleviated by improving the accuracy of the structural solver.
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