# Identification of Engine Inertia Parameters and System Dynamic Stiffness via In Situ Method

Authors: Chuanyan Xu; Xun Gong; Lixue Meng; Aijuan Li
Journal: Mathematical Problems in Engineering
 (2021)

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## Abstract

An in situ method is presented to identify ten engine inertia parameters and system dynamic stiffness from the frequency response functions. The ten engine inertia parameters and system dynamic stiffness are estimated from two distinct steps. The accuracy of the proposed technique is verified by finite element simulation, and then the generality is validated using an engine supported by a specially designed curved bar spring. The locations of the measure points on the results are also carefully investigated. The identification of system dynamic stiffness is validated comparing with the engine with an auxiliary plate, which shows good consistency with the results identified from the study.


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## Body

## 1. Introduction

The identification of engine inertia parameters is important in the analysis of dynamic behaviour, suspension system optimization design, vibration attenuation and isolation, and engine fault diagnosis. During the dynamic structure design, the inertia parameters are regarded as known parameters, for example, when analysing the vehicle vibration noise due to the unbalance forces and moments caused by the engine, the engine is commonly simplified as a three-dimensional model by setting inertia parameters. The inertia parameters of a rigid body directly affect the dynamic behaviour of the system; when there are errors in the identification of the inertia parameter, the dynamic characteristics of the structure will be affected inevitably; and a 5% error of the inertial parameters identification can lead to some order modal frequency reaches more than 1 Hz [1]. Therefore, the accurate identification of inertia parameters is of great significance to engineering practice. Engines on the test bench and the actual vehicle are mounted by rubber suspension, from a practical application point of view; work efficiency is no less important than the accuracy of the test. It is quite necessary to develop a method to identify inertial parameters and system dynamic stiffness simultaneously for the engine mounting system.The conventional techniques for parameters identification of the rigid body can be divided into two categories, i.e., time domain methods [2–7] and frequency domain methods. The frequency domain methods may be further subdivided into three categories: modal model method [8–10], residual inertia method [11–15], and direct system identification method [16, 17]. The classical domain pendulum method is often time-consuming due to repetitive configuration adjustments of a heavy target and complicated body such as an automotive powertrain. The classical residual inertia method must overhang the test rigid body and consider mass as a known parameter; in actual application, the mass is often unknown, and large structure weighing is difficult to achieve. The modal method and direct system identification methods are based on the orthogonality relationship between the mass matrix and six rigid body modes. In order to get the ideal m rigid body modes, ideal spring constraints must be artificially added [18]. Unfortunately, in actual test, ideal boundary conditions are almost impossible to achieve. Thus, it has usually difficulty exciting all six rigid body modes at the same time due to the coupling of rigid body modes [19, 20]; the identification accuracy is hard to guarantee. Vahid et al. [21] and Jeffrey et al. [22] provided methods to estimate the vehicle engine rigid body inertia properties based on in situ measurements. However, a quadratic integral is applied to calculate the mount reaction forces; when the second integral is executed, the unknown primitive value of the velocity and displacement must be set at zero, which can lead to greater identification errors. In addition, the maximum error in the literature [23] reaches 30%. In recent years, the intelligent method is widely used in structural parameter analysis and diagnosis [24–26], and the firefly algorithm is used to identify inertial parameters of the powertrain mounting system from simulation. However, such a method requires experiments to verify its effectiveness [27].Stiffness and damping characteristics are the most important parameters for predicting the dynamic characteristics of the structural system and isolating the vibration and noise of sources to reduce fatigue failure or damage caused by vibration [28, 29]. Normally, the identification of the engine suspension system dynamic behaviour requires special experiments and special facilities [30]. In this paper, we provide a method to identify the dynamic stiffness of the suspension system in situ without a special experiment.The main contributions of the paper are as follows. (1) An in situ identification method for engine inertia parameters and system dynamic stiffness is proposed. The method does not need to calculate the mount reaction force and avoid the error caused by the quadratic integral of acceleration. (2) The effects on the results due to the shaker location and response location are investigated.


## 2. Identification Method

### 2.1. Identification of the Inertia Properties

Since the natural frequency of a powertrain mounting system is commonly within 30 Hz, the engine support system vibration model can be viewed as six degrees of freedom of vibration [19]. The equations of motion for the engine can be expressed as follows:(1)MQ¨t+CQ˙t+KQt=Ft,where M is the mass matrix whose elements are the inertia parameters to be determined, C is the damping matrix, K is the stiffness matrix, Q is the generalized displacement vector, and F is the generalized force vector of origin O.(2)M6×6=m000mzc−myc0m0−mzc0mxc00mmyc−mxc00−mzcmycJxxo−Jxyo−Jxzomzc0−mxc−JxyoJyyo−Jyzo−mycmxc0−Jxzo−JyzoJzzo,K6×6=kxxkxykxzkxαkxβkxγkyxkyykyzkyαkyβkyγkzxkzykzzkzαkzβkzγkαxkαykαzkααkαβkαγkβxkβykβzkβαkββkβγkγxkγykγzkγαkγβkγγ,where kxx, kyy, and kzz are the total reciprocating stiffness of elastic support; kxy, kxz, and kzy are the coupling stiffness of elastic support; and kαα, kββ, and kγγ are the rotary stiffness about the coordinate axis.(3)F6×1=FxFyFzMxMyMz,Q6×1=XoYoZoαβγ.Both sides take Fourier transformation as follows:(4)M−Kω2−jCωQ¨f=Ff.According to the coordinate transformation of the response and excitation points [14], the vibration equation of the engine due to n excitation forces and s measurement points can be obtained as follows:(5)M−1ω2K∗X=T,where(6)X=ETE−1ETH,where H is the transfer function matrix, which can be obtained from the experiment test; E is the transpose matrix for response points; and T is the transpose matrix for excitation points. The number of response points s≥2 is required (in three directions), so that the rank of matrix E is above 6, and Q¨ can be determined in a least-square sense. The number of excitation points must be equal to or greater than 6, so matrix M can be calculated in a least-square sense. The locations of the sensors should have sufficient rigidity.Transposing equation (5) and rearranging yield(7)XTM=TT+1ω2XTK∗T.Equation (7) consists of 6 equations and 10 unknowns. In the frequency domain, the force and acceleration are generally complex quantities, so the real and imaginary parts can be separated to yield 12 equations with 10 unknowns(8)ReXTImXTM=ReTT+1ω2XTK∗TIm1ω2XTK∗T.These 12 equations are not linearly independent, so additional equations must be generated to solve forM. Although the frequency response function is a function of the frequency, with different values at each frequency line, the inertia parameters are constant. In addition, the frequency response function values of adjacent frequency lines are nearly identical, which implies that frequency lines must be selected sufficiently far apart to ensure linearly independent equations. The expanded equation is shown as follows:(9)AM=B,where(10)A=ReX1TImX1T⋮ReXrTImXrT,B=ReX1T+1ω12X1TK∗TIm1ω12X1TK∗T⋮ReXrT+1ωr2XrTK∗TIm1ωr2XrTK∗T.Then, matrixM can be calculated in a least-square sense as follows:(11)M=ATA−1ATB.After mass matrixM has been determined, the ten inertia parameters can be obtained.


### 2.2. Identification of the System Dynamic Stiffness

Based on the identified mass matrixM and frequency response functions (FRFs) in the low-rigid-frequency domain, the system dynamic stiffness can be easily estimated.Assuming that(12)Ho=ETE−1ETH.Then,(13)K∗Ho=ω2MHo−T.Once mass matrixM is available, matrix K∗ can be estimated using the pseudoinverse as follows:(14)K∗=ω2MHo−THoTHoHoT−1.An iterative computation method is used to improve the inertia parameters identification accuracy. Consider the system dynamic stiffness identified by equation (14) as known parameters, we substitute equation (14) into equation (7), calculate the inertia parameters, and repeat this step until the identified inertia parameters converge. Thus, the effect of the rigid body modes on the identification of inertia parameters decreases.


## 2.1. Identification of the Inertia Properties

Since the natural frequency of a powertrain mounting system is commonly within 30 Hz, the engine support system vibration model can be viewed as six degrees of freedom of vibration [19]. The equations of motion for the engine can be expressed as follows:(1)MQ¨t+CQ˙t+KQt=Ft,where M is the mass matrix whose elements are the inertia parameters to be determined, C is the damping matrix, K is the stiffness matrix, Q is the generalized displacement vector, and F is the generalized force vector of origin O.(2)M6×6=m000mzc−myc0m0−mzc0mxc00mmyc−mxc00−mzcmycJxxo−Jxyo−Jxzomzc0−mxc−JxyoJyyo−Jyzo−mycmxc0−Jxzo−JyzoJzzo,K6×6=kxxkxykxzkxαkxβkxγkyxkyykyzkyαkyβkyγkzxkzykzzkzαkzβkzγkαxkαykαzkααkαβkαγkβxkβykβzkβαkββkβγkγxkγykγzkγαkγβkγγ,where kxx, kyy, and kzz are the total reciprocating stiffness of elastic support; kxy, kxz, and kzy are the coupling stiffness of elastic support; and kαα, kββ, and kγγ are the rotary stiffness about the coordinate axis.(3)F6×1=FxFyFzMxMyMz,Q6×1=XoYoZoαβγ.Both sides take Fourier transformation as follows:(4)M−Kω2−jCωQ¨f=Ff.According to the coordinate transformation of the response and excitation points [14], the vibration equation of the engine due to n excitation forces and s measurement points can be obtained as follows:(5)M−1ω2K∗X=T,where(6)X=ETE−1ETH,where H is the transfer function matrix, which can be obtained from the experiment test; E is the transpose matrix for response points; and T is the transpose matrix for excitation points. The number of response points s≥2 is required (in three directions), so that the rank of matrix E is above 6, and Q¨ can be determined in a least-square sense. The number of excitation points must be equal to or greater than 6, so matrix M can be calculated in a least-square sense. The locations of the sensors should have sufficient rigidity.Transposing equation (5) and rearranging yield(7)XTM=TT+1ω2XTK∗T.Equation (7) consists of 6 equations and 10 unknowns. In the frequency domain, the force and acceleration are generally complex quantities, so the real and imaginary parts can be separated to yield 12 equations with 10 unknowns(8)ReXTImXTM=ReTT+1ω2XTK∗TIm1ω2XTK∗T.These 12 equations are not linearly independent, so additional equations must be generated to solve forM. Although the frequency response function is a function of the frequency, with different values at each frequency line, the inertia parameters are constant. In addition, the frequency response function values of adjacent frequency lines are nearly identical, which implies that frequency lines must be selected sufficiently far apart to ensure linearly independent equations. The expanded equation is shown as follows:(9)AM=B,where(10)A=ReX1TImX1T⋮ReXrTImXrT,B=ReX1T+1ω12X1TK∗TIm1ω12X1TK∗T⋮ReXrT+1ωr2XrTK∗TIm1ωr2XrTK∗T.Then, matrixM can be calculated in a least-square sense as follows:(11)M=ATA−1ATB.After mass matrixM has been determined, the ten inertia parameters can be obtained.


## 2.2. Identification of the System Dynamic Stiffness

Based on the identified mass matrixM and frequency response functions (FRFs) in the low-rigid-frequency domain, the system dynamic stiffness can be easily estimated.Assuming that(12)Ho=ETE−1ETH.Then,(13)K∗Ho=ω2MHo−T.Once mass matrixM is available, matrix K∗ can be estimated using the pseudoinverse as follows:(14)K∗=ω2MHo−THoTHoHoT−1.An iterative computation method is used to improve the inertia parameters identification accuracy. Consider the system dynamic stiffness identified by equation (14) as known parameters, we substitute equation (14) into equation (7), calculate the inertia parameters, and repeat this step until the identified inertia parameters converge. Thus, the effect of the rigid body modes on the identification of inertia parameters decreases.


## 3. Numerical Study

Mounts greatly vary in stiffness due to the manufacturing variability, temperature, and displacement. Thus, the identification of inertia parameters of a certain frequency line is not representative. To verify the generality of the method, a specially designed curved bar spring in Figure1 is used to support a standard block (the mass is 160.6 kg, and the density is 7.85 × 106/m3) simulated the engine (Figure 2). One end of the spring is attached to the standard block, while the other end is fixed by six degrees of freedom. The characteristics of the curved bar spring are as follows: (1) linearly elastic: the three directions of its local coordinate system are linear, and the coupling directions are also linear and (2) small damp: the damp of the spring is negligible.Figure 1
Curve bar spring.Figure 2
Standard block supported by curve bar springs.The 4 response measurement points and 9 applied forces were selected for testing points. The FRFs of the block were measured with the sampling frequency of 2048 Hz and 512 sampling points by the structural Nastran FRF case module. The modulus of the FRFs is shown in Figure3.Figure 3
Modulus of the FRFs.Figure3 shows that the rigid body modes of the engine lie below 35 Hz, and there is no coupling phenomenon. The first elastic resonance frequency is about 177 Hz with little amplitude; it is available to estimate the mass line from the measured FRFs. In addition, the dynamic stiffness of the support system has little effect on the mass line; it is negligible from engineering practice.In general, more testing points than required are selected to ensure a good result. By equation (12), Ho can be calculated; then the FRFs of the jth frequency line Hj can be derived by inverse operation Hj′. The difference between Hj and Hj′ can be used to determine the error of the results, which can be expressed as follows:(15)errj=Ηj−Hj′.The total error can be calculated as follows:(16)err=13×N×P∑j=13×N×PΗj−Hj′.To improve the inertia parameters identification accuracy, the error should remain in a certain range, that is,errj<err×level (level, the initial value), or Hj should be eliminated. Since equation (11) uses a least-square method, the rank of matrix T should be full, and the condition number con of matrix T should be lower than 20 [20]. In conclusion, there are three conditions to select the frequency lines of the FRFs: (1) errj<err×level, (2) rankT=6, and (3) CondT<con. The response points are selected in similar manners.The frequency bands from 90 Hz up to 150 Hz were selected to identify the ten inertia parameters by equation (11). The identified standard block inertia parameters are presented in Table 1 with a comparison to the finite element simulation results, and the stiffness of the curve bar spring is shown in Table 2. The maximum inertia parameters error is 1.74% for xc; the element error of the matrix K is within 2%; and the identified results are consistent with the theory values. In addition, the linear characteristics of the curve bar spring verify the generality of the method.Table 1
Standard block inertia parameters.
FEMProposed methodError (%)Mass (kg)m161.2163.3−1.28Centre of gravity (mm)xc147.0144.41.74yc152.3152.30.03zc112.9112.70.15Moment of inertia (kg⋅m2)Jx7.777.87−1.31Jy7.747.82−0.99Jz9.9010.02−1.22Product (kg⋅m2)Jxy3.663.640.44Jxz2.762.79−1.11Jyz2.432.410.59Table 2
Identified system stiffness of the curve bar spring.
DirectionxyzαβγFEM system stiffness (N/m)x26951930536118.7044461.070y027530209247.3950−69097.7z536118.701416128085055.210α09247.395022965.870−13059.3β44461.07085055.21037323.230γ0−69097.70−13059.3041700.41Estimated system stiffness (N/m)x2686950.3−67.8536001.980395.7313059.6−403005.1y61.9272706.363.0−18142.715.7−68023.4z539171.3−36.31419722.6212926.3139301.4−80845.6α80788.2−18181.8212693.055748.020843.2−18336.2β313161.14.2138468.020756.373034.6−46970.4γ−403015.0−68262.8−80467.7−18264.8−46967.9101906.0Error (%)x0.31—0.020.030.290.32y—0.94—0.77—1.55z−0.57—−0.25−0.24−0.46−0.53α−0.460.55−0.13−0.03−0.21−0.68β0.26—0.140.210.180.27γ0.311.21−0.06−0.290.270.43The six rigid mode shapes have a relatively large magnitude; it is necessary to study their effect on the identification of inertia parameters, so as to see the dynamic behaviour of the engine support system. To ignore the effect of rigid mode shapes, the inertia parameters can be computed using the method in the literature [14], that is, the swing method. The residual inertia method was used to estimate the inertia parameters. To consider the effect of rigid mode shapes, substitute the FEM system stiffness into equation (5); the frequency bands from 90 Hz up to 150 Hz were used to identify the ten inertia parameters. The results are shown in Table 3. The rigid mode shapes have little effect on the estimation of inertia parameters. Since the first elastic mode shapes have a very small magnitude, the inertia parameters are basically unchanged. Both the six rigid and first elastic mode shapes can be ignored from a practical application point of view.Table 3
Effects of rigid shapes on the identification of inertia parameters.
TheoryIgnore rigid shapesError (%)Consider rigid shapesError (%)Mass (kg)m160.6161.3−0.44163.7−0.44Centre of gravity (mm)xc147.0147.00.00144.80.00yc152.3151.10.79148.40.79zc112.9112.90.001110.00Moment of inertia (kg⋅m2)Jx7.747.79−0.657.78−0.65Jy7.717.700.137.680.13Jz9.869.89−0.309.87−0.30Product (kg⋅m2)Jxy3.643.65−0.273.65−0.27Jxz2.752.721.092.711.09Jyz2.422.381.652.381.65


## 4. Errors of the Testing Point Location Effect

Since the testing point locations are essential input parameters for the algorithm, random errors were added to understand the sensibility of the method to location errors in this step. One hundred simulation runs were performed for each random error. The errors introduced into the inertia parameters are shown in Figure4, and the excitation and response location errors introduced into the system stiffness are presented in Tables 4 and 5, respectively.Figure 4
Sensitivity of inertia parameter to location errors: (a) excitation locations and (b) response locations.
(a)(b)Table 4
Sensitivity of the method to system stiffness errors at excitation locations.
DirectionxyzαβγEstimated stiffness (K/m) with error ±34.8 mmx2688379.0308.4537109.780584.8313371.1−403403.0y−260.8272125.0−652.6−18363.7−124.8−67640.9z538223.553.01417243.0212655.4138738.3−80782.5α80499.8−18736.8211808.655768.420651.1−18095.9β314727.8−155.5142674.121328.573933.7−47109.5γ−403446.0−66291.1−80384.6−17941.4−46977.6100948.6Estimated error (%)x−0.25—0.180.21−0.19−0.22y—−1.15—0.44—−2.11z0.39—0.080.110.050.45α0.102.48−0.290.06−0.72−0.64β0.24—2.892.541.050.03γ−0.21−4.06−0.04−1.49−0.25−1.36Estimated stiffness (K/m) with error ±120 mmx2688603.0274.3536987.380564.2313366.7−403420.0y−269.8272111.2−674.7−18353.5−128.6−67632.9z538230.542.91417220.0212642.0138718.0−80775.2α81008.9−17557.0212938.155060.520849.3−18396.5β314197.91176.8140636.621094.473510.2−47674.7γ−404670.0−68378.2−84502.7−19264.0−47828.2102362.8Estimated error (%)x−0.24—0.160.18−0.20−0.21y—−1.16—0.39—−2.12z0.39—0.080.100.040.44α0.74−3.970.24−1.210.241.01β0.07—1.421.410.471.23γ0.10−1.045.085.781.550.02Table 5
Sensitivity of the method to system stiffness errors in response locations.
DirectionxyzαβγRandom error ±34.8 mmx2687089.0−49.4534515.079808.6312370.9−400879.0y−460.3272380.3−820.9−17882.0−362.8−68551.1z538707.6555.91419494.0211825.7141596.3−80095.5α80841.6−17496.1213273.355795.121209.0−18439.5β311702.6−33.8138302.020606.673283.5−46386.5γ−400960.0−68279.8−79754.0−18304.2−46517.9101827.6x−0.3—−0.3−0.76−0.51−0.84y—−1.06—−2.19—−0.79z0.48—0.24−0.282.11−0.40α0.53−4.300.400.111.971.25β−0.73—−0.26−0.930.16−1.51γ−0.82−1.18−0.830.50−1.23−0.50Random error ±120 mmx2687577.0−863.8533317.980772.6326156.1−411843.0y−1342.0269013.3955.6−16104.3−366.2−79734.5z535032.0−4586.71405268.0211346.6177723.6−88411.0α81899.9−18308.2214197.961077.627131.7−21016.2β312780.1−1596.4135979.420503.282414.3−48248.2γ−407703.0−69072.3−81083.1−20979.8−48705.7113786.3Estimated error (%)x−0.28—−0.520.443.881.87y—−2.28—−11.92—15.39z−0.20—−0.77−0.5028.179.94α1.840.140.849.5930.4415.40β−0.38—−1.94−1.4312.642.44γ0.85−0.040.8315.203.4211.18The errors in the locations of test points have almost no influence on the estimated mass. Both errors in other properties increase with the increase in the testing error. Approximately 4% error is introduced by an error in the excitation locations, and approximately 9% error is introduced by an error in the response locations. From Tables4 and 5, we can see that the error has a relatively larger effect on the estimated system dynamic stiffness, especially on the coupling stiffness; when the random error is in the range of [–120, 120], the estimated error on the coupling stiffness is 30.44%. As shown, care must be taken in measuring geometry to avoid incorrect results. The units of the elements of the stiffness matrix are the corresponding generalized force divided by the generalized displacement.


## 5. Experiments

### 5.1. Curve Bar Spring Engine System

The test engine was supported by 3 specially designed curve bar springs shown in Figure5. Here, 4 response points and 18 excitation points were taken into account. The coordinates of test points were measured by the 3D coordinate measuring apparatus.Figure 5
Test engine supported by curve bar springs.The FRFs were measured with the sampling frequency of 1024 Hz and 1024 sampling points. The modulus of the FRFs for 4 response points and 3 of 18 excitation points are presented in Figure6. We can see that all six rigid body modes are excited within 30 Hz, and the first elastic resonance frequency is approximately 118.5 Hz. The FRFs and the corresponding coherence functions for response point 1 are shown in Figure 7. The values of the coherent coefficients for the three directions are all greater than 0.8, which verifies the reliability of the experiment.Figure 6
Amplitude-frequency response for response measurement points and applied forces.Figure 7
Example of the test FRFs (excitation: F17; response: Acc3): (a) FRF and (b) coherence.
(a)(b)The coordinate transformation of the test points [14] is valid only when the rigidity condition is satisfied. In this section, the measured and calculated FRFs were compared at the fourth accelerometer to check the rigidity of the engine. According to coordinate transformation, the FRFs of the fourth accelerometer can be calculated by the other three accelerometers, that is, Acc1, Acc2, and Acc3. As shown in Figure 8, the calculated FRFs agree well with the measured FRFs within 100 Hz, which verified the rigidity of the engine.Figure 8
Rigidity check of the engine: (a) amplitude and (b) phase.
(a)(b)The frequency bands from 60 Hz to 85 Hz were used to identify the 10 inertia parameters by equation (11) (Table 6). Then, the FRFs from 3 Hz to 35 Hz were used to identify the curve bar spring stiffness in Table 7. The inertia parameters of the engine were also computed by the swing method [16], for comparison. The proposed method can identify the engine inertia method under normal installation conditions (in situ), while the swing method must remove the engine from the support infrastructure to ensure free-free boundary conditions.Table 6
Identified inertia parameters of the engine curve bar spring system.
Inertia parametersProposed methodSwing methodMass (kg)m115.2109.3Centre of gravity (mm)xc16.733.4yc206.8216.3zc119.1135.5Moment of inertia (kg⋅m2)Jx11.5211.62Jy5.505.42Jz8.808.46Product (kg⋅m2)Jxy0.270.03Jxz3.253.31Jyz0.230.12Table 7
Identified system stiffness of the engine supported by curve bar springs.
DirectionxyzαβγIdentified system stiffness (N/m)x290120.748337.8386771.5116531.3−22822.5−52696.2y70933.0395010.3137520.8−10216.1−16877.220108.6z553817.977824.81160978.8268614.316786.5−124765.4α150337.5−14657.5278525.7133840.115069.3−44197.4β−57322.6−10786.8−35724.611531.164754.89857.5γ−47982.520608.0−89536.5−38565.4−1114.031575.3Since the engine and curve bar springs were connected through 3 switchover pieces (0.81 kg × 3) and an auxiliary plate (Figure5), the identified engine mass was somewhat larger than the swing method estimated. In addition, the centre of gravity should reduce in value due to the effect of the switchover pieces (0.81 kg × 3) and an auxiliary plate compared with the swing method, and the results are consistent with the trend. The identified results of the proposed method are close to the results from the swing method. The stiffness values estimated from the presented method and extracted by the finite element simulation have a bias because: (1) there is machining error, (2) the three curve bar springs do not have exactly identical stiffness, and (3) the spring stiffness has a certain degree of nonlinearity.Once the inertia parameters and system dynamic stiffness are known, the FRFs corresponding to the measured FRFs can be calculated. Comparing the sum of all calculated FRFs with the measured values, we find that the two FRFs have consistent moduli, as shown in Figure9, which verifies the consistency of the identified results. Hereafter, if there is no specific declaration, the same method is utilized.Figure 9
Modulus of the measured and calculated FRFs.


### 5.2. Mount Engine System

Here, the engine was supported by three mounts as shown in Figure10. The engine and measuring points are identical to those in Figure 5. Similar steps to estimate the inertia parameters and system dynamic stiffness are applied in this section. The signals were collected with the sampling frequency of 256 Hz and 1024 points. The moduli of the calculated FRFs for all points are shown in Figure 11.Figure 10
Test engine supported by the mount.Figure 11
FRFs for all measurement points of the engine supported by the mount.The coherent coefficients are greater than 0.8, and the rigidity condition of the engine holds within 100 Hz. The identified inertia parameters and system dynamic stiffness are presented in Tables8 and 9, respectively. From Table 8, we can see that the identified inertia parameters agree well with those from the swing method.Table 8
Identified inertia parameters of the powertrain mount system.
Inertia parametersProposed methodSwing methodMass (kg)m110.8109.3Centre of gravity (mm)xc19.533.4yc208.1216.3zc134.2135.5Moment of inertia (kg⋅m2)Jx11.5611.62Jy5.615.42Jz8.018.46Product (kg⋅m2)Jxy0.340.56Jxz3.363.31Jyz0.260.15Table 9
Identified system dynamic stiffness of the powertrain mount system.
DirectionxyzαβγSystem stiffness (N/m)x1490171.8−62047.3−363210.4−101692.6−245141.7−341731.1y254.81910981.1−776855.1199150.6241490.1259257.6z−547878.2−781461.84635226.61067626.9−694916.0−11255.6α−119562.5378584.31195191.6436581.8−175183.990437.8β−265289.7223319.6−697592.1−143398.3222587.392242.3γ−369934.7273163.7−63350.437893.586895.9174911.2System damp (N⋅s/m)x121371.1−19433.432809.819086.018288.5−24051.3y−58827.4189173.6−95132.9−4759.918617.548450.6z171024.9−213459.0651576.1158276.4−101082.1−91967.9α72740.8−44961.6232898.857961.3−25358.0−34826.9β−39033.159188.1−88440.0−13369.631634.414076.3γ−37373.031182.6−30948.1−9501.8−4297.216228.2The change in system dynamic stiffness with frequency in the three directions of its local coordinate system is shown in Figure12. The modulus of the calculated and the measured FRFs is shown in Figure 13 and verifies the consistency of the identified results.Figure 12
Estimated system dynamic stiffness.Figure 13
Modulus of the measured and calculated FRFs of the engine mount system.


### 5.3. Mount Engine with an Auxiliary Plate

Since the mount stiffness is not available, to verify the accuracy of the identified stiffness in Section5.2, an auxiliary plate (14.9 kg) was rigidly connected to the engine as shown in Figure 14; then, the same steps were applied to calculate the system dynamic stiffness. If the identified stiffness agrees well with that identified in Section 5.2, the identified results are reliable. The sampling frequency and engine attitude are identical to those in Section 5.2. The measured FRFs calculated for points are presented in Figure 15.Figure 14
Engine with an auxiliary plate.Figure 15
FRFs for all measurement points of the engine plate mount system.The inertia parameters and system dynamic stiffness identified results are presented in Tables10 and 11, respectively. Differences between the identified main stiffness are shown in Table 12. In Table 12, the system equivalent stiffness is close, although there is a difference due to the preload. The changes in Kx, Ky, and Kz with frequency for the engine with and without the auxiliary plate are shown in Figure 16. The two curves are basically identical in each direction, which verify the accuracy of the identified stiffness.Table 10
Identified inertia parameters of the engine plate.
Inertia parametersEngine plateEngineDifferencesMass (kg)m126.2110.815.4Centre of gravity (mm)xc22.419.52.9yc180.2208.1−27.9zc98.1134.2−36.1Moment of inertia (kg⋅m2)Jx11.4611.56−0.1Jy6.575.610.96Jz7.978.01−0.04Product (kg⋅m2)Jxy0.970.340.63Jxz3.083.36−0.28Jyz0.460.260.2Table 11
Identified system dynamic stiffness of the powertrain mount system.
DirectionxyzαβγSystem stiffness (N/m)x1395591.8−30449.8−942324.2−281524.7−163269.4−374485.9y−113718.01334671.3−681578.8141792.68774.2210950.1z−525103.2−319732.44847951.01226340.0−643756.5136427.0α−96400.5187465.11490075.0489962.4−255752.362305.0β−342200.549534.8−1123473.9−291110.9334301.883100.4γ−398453.2219841.273853.783061.151541.5187883.5System damp (N⋅s/m)x48323.9−1701.9−107602.7−37387.421710.4−18127.0y−95842.9147080.144298.340013.9−36403.235169.6z109125.4−50897.6515109.4138443.2−24243.4−23883.1α10866.721260.1180011.559125.0−7614.71522.5β−83656.940028.1−63065.61426.821217.124798.1γ−41526.325703.9−1744.17179.4−7047.316897.5Table 12
Differences in identified main stiffness between the engine plate and the engine.
Stiffness (N/m)kxxkyykzzkααkββkγγEngine plate139559213346714847951489962.4234301.8187883.5Engine149017219109814635227436581.8222587.3174911.2Differences (%)−6.34692−30.15784.58929912.226945.2628797.416506Figure 16
Change in (a)Kx, (b) Ky, and (c) Kz with frequency.
(a)(b)(c)Table10 also shows that the identified mass of the engine with the auxiliary plate is 15.4 kg heavier than that of the engine without an auxiliary plate. The difference in quality is due to the quality of the auxiliary plate (14.9 kg). Under the effect of the auxiliary plate, the value of the centre of mass of yc and zc should be smaller than that of the engine without an auxiliary plate, and the trend of the identified results is consistent, which verifies the accuracy of the method.Similar to Section5.1, the modulus of the calculated FRF is consistent with the measured one in Figure 17, which verifies the consistency of the identified results.Figure 17
Modulus of the measured and calculated FRFs of the engine plate mount system.


## 5.1. Curve Bar Spring Engine System

The test engine was supported by 3 specially designed curve bar springs shown in Figure5. Here, 4 response points and 18 excitation points were taken into account. The coordinates of test points were measured by the 3D coordinate measuring apparatus.Figure 5
Test engine supported by curve bar springs.The FRFs were measured with the sampling frequency of 1024 Hz and 1024 sampling points. The modulus of the FRFs for 4 response points and 3 of 18 excitation points are presented in Figure6. We can see that all six rigid body modes are excited within 30 Hz, and the first elastic resonance frequency is approximately 118.5 Hz. The FRFs and the corresponding coherence functions for response point 1 are shown in Figure 7. The values of the coherent coefficients for the three directions are all greater than 0.8, which verifies the reliability of the experiment.Figure 6
Amplitude-frequency response for response measurement points and applied forces.Figure 7
Example of the test FRFs (excitation: F17; response: Acc3): (a) FRF and (b) coherence.
(a)(b)The coordinate transformation of the test points [14] is valid only when the rigidity condition is satisfied. In this section, the measured and calculated FRFs were compared at the fourth accelerometer to check the rigidity of the engine. According to coordinate transformation, the FRFs of the fourth accelerometer can be calculated by the other three accelerometers, that is, Acc1, Acc2, and Acc3. As shown in Figure 8, the calculated FRFs agree well with the measured FRFs within 100 Hz, which verified the rigidity of the engine.Figure 8
Rigidity check of the engine: (a) amplitude and (b) phase.
(a)(b)The frequency bands from 60 Hz to 85 Hz were used to identify the 10 inertia parameters by equation (11) (Table 6). Then, the FRFs from 3 Hz to 35 Hz were used to identify the curve bar spring stiffness in Table 7. The inertia parameters of the engine were also computed by the swing method [16], for comparison. The proposed method can identify the engine inertia method under normal installation conditions (in situ), while the swing method must remove the engine from the support infrastructure to ensure free-free boundary conditions.Table 6
Identified inertia parameters of the engine curve bar spring system.
Inertia parametersProposed methodSwing methodMass (kg)m115.2109.3Centre of gravity (mm)xc16.733.4yc206.8216.3zc119.1135.5Moment of inertia (kg⋅m2)Jx11.5211.62Jy5.505.42Jz8.808.46Product (kg⋅m2)Jxy0.270.03Jxz3.253.31Jyz0.230.12Table 7
Identified system stiffness of the engine supported by curve bar springs.
DirectionxyzαβγIdentified system stiffness (N/m)x290120.748337.8386771.5116531.3−22822.5−52696.2y70933.0395010.3137520.8−10216.1−16877.220108.6z553817.977824.81160978.8268614.316786.5−124765.4α150337.5−14657.5278525.7133840.115069.3−44197.4β−57322.6−10786.8−35724.611531.164754.89857.5γ−47982.520608.0−89536.5−38565.4−1114.031575.3Since the engine and curve bar springs were connected through 3 switchover pieces (0.81 kg × 3) and an auxiliary plate (Figure5), the identified engine mass was somewhat larger than the swing method estimated. In addition, the centre of gravity should reduce in value due to the effect of the switchover pieces (0.81 kg × 3) and an auxiliary plate compared with the swing method, and the results are consistent with the trend. The identified results of the proposed method are close to the results from the swing method. The stiffness values estimated from the presented method and extracted by the finite element simulation have a bias because: (1) there is machining error, (2) the three curve bar springs do not have exactly identical stiffness, and (3) the spring stiffness has a certain degree of nonlinearity.Once the inertia parameters and system dynamic stiffness are known, the FRFs corresponding to the measured FRFs can be calculated. Comparing the sum of all calculated FRFs with the measured values, we find that the two FRFs have consistent moduli, as shown in Figure9, which verifies the consistency of the identified results. Hereafter, if there is no specific declaration, the same method is utilized.Figure 9
Modulus of the measured and calculated FRFs.


## 5.2. Mount Engine System

Here, the engine was supported by three mounts as shown in Figure10. The engine and measuring points are identical to those in Figure 5. Similar steps to estimate the inertia parameters and system dynamic stiffness are applied in this section. The signals were collected with the sampling frequency of 256 Hz and 1024 points. The moduli of the calculated FRFs for all points are shown in Figure 11.Figure 10
Test engine supported by the mount.Figure 11
FRFs for all measurement points of the engine supported by the mount.The coherent coefficients are greater than 0.8, and the rigidity condition of the engine holds within 100 Hz. The identified inertia parameters and system dynamic stiffness are presented in Tables8 and 9, respectively. From Table 8, we can see that the identified inertia parameters agree well with those from the swing method.Table 8
Identified inertia parameters of the powertrain mount system.
Inertia parametersProposed methodSwing methodMass (kg)m110.8109.3Centre of gravity (mm)xc19.533.4yc208.1216.3zc134.2135.5Moment of inertia (kg⋅m2)Jx11.5611.62Jy5.615.42Jz8.018.46Product (kg⋅m2)Jxy0.340.56Jxz3.363.31Jyz0.260.15Table 9
Identified system dynamic stiffness of the powertrain mount system.
DirectionxyzαβγSystem stiffness (N/m)x1490171.8−62047.3−363210.4−101692.6−245141.7−341731.1y254.81910981.1−776855.1199150.6241490.1259257.6z−547878.2−781461.84635226.61067626.9−694916.0−11255.6α−119562.5378584.31195191.6436581.8−175183.990437.8β−265289.7223319.6−697592.1−143398.3222587.392242.3γ−369934.7273163.7−63350.437893.586895.9174911.2System damp (N⋅s/m)x121371.1−19433.432809.819086.018288.5−24051.3y−58827.4189173.6−95132.9−4759.918617.548450.6z171024.9−213459.0651576.1158276.4−101082.1−91967.9α72740.8−44961.6232898.857961.3−25358.0−34826.9β−39033.159188.1−88440.0−13369.631634.414076.3γ−37373.031182.6−30948.1−9501.8−4297.216228.2The change in system dynamic stiffness with frequency in the three directions of its local coordinate system is shown in Figure12. The modulus of the calculated and the measured FRFs is shown in Figure 13 and verifies the consistency of the identified results.Figure 12
Estimated system dynamic stiffness.Figure 13
Modulus of the measured and calculated FRFs of the engine mount system.


## 5.3. Mount Engine with an Auxiliary Plate

Since the mount stiffness is not available, to verify the accuracy of the identified stiffness in Section5.2, an auxiliary plate (14.9 kg) was rigidly connected to the engine as shown in Figure 14; then, the same steps were applied to calculate the system dynamic stiffness. If the identified stiffness agrees well with that identified in Section 5.2, the identified results are reliable. The sampling frequency and engine attitude are identical to those in Section 5.2. The measured FRFs calculated for points are presented in Figure 15.Figure 14
Engine with an auxiliary plate.Figure 15
FRFs for all measurement points of the engine plate mount system.The inertia parameters and system dynamic stiffness identified results are presented in Tables10 and 11, respectively. Differences between the identified main stiffness are shown in Table 12. In Table 12, the system equivalent stiffness is close, although there is a difference due to the preload. The changes in Kx, Ky, and Kz with frequency for the engine with and without the auxiliary plate are shown in Figure 16. The two curves are basically identical in each direction, which verify the accuracy of the identified stiffness.Table 10
Identified inertia parameters of the engine plate.
Inertia parametersEngine plateEngineDifferencesMass (kg)m126.2110.815.4Centre of gravity (mm)xc22.419.52.9yc180.2208.1−27.9zc98.1134.2−36.1Moment of inertia (kg⋅m2)Jx11.4611.56−0.1Jy6.575.610.96Jz7.978.01−0.04Product (kg⋅m2)Jxy0.970.340.63Jxz3.083.36−0.28Jyz0.460.260.2Table 11
Identified system dynamic stiffness of the powertrain mount system.
DirectionxyzαβγSystem stiffness (N/m)x1395591.8−30449.8−942324.2−281524.7−163269.4−374485.9y−113718.01334671.3−681578.8141792.68774.2210950.1z−525103.2−319732.44847951.01226340.0−643756.5136427.0α−96400.5187465.11490075.0489962.4−255752.362305.0β−342200.549534.8−1123473.9−291110.9334301.883100.4γ−398453.2219841.273853.783061.151541.5187883.5System damp (N⋅s/m)x48323.9−1701.9−107602.7−37387.421710.4−18127.0y−95842.9147080.144298.340013.9−36403.235169.6z109125.4−50897.6515109.4138443.2−24243.4−23883.1α10866.721260.1180011.559125.0−7614.71522.5β−83656.940028.1−63065.61426.821217.124798.1γ−41526.325703.9−1744.17179.4−7047.316897.5Table 12
Differences in identified main stiffness between the engine plate and the engine.
Stiffness (N/m)kxxkyykzzkααkββkγγEngine plate139559213346714847951489962.4234301.8187883.5Engine149017219109814635227436581.8222587.3174911.2Differences (%)−6.34692−30.15784.58929912.226945.2628797.416506Figure 16
Change in (a)Kx, (b) Ky, and (c) Kz with frequency.
(a)(b)(c)Table10 also shows that the identified mass of the engine with the auxiliary plate is 15.4 kg heavier than that of the engine without an auxiliary plate. The difference in quality is due to the quality of the auxiliary plate (14.9 kg). Under the effect of the auxiliary plate, the value of the centre of mass of yc and zc should be smaller than that of the engine without an auxiliary plate, and the trend of the identified results is consistent, which verifies the accuracy of the method.Similar to Section5.1, the modulus of the calculated FRF is consistent with the measured one in Figure 17, which verifies the consistency of the identified results.Figure 17
Modulus of the measured and calculated FRFs of the engine plate mount system.


## 6. Conclusions and Discussion

An in situ method for identifying ten inertia parameters and system dynamic stiffness of an engine was presented in this paper. Further investigation of the errors of the testing point location effect shows that the coordinates of measuring points should be carefully measured since errors in coordinates lead to errors in results.The results from the test on the engine supported by the curve bar spring verify the generality of the method, while the results from the test on the engine supported by the mount are comparable to those of a swing test, which indicates the accuracy of the estimation inertia parameter method. The consistency of the identified dynamic stiffness of the engine with and without an auxiliary plate shows that the estimation of the system dynamic stiffness is reliable. In addition, for each experiment, the modulus of all FRFs calculated from the inertia parameters and system dynamic stiffness has high consistent with the measured value, which further verifies the accuracy of the identified results.However, the system dynamic stiffness identification method can only identify the stiffness at the origin of the coordinates. This method cannot identify the stiffness of each mount. In future research, we will study more appropriate methods to overcome this deficiency.



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*Source: 6439762-2021-08-11.xml*