Finite element model updating of riveted joints of simplified model aircraft structure

Yunus, M. A.; Rani, M. N. Abdul; Sani, M. S. M.; Shah, M. A. S. Aziz

doi:10.1063/1.5031975

Cited by 22 publications

(7 citation statements)

References 11 publications

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“…On EMA, the irregular plate was discretised into 30 measurements points (EMA modal model), as presented in Figure 2. The measurement points decided to reduce the possibility of losing any mode and obtaining a suitable mesh for animating the modes of interest [20]. The configuration of the EMA modal model used in developing the reduced FE model of the irregular plate is vital to the mode expansion.…”

Section: Description Of Case Studymentioning

confidence: 99%

Estimating Rotational Frequency Response Function Using Mode Expansion and Frequency Response Function Synthesis Method

Mirza¹,

Rani²,

Yunus³

et al. 2021

IJAME

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The rotational frequency response function (RFRF) plays a crucial role in increasing the accuracy of the calculated results of the frequency-based substructuring method. However, RFRFs are often omitted due to the difficulties in the measurement process and limitations of the equipment. This paper presents a scheme of estimating the rotational FRF of an irregular plate structure using the FE model reduction and expansion method. The reduced FE model was introduced using the improved reduction system (IRS) and expanded to the experimental modal model (EMA model) using the system reduction and the expansion (SEREP) method. The FRF expanded method was then employed to derive the translational and rotational FRFs from the expanded EMA model. The accuracy of the expanded FRFs was evaluated with the EMA model of the irregular plate. It was found that the translational and rotational FRFs estimated from the proposed scheme were in good agreement with the EMA counterparts. Furthermore, the patterns of the estimated RFRFs were well correlated with the EMA RFRFs. This work shows that the proposed scheme may offer an attractive alternative way of accurately determining the RFRs of complex structures or structural components.

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Section: Description Of Case Studymentioning

confidence: 99%

Estimating Rotational Frequency Response Function Using Mode Expansion and Frequency Response Function Synthesis Method

Mirza¹,

Rani²,

Yunus³

et al. 2021

IJAME

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show abstract

“…In this study, two types of coupling configuration had been performed. The first one was the traditional single node FRF coupling [31,32] as shown in Figure 7. Initially, the two substructures were coupled by using both translational and rotational DOFs in order to obtain the actual and reference FRF for benchmarking purposes.…”

Section: Two Bolted Jointsmentioning

confidence: 99%

Frequency Based Substructuring for Structure with Double Bolted Joints: A Case Study

Mirza

Rani

Yunus

et al. 2019

IJAME

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Adopting dynamic substructuring schemes is a common practice in the field of structural dynamics, where the dynamic behaviour of a structure is predicted by combining the multiple subsystems that are analysed individually. This paper investigated the dynamic behaviour of a structure with doubled bolted joints using the frequency based substructuring (FBS) method. In the attempt, the substructures were combined with the frequency domain that can be numerically derived or experimentally measured. However, the applicability of this method suffered from several issues where most of them were related to the frequency response function (FRF) of the rotational degree of freedom (DOF) at the subsystem’s interface. In some cases, the system’s interface vibrated in the rotary motion of certain modes, for instance, a car side rear view mirror. Therefore, excluding the rotational FRF during the coupling process could lead to a completely different result. This paper presents the use of the FBS method for a structure with double bolted joints by using the equivalent multipoint constraint (EMPC) method through which rotational DOFs can be completely neglected. The actual tested structure for this study was an assembled structure consisting of two substructures: a simple beam and an irregular plate steel structure. The FRFs of both substructures were derived from using the FRF synthesis from finite element models and combined together via the FBS method. This study reveals that the use of the FBS method with the EMPC method for a structure double bolted joints has led to very promising results.

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“…For example, the techniques to revise the computational dynamic scheme, regarding aircraft manufactured from conventional materials, are discussed in the papers [6], from composite materials -in [7,8], UAVs -in [9]. The articles [10][11][12] deal with updating of infinite-element models designed to describe the dynamic construction behavior (including aerospace structures) with the riveted [10] and bolted [11,12] joints.…”

Section: Introductionmentioning

confidence: 99%

About revising the computational dynamic scheme of an unmanned aerial vehicle based on the results of ground-based modal test operations in the aeroelasticity problems

Парафесь

2022

Naučn. vestn. MGTU GA

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The problem of revising the computational dynamic scheme of an unmanned aerial vehicle (UAV), based on the results of ground-based modal test operations, in order to study the UAV flutter and to assess the aeroelastic stability of an UAV with an automatic control system (ACS), is considered. It is noted that at the design stage, when there is no UAV prototype or its units yet, the determination of modal characteristics, specifically natural frequencies, modes and generalized masses, is carried out using the computational dynamic scheme developed according to the design documentation. However, the similar computations, performed even with the use of modern finite-element software systems, do not give sufficiently precise values of the parameters of the UAV design elastic-mass schematization. In this regard, it is relevant and important to specify the parameters of the design schematization in conformity with data of ground test operations for UAV prototypes. The provisions, allowing us to achieve satisfactory results when revising the UAV computational dynamic scheme, are made. The criteria of revising are considered. The features of revising the computational dynamic scheme, while studying the flutter and aeroelastic stability of the ACS-fitted UAV, are presented. It is noted that along with the provisions that are universal for dynamic aeroelasticity problems, specifically for flutter, and related to compensating of natural frequencies, modes and coefficients of structural damping for the UAV model according to the results of ground modal tests. In the problems of aeroelastic stability study of the UAV equipped with the ACS, it is also crucial to correct the UAV body transfer function from the section, corresponding to the axis of controls rotation, to the section where ACS sensors are installed. This is because the UAV hull is an integral part of the UAV stabilization loop and significantly affects its stability margin. The example of revising the computational dynamic scheme of a maneuverable cruciform UAV is given.

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Finite element model updating of riveted joints of simplified model aircraft structure

Cited by 22 publications

References 11 publications

Estimating Rotational Frequency Response Function Using Mode Expansion and Frequency Response Function Synthesis Method

Estimating Rotational Frequency Response Function Using Mode Expansion and Frequency Response Function Synthesis Method

Frequency Based Substructuring for Structure with Double Bolted Joints: A Case Study

About revising the computational dynamic scheme of an unmanned aerial vehicle based on the results of ground-based modal test operations in the aeroelasticity problems

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