# A Computational Method for Dynamic Analysis of Deployable Structures

Authors: Ying Wang; Bin Sun
Journal: Shock and Vibration
 (2020)

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## Abstract

A computational method is developed to study the dynamics of lightweight deployable structures during the motion process without regard to damping. Theory and implementation strategy of the developed method are given in this study. As a case study, the motion process of a bar-joint structure and a ring array scissor-type structure was simulated under external dynamic loading. In order to verify the effectiveness of the method, the simulation results are compared with the results predicted by the authenticated multibody system dynamics and simulation program. It shows that the method is effective to dynamic analysis of deployable structures no matter the structures are rigid or elastic. Displacement, velocity, and acceleration for the entire deployable structures during the motion process can be computed, as well as strain if the deployable structure is elastic.


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## Body

## 1. Introduction

Due to their excellent properties, such as being convenient for transportation and construction, high efficiency, and reutilization, deployable structures offer a new structural engineering design and have been widely used in aerospace, civil engineering, and in other areas [1–7], which are different from traditional constructional methods. At present, the research of deployable structure mainly focuses on the geometric configuration and dynamic and static characteristics of the structure and has achieved a lot of high-level research results [8]. For example, Wei et al. analyzed mobility and geometric characteristics of the Hoberman switch-pitch ball [9]. Sun et al. studied the kinematics, dynamics, and mobility of the deployable scissor structures using the modified screw theory [10, 11]. Tanaka et al. developed a two-dimensional 8-bar jointed structure and analyzed its dynamic characteristics [12]. Muvengei et al. studied the dynamic behavior of planar rigid-body systems using the fine model for considering dynamic interaction of multiple revolute joints with clearances [13]. Although such excellent research works have reached a relatively high degree of maturity, there are still many new questions in need of solution, and their many design concepts and computational methods are still not fully accepted as a feasible engineering solution, especially for lightweight deployable structures under dynamic loading, since their structural damping is generally low, and there will be a challenge when they are subjected to dynamic loading [14].Due to their benefits, there are many lightweight deployable structures such as tensegrity structures, which are a kind of pin-jointed structures composed of struts (in compression) and tendons (in tension) [15–17]. The dynamic behavior of tensegrity structures is still being widely studied due to its importance [14]. Sultan et al. developed linearized motion models for certain tensegrity structures and studied their dynamic behavior [18]. Cheong et al. developed a computational method for the dynamic analysis of a tensegrity structure by using nonminimal coordinates [19]. Nagase and Skelton presented the motion equations for dynamic analysis of tensegrity structures [20]. Oliveto and Sivaselvan developed a method for dynamic analysis of a tensegrity system restricted to small-deformation analysis based on a complementarity framework [21].The main objective of this work is to develop an efficient computational method for dynamic analysis of lightweight deployable structures including but not limited to tensegrity structures, which can be used to study their dynamic characteristics for better structural design. Compared to the previous works [22], the novelty of the developed method is that the method can be used to deformation, kinematic, and dynamic analyses of deployable structures, no matter the deployable structure is a stable structure or mechanism. In order to determine the motion process of deployable structures under external dynamic loading, displacement, velocity, and acceleration of the deployable structure during the expansion and compression process can be computed using the developed method. In order to verify effectiveness of the developed method, a simple bar-joint structure is studied and analyzed. And the simulation results are compared with the numerical results predicted by ADAMS (Automatic Dynamic Analysis of Mechanical Systems), which is an authenticated multibody system dynamics and simulation software. Lastly, as a case study of application, the motion process of a ring array scissor-type deployable structure including displacement, velocity, and acceleration, as well as strain, is studied and analyzed under external dynamic loading.


## 2. Governing Equations for the Motion Process of Lightweight Deployable Structures

This study aims to develop a computational method to analyze the dynamics of lightweight deployable structures with low structural damping during the expansion and compression process. Since bar-joint structures is one of the most common types of deployable structures [23], here we take a bar-joint structure as an example to describe the governing equations of the developed method in this section, which contain link members and revolute joints allowing a relative rotation shown in Figure 1.Figure 1
Notations of a simple bar-joint structure.The equations of motion for deployable structures can be expressed in global coordinates as follows:(1)Mgd¨gt+Cgd˙gt+Kgdgt=Fbt,where Mg are the mass matrices, Cg are damping matrices, d¨gt, d˙gt, and dgt are, respectively, the acceleration, velocity, and displacement vectors of the structure at time t, Fbt is the external dynamic loading, and Kg are global stiffness matrices of the structure. In this study, only deployable structures with low structural damping have been paid attention to, so equation (1) does not require the damping matrix and can be rewritten as(2)Mgd¨gt+Kgdgt=Fbt.The global massMg and stiffness Kg matrices can be calculated by combining all individual elements mass Me and stiffness Ke matrices described in global coordinate. Here, each link member denoted as m with length l shown in Figure 1 can be defined as an element, and the notations of the element can also be found in Figure 1. The element has two nodes i and j. Xi=xi,yi and Xj=xj,yj, Fxim,Fyim and Fxjm,Fyjm, and νim,uim and νjm,ujm are, respectively, global Cartesian coordinate vectors, force vectors, and displacement vectors of the two nodes i and j. θm is the angle between the link member m and x-axis. The mass Me and stiffness Ke matrices for the element can be described as in global coordinate:(3)Me=TeTρAl62010020110200102Te,(4)Ke=TeTEAl10−100000−10100000Te,where ρ, A, and E are, respectively, the density, cross-sectional area, and elastic modulus of the link member.Te is transformation matrix from local Cartesian coordinates to global Cartesian coordinates and can be expressed as(5)Te=cosθmsinθm00−sinθmcosθm0000cosθmsinθm00−sinθmcosθm.


## 3. Implementation Strategy for Dynamic Analysis of Deployable Structures Using the Developed Method

Here, the following equations are used to solve equation (2) which controls the motion process of lightweight deployable structures without regard to structural damping in this study [24, 25]:(6)dgt+Δt=dgt+d˙gtΔt+12d¨gt+αd¨gt+Δt−d¨gtΔt2,(7)d˙gt+Δt=d˙gt+1−δd¨gt+δd¨gt+ΔtΔt,where Δt is the interval time integration and α and δ are model parameters.Based on equations (6) and (7), the recursive form of equation (2) can be expressed as follows:(8)1αΔt2Mg+Kgdgt+Δt=Fbt+Δt+12α−1Mgd¨gt+1αΔtMgd˙gt+1αΔt2Mgdgt.Based on the above description in this section, the solution strategy for dynamic analysis of deployable structures using the developed method can be described as follows:(1)
Calculate the global massMg and stiffness Kg matrices by combining all individual elements mass Me and stiffness Ke, respectively, as shown in equations (3) and (4).(2)
Set initial vectord˙gt0 and dgt0 and calculate d¨gt0=Mg−1Fbt0−Kgdgt0.(3)
ChooseΔt, α, and δ and calculate the following parameters:(9)A1=1αΔt2,A2=1αΔt,A3=12α−1.(4)
Calculate the global effective stiffness matricesK¯g by combining all individual elements’ effective stiffness K¯e, which can be expressed as(10)K¯e=Ke+Ken+A1Me,where Ken is caused by nonlinear geometry, which is the contribution of internal forces for the stiffness matrices, and can be expressed as(11)Ken=Felsin2θm−cosθmsinθm−sin2θmcosθmsinθm−sinθmcosθmcos2θmsinθmcosθm−cos2θm−sin2θmsinθmcosθmsin2θm−sinθmcosθmsinθmcosθm−cos2θm−sinθmcosθmcos2θm,where Fe is the axial force of the link member. Note that θm should be updated with time t since large rotation condition is considered here.(5)
Calculate the effective load matricesFb¯t0+Δt at time t0+Δt:(12)Fb¯t0+Δt=Fbt0+Δt+A3Mgd¨gt0+A2Mgd˙gt0+A1Mgdgt0.(6)
Calculate the displacement vectordgt0+Δt at time t0+Δt:(13)dgt0+Δt=K¯g−1Fb¯t0+Δt.(7)
Calculate the accelerationd¨gt0+Δt and velocity d˙gt0+Δt vectors at time t0+Δt:(14)d¨gt0+Δt=A1dgt0+Δt−dgt0−A2d˙gt0−A3d¨gt0,d˙gt0+Δt=d˙gt0+1−δd¨gt0+δd¨gt0+ΔtΔt.Using the above recursive process, we can calculate the motion process of the deployable structure under external dynamic loading within the whole time history.


## 4. Verification of the Developed Method

In this section, dynamics of a simple bar-joint structure, such as displacement, velocity, and acceleration, are studied. As shown in Figure2, the simple bar-joint structure is composed of eight nodes and twelve link members. The initial structural geometric size and material properties are given in Figure 2, and the coordinates of all nodes are also given. The cross-sectional area of the link member is 5×10−4m2.The elastic modulus E and density ρ are, respectively, chosen as 2.1GPa and 7801kg/m3 for steel. Boundary conditions and applied loading are also described in Figure 2. Node 1 can rotate but not move. The force of 10 N is applied on node 8 along z direction. We set initial velocity of all nodes to zero. Here, the values of α and δ in the method are, respectively, chosen as 0.253 and 0.505, and the value of Δt is chosen as 0.01 s.Figure 2
Initial mode shape of the deployable structure.The displacement, velocity, and acceleration of the deployable structure during the motion process without regard to gravity are computed using the developed method. In order to verify the effectiveness of the developed method, the simulation results are compared with the numerical results predicted by the authenticated multibody system dynamics and simulation software ADAMS. As shown in Figures3(a)–3(c), the displacement, velocity, and acceleration of node 8 shown in Figure 2 along z axis, respectively, predicted by the developed method and ADAMS are given. We can find that the simulation results predicted by the developed method and ADAMS are almost unanimous. The transformations of mode shapes for the structure during the motion process are also given in Figure 3(d). It shows that the developed method is effective to analyze the dynamics of the deployable bar-joint structure.Figure 3
Dynamic analysis of the deployable structure using the developed method and compared with numerical results predicted by ADAMS. (a)z-displacement of node 8. (b) z-velocity of node 8. (c) z-acceleration of node 8. (d) Transformations of mode shapes during the motion process.
(a)(b)(c)(d)


## 5. Dynamic Analysis for a Ring Array Scissor-Type Deployable Structure Using the Developed Method

As a case of application of the developed method, dynamics of a ring array scissor-type deployable structure are numerically analyzed. The initial structural geometric size and material properties of the ring array scissor-type deployable structure are given in Figure4. As shown in Figure 4, the ring array scissor-type deployable structure is composed of six same scissor units in each which four link members with the same length l are connected by a revolute joint for allowing rotation and translation. The angle θ between two nodes of every scissor unit and origin point O shown in Figure 4 has the same angle, i.e., π/3, in the ring array scissor-type deployable structure. The cross-sectional area of the link member is 4×10−4m2. The applied loading is also described in Figure 4, which is a decreasing function of time t. We set initial velocity of all nodes to zero. As described in Section 4, the elastic modulus E and density ρ are also, respectively, chosen as 2.1GPa and 7801kg/m3 for steel. The values of α and δ are, respectively, chosen as 0.253 and 0.505, and the value of Δt is chosen as 0.01 s.Figure 4
Initial mode shape of the ring array scissor-type deployable structure.The dynamics such as displacement, velocity, and acceleration of the deployable structure during the motion process without regard to gravity are computed using the developed method. As shown in Figures5–7, the displacement, velocity, and acceleration curves over time of node 1, node 2, and node 3 along x axis are predicted by the developed method and given. The transformations of mode shapes for the structure during the motion process for the time 0.2s, 0.6s, 1s, 1.4s, 1.8s, and 2.2s are also given in Figure 8. It shows that the developed method is also effective to analyze the dynamics of the ring array scissor-type deployable structure. And the displacement, velocity, and acceleration for the entire deployable structures during the motion process can be computed by the developed method. Meanwhile, different from traditional multi-rigid-body system dynamics and simulation program, the developed method can also be used to compute the dynamics of elastic deployable structures, which can be confirmed by this numerical example in this section. As shown in Figure 9, the cloud image for the axial strain of the entire structure during the motion process over time can be computed and given by the developed method.Figure 5
Curves ofx-displacement over time for some nodes in the deployable structure.Figure 6
Curves ofx-velocity over time for some nodes in the deployable structure.Figure 7
Curves ofx-acceleration over time for some nodes in the deployable structure.Figure 8
Transformations of mode shapes for the deployable structure during the motion process. (a) Time: 0.2 s. (b) Time: 0.6 s. (c) Time: 1 s. (d) Time: 1.4 s. (e) Time: 1.8 s. (f) Time: 2.2 s.
(a)(b)(c)(d)(e)(f)Figure 9
Axial strain for the deployable structure during the motion process. (a) Time: 0.2 s. (b) Time: 0.6 s. (c) Time: 1 s. (d) Time: 1.4 s. (e) Time: 1.8 s. (f) Time: 2.2 s.
(a)(b)(c)(d)(e)(f)Actually, if the elastic modulus of link member is set to a large enough value, the developed method in this study can also be used to compute the dynamics of the rigid deployable structures. In conclusion, the numerical examples, as described in Sections4 and 5, demonstrate that the developed method here can be used as an effective numerical tool to compute the dynamics of deployable structures no matter the structures are elastic or rigid.


## 6. Conclusions

The major conclusions can be summarized as follows:(1)
A computational method is developed to compute dynamics of lightweight deployable structures without regard to damping during the expansion or compression process.(2)
As a case study, it shows that dynamics such as displacement, velocity, and acceleration for the entire deployable structures during the motion process can be computed by the method, as well as the strain if the structures are elastic.(3)
By comparison of the numerical results, respectively, predicted by the developed method and ADAMS, it shows that the method is effective for dynamic analysis of the deployable structures.(4)
From the numerical analysis, the developed method is effective for the dynamic analysis of the elastic or rigid deployable structures.



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*Source: 2971784-2020-06-27.xml*