# The Pretension Design of Cable Mesh considering the Large Deformation of Ring Truss

Authors: Hu Jianfeng; Wang Lipeng; Yang Jungang
Journal: International Journal of Aerospace Engineering
 (2023)

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## Abstract

The conventional pretension design of cable mesh usually takes the ring truss as a rigid body or assumes small deformation. This method needs to be more accurate in designing super large aperture antennas. A cable mesh design method considering the large deformation of the ring truss is proposed in this paper based on the flexible multibody dynamics (FMD) and the force density method (FDM). With this method, the significant range deviation of the boundary points’ position of the ring truss under the tension of the external area of the cable mesh after the completion of the pretension design can be predicted with high accuracy. After the ring truss and cable mesh surface are assembled stably, there is only a minimal deviation between the actual mesh surface and the theoretical mesh surface of the antenna, and there is only a minimal deviation between the genuine mesh pretension and the design pretension. The above calculation method is verified by numerical simulation, and the simulation results show that the technique can be applied to the mesh pretension design of a super large aperture ring deployable antenna.


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## Body

## 1. Introduction

With the development of electronic reconnaissance and mobile communications, the demand for a super large aperture antenna is increasingly urgent. The large ring deployable antenna has become one of the research hot spots in the world for its lightweight and high storage ratio [1, 2]. The deployable ring antenna mainly consists of a ring truss, front mesh, metal mesh, rear mesh, and tension ties, as shown in Figure 1(a). The ring truss is mainly composed of the quadrilateral element that consists of the longeron, batten, thick diagonal, thin diagonal, T-shaped connection, and synchronous connection, as shown in Figure 1(b). The rod is usually made of light and long composite thin-walled pipe fittings, and the connection is usually made of high-strength and high-rigidity metal. The connecting part between the cable mesh and the ring truss is called the external mesh area; the rest is called the internal mesh area. The mesh model pretension design is one of the key issues that researchers focus on during the development of the deployable ring antenna [3–5]. At present, the cable mesh pretension design methods of large deployment antennae include the force density method [6, 7], the equilibrium matrix method [8, 9], and the dynamic relaxation method [5]. In addition, in recent years, some scholars have assumed that the ring truss occurs small deformation and performed the cable mesh pretension design by using the overall calculation method of the ring antenna [10, 11]. The above methods usually assume that the ring truss is rigid or occurs small deformation in the design of mesh pretension. However, with the increased antenna aperture, the super large aperture ring truss always produces large deformation and displacement under the cable mesh tension. With the mesh pretension design method that assumes the ring truss is rigid or occurs small deformation for super large aperture ring antenna, if the mesh is connected to the deployable truss according to the theoretical design in the real assembly environment, the connection nodes for the mesh and ring truss are deviated from the initial design and the mesh pretension is reduced to a certain extent compared with the initial pretension. Therefore, the mesh surface accuracy and pretension cannot meet the initial design requirements. The larger the reflector aperture, the greater the difference, as shown in Figure 2.Figure 1
The composition of the ring deployable antenna.
(a)
Components of AstroMesh I antenna(b)
Quadrilateral elementFigure 2
The deformation of the ring truss under the cable mesh tension.In recent years, researchers from Tsinghua University and China Academy of Space Technology applied the flexible multibody system dynamic theory to the dynamic simulation of the deployment process and structural optimization design of large deployable antenna [12–17]. They precisely predicted the large deformation and displacement of flexible rods which cannot be completed by the traditional finite element method during the deployment process of a large deployable antenna in ground test and orbit environments, and the simulation is proved by ground tests and observation in space.However, few literatures are found on the research of the mesh design for super large aperture antennas. For this purpose, this paper proposes a cable mesh pretension method that considers the large deformation of the ring truss based on the flexible multibody dynamic theory as mentioned above. This method takes the large displacement and deformation of the ring truss under the mesh pretension into full consideration. Therefore, the connection node for the ring truss and the cable mesh after deformation has a very minimal deviation from the theoretical design. In this way, the mesh pretension is almost consistent with the design pretension. Finally, the antenna has high mesh surface accuracy, and the actual mesh and design pretension meet the accuracy requirements. The simulation results show that this method is correct and effective and can be used for the cable mesh design of the deployable ring antenna with a super large aperture.


## 2. The Force Density Method

The force density method is basically to establish the force equilibrium equation of each node on the equilibrium geometries of the cable mesh structure and convert the nonlinear balance equation into a linear system of equations for the solution by introducing the force density [18, 19].As shown in Figure3, the force equilibrium equation of the node i in the direction x in the mesh structure equilibrium state is
(1)∑j∈UiTijLijxi−xj=fix.Figure 3
The force density method description.In Formula (1), Ui is a set of nodes connected to node i. ij is the element that connects node i and node j. Tij is the tension of the element ij, and Lij is the length of the element ij.Ifqij=Tij/Lij is defined as the force density of the element ij, the above formula can be expressed as
(2)∑j∈Uiqijxi−xj=fix.The force equilibrium equation for all nodes in the directionx in the mesh structure equilibrium state is written in the matrix form
(3)CTQCx=fx,where C is the structural topology matrix of m×n, m is the total number of cable elements, n is the total number of nodes, and Q is a diagonal matrix of m×m consisting of the force density of cable elements. Suppose that in the n nodes, the number of free nodes is nf, the number of fixed nodes is ng, and the topological matrix C are divided into blocks Cf and Cg. xf is the coordinate of free nodes, xg is the coordinate of fixed nodes, the external force on free nodes is equal to 0, and fxg is the reaction force of fixed node support. Therefore, Formula (3) can be expressed as
(4)CfCgQCfCgxfxg=0fxg.By solving Formula (4), the coordinates of all free nodes in the direction x and the force of fixed nodes in the direction x are obtained.Similarly, the force equilibrium matrix of nodesy and z can be obtained. Thus, the coordinates of all free nodes and the fixed node forces are obtained. According to the obtained node coordinates, the length Lij of the cable segment at the time of force balance can be calculated, and then, the cable force Tij at the time of balance can be obtained by using qij=Tij/Lij. The pretension form finding for the ring deployable antenna is to ensure that by finding a set of force density, the coordinates of the free nodes of the cable mesh are at the theoretic coordinates when the cable mesh is balanced, and the cable mesh tension is as uniform as possible. In this paper, the objective optimization mathematical model is established with the cable segment force density as the design parameter. The optimization model is shown in Formula (5).
(5)Findq1,q2,⋯qm,Minf=TmaxTmin,s.t.CTQCx=fx,CTQCy=fy,CTQCz=fz,0<qi<q,i=1~m,zfi=xfi2+yfi24f,xgi,ygi,zgiT=const,where qi is the force density of each segment, m is the number of segments for the cable structure, f is the objective function, q is the maximum design allowable value of the force density of the cable segment, fi is the number of free nodes, and gi is the number of fixed nodes.


## 3. Dynamic Modelling of the Large Ring Truss

The deployable ring truss consists of the hinge with minimal deformation and the rod with large deformation. This paper assumes that the hinge is rigid, and its model is built based on the rigid body dynamics theory. The rod model is based on the geometrically exact beam theory [20, 21]. Finally, the constraints model is built based on the multirigid-body dynamic theory.In the study of the flexible multibody dynamics, Lagrange’s equation of first kind is adopted as the governing equation of the system dynamics as shown in Formula (6)
(6)ddt∂T∂q̇−∂T∂q+∂V∂q+ΦqTλ=Q,Φq,t=0,where T is kinetic energy, q is generalized coordinate, q̇ is generalized speed, V is elastic potential energy, Φ is constraint equations, λ is the Lagrange multiplier, and Q is the generalized external force.


### 3.1. Rigid Body Modelling

The motion of a rigid body in three-dimensional space can be divided into the translation in three directions and the rotation in three directions. Each rigid body has 6-degree of freedom. In selecting generalized coordinates, the position of the center of mass of the rigid body is used to determine the translational configuration, there are many descriptions of rotation in literature [22]. In this paper, the rotation vector method is used to describe the rotation of a rigid body. According to Euler’s rotation theorem and the definition of the rotation vector [22], the rotation vector φ is parallel to the rotation axis a, and the modulus is equal to the rotation angle. The conversion relationship from rotation vector φ to rotation matrix A is
(7)A=I+h1φ~+h2φ~φ~,where I is the 3D identity matrix and h1 and h2 are the functions of the rotation angle φ(8)h1=sinφφ,h2=1−cosφφ2.φ~ is the antisymmetric matrix of the rotation vector φ, and the three Cartesian components φ1, φ2, and φ3 using φ can be expressed as
(9)φ~=0−φ3φ2φ30−φ1−φ2φ10.The component formω and the rotation vector φ̇ of the angular velocity of the local coordinate system in the global coordinate system satisfy the following conversions to the time derivative:
(10)ω=Hφφ̇,H=h1I−h2φ~+h3φφT,where
(11)h3=φ−sinφφ3.In addition, the component formω¯ of the angular velocity of the rotation system of coordinates in the local coordinate system can be obtained by ω multiplying the inverse matrix of A(12)ω¯=ATω=ATHφ̇.It can be further proved that(13)HT=ATH.Finally, we can get(14)ω¯=HTφ̇.Considering that the rigid body has no elastic potential energy term, Formula (6) can be simplified as
(15)ddt∂T∂q̇T+ΦqTλ=Q,Φq,t=0,where q=riφi .The kinetic energy expression in the above formula is
(16)T=12miṙiTṙi+12ω¯iTJiω¯i,where J is the moment of inertia in the center of mass coordinate system.


### 3.2. Flexible Body Modelling

Under the external mesh cable tension, the composite thin-walled pipe fittings of the ring truss will have large-scale displacement and large deformation. According to the geometrically exact beam theory, the section curvature of any beam element with large deformation and large-scale rotation is geometrically accurate. Therefore, the model of the composite thin-walled rods using the geometrically exact beam theory is more accurate than the conventional finite element method. This paper uses the flexible beam model based on the geometrically exact beam theory. In the modeling process, the centerline positionr at the left and right ends of the beam element and the rotation vector φ is selected as the generalized coordinates to describe the beam element configuration, as shown in Figure 4.Figure 4
Flexible beam element.The generalized coordinates of the beam element can be expressed as(17)qb=r1Tφ1Tr2Tφ2TT.For the interpolation of the rotation vectorφ, Crisfield and Jelenić [23] proposed to establish a reference coordinate system in the beam element and interpolate the rotation vector under the reference coordinate system. Without the influence of the reference coordinate system, the curvature obtained based on this calculation can be the same in any observation coordinate system. In this paper, the rotation vector is interpolated according to this method. The rotation vector of any node relative to the reference coordinate system is written as φr. According to the above, any node of the centerline in the beam element r and φr are expressed as follows:
(18)r=1−ξr1+ξr2,φr=1−ξφ1r+ξφ2r,where ξ∈0,1 is the parameter coordinates in the beam element. According to the above beam element functions, it can be expressed as follows:
(19)Tb=L2∫01ρAṙTṙ+ω¯TJω¯dξ,where L is the length of the beam element and A is the cross-section area of the element.The beam element’s potential energy can be expressed as(20)V=L2∫01NTγ−γ0+MTκ−κ0dξ,where
(21)γ=ATr′,κ=HTφ′,N=CNγ−γ0,M=CMκ−κ0,where γ is the strain vector, γ0 is the initial strain vector, κ is the curvature vector, κ0 is the initial curvature vector, and N and M are section force and moment, respectively. The above physical quantities can be expressed using the generalized coordinates. CN and CM are the constitutive matrix only related to the material and the section features.


### 3.3. Constraint Modelling

In the deployed state, the deployable ring antenna features a fixed constraint between the hinge and the batten, a fixed constraint between the thick diagonal and thin diagonal, and a rotational constraint between the thin diagonal and the hinge.The beam section can be regarded as the rigid body according to the geometrically exact beam theory. Therefore, the constraint model can be processed as follows. Assuming a mark point on a beam section, the position and attitude of the mark point relative to the section center point will not change during the movement. Assuming that the coordinate system described by the attitude of the center point of the section is the rigid body coordinate system, record the relative position of the initial mark point in the coordinates system of the rigid body asrm. The component forms of this point in the coordinates system of the rigid body are recorded as xm, ym, and zm. If the position of the section center point in the global coordinate system is r, the rotation vector is ϕ, and the vector rotation matrix is A, the position Rm of the mark point in the global coordinate system is
(22)Rm=r+Arm.In addition, the axial componentsxm, ym, and zm of the mark point in the rigid body coordinate system and the components Xm, Ym, and Zm in the global coordinate system are, respectively,
(23)Xm=Axm,Ym=Aym,Zm=Azm.Assume that the mark points of two different components forming a fixed constraint are, respectively,i and j. The fixed constraint requires that the position and altitude of two-mark points coincide completely and include 6 constraint equations.
(24)Rim−Rjm=0,Xim⋅Zjm=0,Xim⋅Yjm=0,Yim⋅Zjm=0.Similarly, assume that two-mark points of two different components forming the revolute constraint arei and j. The revolute constraint requires that the positions of two-mark points coincide completely, and one of the coordinate systems coincides completely. The rotation around this axis is allowed between two-mark points. Assuming the rotation is around the z-axis, it contains five constraint equations.
(25)Rim−Rjm=0,Xim⋅Yjm=0,Xim⋅Zjm=0.


### 3.4. Large Deformation Numerical Example

A classical large deformation flexible beam test example [21, 24–26] (shown in Figure 5) is carried out to prove the availability of the proposed method in large deformation simulation calculation, and the test results are compared with the calculation results of commercial software Ansys Workbench 2020. There is an analytical solution for the concentrated bending moment of this cantilever beam; therefore, it is widely used in the test of large deformation beam modeling method.Figure 5
Cantilever beam undergoes bending load.The structural parameters of the cantilever beam are shown in Figure5. During the calculation, the cantilever beam is divided by 10 elements. The proposed method integral error is set to 1e−3 in this paper. The beam element is modelled by Beam188, and the convergence criterion is carried out according to the system default criterion in Ansys.According the test results shown in Tables1 and 2 and Figure 6,when the applied torque does not exceed 0.4πEI/L, the difference between the calculation of 10 elements using the proposed method and the theoretical value is within 1%, while Ansys has an error within 0.01%. When the applied torque is not lower than 0.6πEI/L, Ansys has a larger error and its calculation even cannot converge. However, the proposed method still has high calculation accuracy, with the maximum within 2.8%.Table 1
Comparison of tip axial displacement using FDM and Ansys (m).
ML/πEIAnalyticalFDMAnsys0.20.645110.639370.645190.42.431732.409262.431910.64.954494.854514.448310.87.661287.56397Unconverged110.000009.96377UnconvergedTable 2
Comparison of tip vertical displacement using FDM and Ansys (m).
ML/πEIAnalyticalFDMAnsys0.23.039583.018943.039710.45.498665.477495.498800.66.944556.971156.672730.87.197857.30276Unconverged16.366206.54480UnconvergedFigure 6
Large deformation of the cantilever under bending moments.The error can be further reduced to 0.05% by dividing into 50 elements with the proposed method. Even if Ansys increases the step size by 100 times and dividing into 100 elements, its calculation results cannot converge when calculating the applied torqueM=πEI/L.By comprehensive consideration, the proposed modeling method has more advantages than Ansys when dealing with the large deformation flexible beam element model.


## 3.1. Rigid Body Modelling

The motion of a rigid body in three-dimensional space can be divided into the translation in three directions and the rotation in three directions. Each rigid body has 6-degree of freedom. In selecting generalized coordinates, the position of the center of mass of the rigid body is used to determine the translational configuration, there are many descriptions of rotation in literature [22]. In this paper, the rotation vector method is used to describe the rotation of a rigid body. According to Euler’s rotation theorem and the definition of the rotation vector [22], the rotation vector φ is parallel to the rotation axis a, and the modulus is equal to the rotation angle. The conversion relationship from rotation vector φ to rotation matrix A is
(7)A=I+h1φ~+h2φ~φ~,where I is the 3D identity matrix and h1 and h2 are the functions of the rotation angle φ(8)h1=sinφφ,h2=1−cosφφ2.φ~ is the antisymmetric matrix of the rotation vector φ, and the three Cartesian components φ1, φ2, and φ3 using φ can be expressed as
(9)φ~=0−φ3φ2φ30−φ1−φ2φ10.The component formω and the rotation vector φ̇ of the angular velocity of the local coordinate system in the global coordinate system satisfy the following conversions to the time derivative:
(10)ω=Hφφ̇,H=h1I−h2φ~+h3φφT,where
(11)h3=φ−sinφφ3.In addition, the component formω¯ of the angular velocity of the rotation system of coordinates in the local coordinate system can be obtained by ω multiplying the inverse matrix of A(12)ω¯=ATω=ATHφ̇.It can be further proved that(13)HT=ATH.Finally, we can get(14)ω¯=HTφ̇.Considering that the rigid body has no elastic potential energy term, Formula (6) can be simplified as
(15)ddt∂T∂q̇T+ΦqTλ=Q,Φq,t=0,where q=riφi .The kinetic energy expression in the above formula is
(16)T=12miṙiTṙi+12ω¯iTJiω¯i,where J is the moment of inertia in the center of mass coordinate system.


## 3.2. Flexible Body Modelling

Under the external mesh cable tension, the composite thin-walled pipe fittings of the ring truss will have large-scale displacement and large deformation. According to the geometrically exact beam theory, the section curvature of any beam element with large deformation and large-scale rotation is geometrically accurate. Therefore, the model of the composite thin-walled rods using the geometrically exact beam theory is more accurate than the conventional finite element method. This paper uses the flexible beam model based on the geometrically exact beam theory. In the modeling process, the centerline positionr at the left and right ends of the beam element and the rotation vector φ is selected as the generalized coordinates to describe the beam element configuration, as shown in Figure 4.Figure 4
Flexible beam element.The generalized coordinates of the beam element can be expressed as(17)qb=r1Tφ1Tr2Tφ2TT.For the interpolation of the rotation vectorφ, Crisfield and Jelenić [23] proposed to establish a reference coordinate system in the beam element and interpolate the rotation vector under the reference coordinate system. Without the influence of the reference coordinate system, the curvature obtained based on this calculation can be the same in any observation coordinate system. In this paper, the rotation vector is interpolated according to this method. The rotation vector of any node relative to the reference coordinate system is written as φr. According to the above, any node of the centerline in the beam element r and φr are expressed as follows:
(18)r=1−ξr1+ξr2,φr=1−ξφ1r+ξφ2r,where ξ∈0,1 is the parameter coordinates in the beam element. According to the above beam element functions, it can be expressed as follows:
(19)Tb=L2∫01ρAṙTṙ+ω¯TJω¯dξ,where L is the length of the beam element and A is the cross-section area of the element.The beam element’s potential energy can be expressed as(20)V=L2∫01NTγ−γ0+MTκ−κ0dξ,where
(21)γ=ATr′,κ=HTφ′,N=CNγ−γ0,M=CMκ−κ0,where γ is the strain vector, γ0 is the initial strain vector, κ is the curvature vector, κ0 is the initial curvature vector, and N and M are section force and moment, respectively. The above physical quantities can be expressed using the generalized coordinates. CN and CM are the constitutive matrix only related to the material and the section features.


## 3.3. Constraint Modelling

In the deployed state, the deployable ring antenna features a fixed constraint between the hinge and the batten, a fixed constraint between the thick diagonal and thin diagonal, and a rotational constraint between the thin diagonal and the hinge.The beam section can be regarded as the rigid body according to the geometrically exact beam theory. Therefore, the constraint model can be processed as follows. Assuming a mark point on a beam section, the position and attitude of the mark point relative to the section center point will not change during the movement. Assuming that the coordinate system described by the attitude of the center point of the section is the rigid body coordinate system, record the relative position of the initial mark point in the coordinates system of the rigid body asrm. The component forms of this point in the coordinates system of the rigid body are recorded as xm, ym, and zm. If the position of the section center point in the global coordinate system is r, the rotation vector is ϕ, and the vector rotation matrix is A, the position Rm of the mark point in the global coordinate system is
(22)Rm=r+Arm.In addition, the axial componentsxm, ym, and zm of the mark point in the rigid body coordinate system and the components Xm, Ym, and Zm in the global coordinate system are, respectively,
(23)Xm=Axm,Ym=Aym,Zm=Azm.Assume that the mark points of two different components forming a fixed constraint are, respectively,i and j. The fixed constraint requires that the position and altitude of two-mark points coincide completely and include 6 constraint equations.
(24)Rim−Rjm=0,Xim⋅Zjm=0,Xim⋅Yjm=0,Yim⋅Zjm=0.Similarly, assume that two-mark points of two different components forming the revolute constraint arei and j. The revolute constraint requires that the positions of two-mark points coincide completely, and one of the coordinate systems coincides completely. The rotation around this axis is allowed between two-mark points. Assuming the rotation is around the z-axis, it contains five constraint equations.
(25)Rim−Rjm=0,Xim⋅Yjm=0,Xim⋅Zjm=0.


## 3.4. Large Deformation Numerical Example

A classical large deformation flexible beam test example [21, 24–26] (shown in Figure 5) is carried out to prove the availability of the proposed method in large deformation simulation calculation, and the test results are compared with the calculation results of commercial software Ansys Workbench 2020. There is an analytical solution for the concentrated bending moment of this cantilever beam; therefore, it is widely used in the test of large deformation beam modeling method.Figure 5
Cantilever beam undergoes bending load.The structural parameters of the cantilever beam are shown in Figure5. During the calculation, the cantilever beam is divided by 10 elements. The proposed method integral error is set to 1e−3 in this paper. The beam element is modelled by Beam188, and the convergence criterion is carried out according to the system default criterion in Ansys.According the test results shown in Tables1 and 2 and Figure 6,when the applied torque does not exceed 0.4πEI/L, the difference between the calculation of 10 elements using the proposed method and the theoretical value is within 1%, while Ansys has an error within 0.01%. When the applied torque is not lower than 0.6πEI/L, Ansys has a larger error and its calculation even cannot converge. However, the proposed method still has high calculation accuracy, with the maximum within 2.8%.Table 1
Comparison of tip axial displacement using FDM and Ansys (m).
ML/πEIAnalyticalFDMAnsys0.20.645110.639370.645190.42.431732.409262.431910.64.954494.854514.448310.87.661287.56397Unconverged110.000009.96377UnconvergedTable 2
Comparison of tip vertical displacement using FDM and Ansys (m).
ML/πEIAnalyticalFDMAnsys0.23.039583.018943.039710.45.498665.477495.498800.66.944556.971156.672730.87.197857.30276Unconverged16.366206.54480UnconvergedFigure 6
Large deformation of the cantilever under bending moments.The error can be further reduced to 0.05% by dividing into 50 elements with the proposed method. Even if Ansys increases the step size by 100 times and dividing into 100 elements, its calculation results cannot converge when calculating the applied torqueM=πEI/L.By comprehensive consideration, the proposed modeling method has more advantages than Ansys when dealing with the large deformation flexible beam element model.


## 4. The Cable Mesh Design Process

The cable mesh design process is shown in Figure7. Firstly, at the initial theoretic boundary C0 of the truss, the initial mesh model is built using FDM and the mesh tension is optimized to be uniform. Then, the first set of mesh coordinates and the mesh element tension is obtained. The force F0 of the external mesh cable to the deployable truss at the connection between the cable mesh and the deployable truss is obtained. The large deformation rod model is built based on the geometrically exact beam theory. The minimal deformation hinge model and the constraint model are built based on the multirigid-body dynamic theory, thus achieving the dynamic modelling of the deployable truss. Considering that the cable mesh is connected to the deployable truss through the external mesh cable, the force F0 of the external mesh cable is applied to the deployable truss. The coordinates C1 of the deployable truss boundary after the deformation under the action F0 of the external mesh cable are obtained, and the displacement variation of each point ξ1 and the maximum displacement variation ξ1max are calculated.Figure 7
Antenna cable mesh design process.When the calculation timek>1, only taking the new truss boundary Ck−1 instead of the initial one and ensuring the others are unchanged (Formula (5)), a set of new mesh coordinates and the mesh element tension are obtained and the force Fk−1 of the external mesh cable to the deployable truss at the connection between the mesh and the deployable truss is extracted.The newly obtained external mesh cable tensionFk−1 is applied to the deployable truss to obtain the coordinates Mk of the truss boundary after deformation. The displacement variation ξk of each node from the previous and the maximum displacement variation ξkmax are calculated.Whenξkmax<ξk−1max, set the next calculation truss boundary Ck=Mk or set Ck=Ck−1+Mk−Ck−1/2.The difference between the relative distances of the truss boundary for thek time and for the k−1 time should be less than the allowable error, that is ξkmax−ξk−1max≤tol. The error size is related to the mesh surface accuracy and the mesh tension uniformity. If the above requirement is not satisfied, continue to perform step (3); otherwise, stop the calculation. The mesh is connected to the deployable truss without apparent position deviation or tension change due to truss deformation. The internal node coordinates and the mesh tension meet the theoretical design.


## 5. Simulation Example

The calculation program for the cable mesh design can be obtained through the numerical simulation and programming of the above cable mesh design method. In addition, the pretension design of a positive-feed ring deployable antenna with a 26 m aperture is performed in this paper. The primary antenna parameters are shown in Table3.Table 3
The parameters of simulation model.
ItemCalculation parametersAntenna aperture26 mAntenna focal length4 mRod inner diameter22 mmRod outer diameter24 mmRod elastic modulus160 GPaCable diameter5 mmCable elastic modulus50 GPaThe average tension of front mesh70 NThe average tension of rear mesh180 NMultiple iterative calculations are carried out through the above cable mesh design method. It can be seen from Figure8 that in the early stage of iteration, the maximum displacement change before and after the boundary point deformation decreases rapidly. At the end of the iteration, the change is slow. After 13 counts, the maximum deviation of front and rear boundary points is less than 0.1 mm. When the maximum deviation is less than 0.1 mm, the cable mesh model is built based on the geometrically exact beam theory and the previous modeling method for the ring truss. After the cable mesh system is stable, the RMS deviation of the mesh surface accuracy from the theoretical form is only 0.006 mm, and the change of the cable mesh pretension is less than 0.5% of the initial design.Figure 8
The change of the maximum deviation distance of boundary points with iterations.


## 6. Discussion

At present, the pretension design process of large deployable ring antenna cable mesh is based on the assumption of rigidity or small deformation of the ring truss. However, large displacement and large deformation of the super large ring truss occur under the tension of the cable mesh, and the calculation accuracy is insufficient if the traditional method is used. Therefore, this paper proposes a cable mesh pretension method that considers the large deformation of the ring truss. According to the simulation test results, this method can ensure that the antenna mesh model has high accuracy and that the cable mesh pretension and the initial design pretension change very little after the whole ring antenna has stable cable mesh pretension. Therefore, it can be used to guide the design of the cable mesh pretension for the deployable ring antenna with a super large aperture.Considering the discreteness of mechanical properties of different composite thin-walled pipe fittings, it is to achieve a more accurate design of cable mesh, the mechanical parameters of the bar can be tested and updated to the calculation program.The mesh is usually not unloaded during the development of large ring deployable antenna. For the super large aperture ring deployable antenna, the weight of cable mesh will significantly impact the antenna surface accuracy and the mesh pretension distribution. According to the FDM, relevant modeling and simulation can be carried out in the ground gravity environment to guide the profile adjustment in the gravity environment to ensure that the antenna meets the surface accuracy and cable mesh tension requirements in orbit.



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*Source: 1282797-2023-03-11.xml*