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[结构分析] Ansys命令流经典实例分享

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发表于 2015-10-5 21:55 | 显示全部楼层 |阅读模式

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本帖最后由 Jillian 于 2015-10-5 22:00 编辑

变形释放载荷经典例子
模型解释:(1)一个弹性结构受压(接触)变形,到发生塑性变形。(2)拿开压缩板,结构回弹,但不会回到原始位置。(3)这时计算蠕变,释放掉应力。(4)再压弹性结构到开始压缩位置。比较这四步的接触力。结果:第二,三步当然没有接触力,(若没有应力释放,第一、第四步接触力应一样,)有了应力释放,第四步接触力比第一步减小。

这个模型中的蠕变没用太好。用的是隐式6号蠕变方程,蠕变是时间和应力的函数,参数是乱定的(应力释放太快)。

  1. /prep7
  2.   
  3. !------------CuSn8----------
  4.   
  5. ET,1,182,,,3
  6. mp,ex,1,115e9
  7. mp,prxy,1,0.3
  8. r,1,0.3
  9.   
  10. TB,BKIN,1
  11. TBDATA,1,470E6,0      
  12.   
  13. tm=100
  14. *SET,C1,1.5625E-14      !ASSIGN VALUE
  15. *SET,C2,1.5        !ASSIGN VALUE
  16. *SET,C3,        !ASSIGN VALUE
  17. *SET,C4,0        !ASSIGN VALUE
  18. TB,CREEP,1,,,6        !ACTIVATE DATA TABLE
  19. TBDATA,1,C1,C2,C3,C4      !DEFINE DATA FOR TABLE
  20.   
  21. !-----------contact-----------------
  22. ET,9,169
  23. ET,10,171   
  24. R,9,,,0.1,0.1,,  
  25. !RMORE,,,1.0E20,0.0,1.0,  
  26. !RMORE,0.0,0,1.0,0,0,0.5  
  27. !RMORE,,,1.0,0.0  
  28. MP,MU,9,0.0
  29.   
  30. !----------------geometry  
  31.   
  32. k,,2
  33. k,,2,0.2
  34. k,,,0.2
  35. k,,-0.2
  36. k,,-0.2,1.2
  37. k,,,1
  38. k,,2,1.2
  39. k,,1,1
  40. k,,1.25,1
  41. k,,2,1
  42. L,8,9,
  43.   
  44. k,,1.5,1.2
  45. k,,1.75,1.45
  46.   
  47. L,       1,       2  
  48. L,       1,       4  
  49. L,       4,       5  
  50. L,       5,      11  
  51.   
  52. larc,7,12,11,0.25
  53. larc,11,12,7,0.25
  54. L,       7,      10  
  55. L,      10,       9  
  56. L,       8,       6  
  57. L,       6,       3  
  58. L,       3,       2  
  59.   
  60. LFILLT,11,10,0.3, ,  
  61. !*   
  62. LFILLT,4,5,0.5, ,   
  63. !*   
  64. LFILLT,11,12,0.3, ,  
  65. !*   
  66. LFILLT,4,3,0.5, ,   
  67.   
  68.    
  69. FLST,2,16,4  
  70. FITEM,2,12   
  71. FITEM,2,15   
  72. FITEM,2,11   
  73. FITEM,2,13   
  74. FITEM,2,10   
  75. FITEM,2,1   
  76. FITEM,2,9   
  77. FITEM,2,8   
  78. FITEM,2,7   
  79. FITEM,2,6   
  80. FITEM,2,5   
  81. FITEM,2,14   
  82. FITEM,2,4   
  83. FITEM,2,16   
  84. FITEM,2,3   
  85. FITEM,2,2   
  86. AL,P51X  
  87.   
  88. rect,1,3,1.45+0.001,1.5
  89.   
  90. type,1
  91. mat,1
  92.   
  93. esize,0.05
  94. amesh,all
  95.   
  96. !---------contact------------
  97.   
  98. alls
  99.   
  100. type,10
  101. mat,9
  102. real,9
  103.   
  104. lsel,s,,,6,7
  105. nsll,s,1
  106. esln,s,0
  107. esurf,all
  108.   
  109. type,9
  110. mat,9
  111. real,9
  112.   
  113. lsel,s,,,17
  114. nsll,s,1
  115. esln,s,0
  116. esurf,all
  117.   
  118. !------boundary
  119.   
  120. lsel,s,,,3
  121. nsll,,1
  122. d,all,ux
  123. d,all,uy
  124.   
  125. lsel,s,,,19
  126. nsll,,1
  127. cp,11,uy,all
  128. cplgen,11,ux
  129. *get,nmin,node,,num,min
  130. d,nmin,ux
  131.   
  132. ksel,s,,,10
  133. nslk
  134. *get,ndis,node,,num,min
  135.   
  136. fini
  137.   
  138. /solu
  139.   
  140. antype,static
  141.   
  142. nlgeom,on
  143. autots,on
  144.   
  145. alls
  146.   
  147. save
  148.   
  149. rate,off
  150. time,1e-8
  151.   
  152. d,nmin,uy,-0.3
  153. nsub,20
  154. outres,all,all
  155. solve
  156.   
  157. *get,rf1,node,nmin,rf,fy
  158. *get,dis1,node,ndis,u,y
  159.   
  160. time,2e-8
  161.   
  162. d,nmin,uy,0.0
  163. nsub,20
  164. outres,all,all
  165. solve
  166.   
  167. *get,rf2,node,nmin,rf,fy
  168. *get,dis2,node,ndis,u,y
  169.   
  170. !BFUNIF,TEMP,90
  171. rate,on
  172. TIME,tm
  173. !NSUBST,10
  174. OUTPR,BASIC,10         ! PRINT BASIC SOLUTION FOR EVERY 10TH SUBSTEP
  175. OUTRES,ESOL,1          ! STORE ELEMENT SOLUTION FOR EVERY SUBSTEP
  176. SOLVE
  177.   
  178. *get,rf3,node,nmin,rf,fy
  179. *get,dis3,node,ndis,u,y
  180.   
  181. rate,off
  182. time,tm+1e-8
  183.   
  184. d,nmin,uy,-0.3
  185. nsub,20
  186. outres,all,all
  187. solve
  188.   
  189. *get,rf4,node,nmin,rf,fy
  190. *get,dis4,node,ndis,u,y
  191.   
  192. /EOF
  193.   
  194. time,11
  195.   
  196. d,nmin,uy,-0.0
  197. nsub,20
  198. outres,all,all
  199. solve
  200.   
  201. *get,rf11,node,nmin,rf,fy
  202. *get,dis11,node,ndis,u,y
  203.   
  204. /eof
  205.   
  206. fini
  207.   
  208. /post1
  209.   
  210. *get,rf2,node,nmin,rf,fy
  211. fini
  212.   
  213. /eof
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 楼主| 发表于 2015-10-5 21:57 | 显示全部楼层
高速铁路轨道有限元分析
  1. RESUME,rail_2Dmesh,db   ! 重新开始,导入二维网格划分后的模型
  2. /prep7                           ! 进入前处理
  3. NUMMRG,ALL, , , ,LOW    ! 合并重节点,保留低编号
  4. NUMCMP,ALL                  ! 压缩编号
  5. EXTOPT,ESIZE,30,-0.3    ! 拖拉设置,在拖拉方向产生30个单元,
  6.                                     ! 最小的单元是最大单元的0.3,
  7.                                    ! 负号表示中间的单元小,两头的单元大
  8. EXTOPT,ACLEAR,0         ! 拖拉后不删除原来的面
  9. EXTOPT,ATTR,0,0,0   
  10. MAT,1                          ! 拖拉后,体的材料特性
  11. REAL,_Z4                     ! 拖拉后,体的实常数(默认)
  12. ESYS,0                       ! 单元坐标系(默认)
  13. VOFFST,1,568,           ! 将面1向正法线方向拖拉568个单位
  14. VOFFST,2,568,           ! 将面2向正法线方向拖拉568个单位
  15. VOFFST,3,568,           ! 将面3向正法线方向拖拉568个单位
  16. NUMMRG,ALL, , , ,LOW     
  17. NUMCMP,ALL               
  18.   
  19. EXTOPT,ESIZE,20,        ! 拖拉设置,在拖拉方向产生20个单元,
  20.                                   ! 各个单元大小相等
  21. EXTOPT,ACLEAR,0  
  22. EXTOPT,ATTR,0,0,0   
  23. MAT,1   
  24. REAL,_Z4
  25. ESYS,0   
  26. VOFFST,1,-568,            ! 将面1向负法线方向拖拉568个单位
  27. VOFFST,2,-568,            ! 将面2向负法线方向拖拉568个单位
  28. VOFFST,3,-568,            ! 将面3向负法线方向拖拉568个单位
  29. NUMMRG,ALL, , , ,LOW
  30. NUMCMP,ALL  
  31.   
  32. VGEN,2,4, , ,1136        ! 体复制,将4号体复制一份到沿正法线方向
  33.                                  ! 1136单位处(以现在位置为起点的相对距离)
  34. VGEN,2,5, , ,1136        ! 体复制,将5号体复制一份到沿正法线方向
  35.                                  ! 1136单位处(以现在位置为起点的相对距离)
  36. VGEN,2,6, , ,1136        ! 体复制,将6号体复制一份到沿正法线方向
  37.                                  ! 1136单位处(以现在位置为起点的相对距离)
  38. NUMMRG,ALL, , , ,LOW
  39. NUMCMP,ALL  
  40.   
  41. VGEN,2,4, , ,-568        ! 体复制,将4号体复制一份到沿负法线方向
  42.                                 ! 568单位处(以现在位置为起点的相对距离)
  43. VGEN,2,5, , ,-568        ! 体复制,将5号体复制一份到沿负法线方向
  44.                                 ! 568单位处(以现在位置为起点的相对距离)
  45. VGEN,2,6, , ,-568        ! 体复制,将6号体复制一份到沿负法线方向
  46.                                 ! 568单位处(以现在位置为起点的相对距离)
  47. NUMMRG,ALL, , , ,LOW
  48. NUMCMP,ALL  
  49.   
  50. VGEN,2,4, , ,1704
  51. VGEN,2,5, , ,1704
  52. VGEN,2,6, , ,1704
  53. NUMMRG,ALL, , , ,LOW
  54. NUMCMP,ALL  
  55.   
  56. VGEN, ,ALL, , ,-284, , , , ,1    ! 体平移,将所有体沿负法线方向平移
  57.                                           ! 284个单位(以现在位置为起点的相对距离)
  58.   
  59. NUMMRG,ALL, , , ,LOW
  60. NUMCMP,ALL  
  61.   
  62. NSEL,S,LOC,X,199,369           ! 轨枕处的约束
  63. NSEL,R,LOC,Y,-79
  64. D,ALL,ALL
  65. ALLSEL,ALL
  66.   
  67. NSEL,S,LOC,X,767,937   
  68. NSEL,R,LOC,Y,-79
  69. D,ALL,ALL
  70. ALLSEL,ALL
  71.   
  72. NSEL,S,LOC,X,1335,1420
  73. NSEL,R,LOC,Y,-79
  74. D,ALL,ALL
  75. ALLSEL,ALL
  76.   
  77. NSEL,S,LOC,X,-369,-199
  78. NSEL,R,LOC,Y,-79
  79. D,ALL,ALL
  80. ALLSEL,ALL
  81.   
  82. NSEL,S,LOC,X,-937,-767   
  83. NSEL,R,LOC,Y,-79
  84. D,ALL,ALL
  85. ALLSEL,ALL
  86.   
  87. NSEL,S,LOC,X,-1420,-1335
  88. NSEL,R,LOC,Y,-79
  89. D,ALL,ALL
  90. ALLSEL,ALL
  91. SAVE,rail_3Dmesh_withoutLoad,db    ! 保存数据库为文件格式
  92. FINISH

  93. RESUME,rail_3Dmesh_withoutLoad,db   ! 重新开始分析,恢复rail_3Dmesh_withoutLoad.db   
  94. NSEL,S,LOC,X,0                                 ! 选择中跨跨中位置
  95. NSEL,R,LOC,Y,94,100                         ! 选择中跨跨中位置的轨头节点
  96. NSEL,R,LOC,Z,-25.330,0                      ! 选择中跨跨中位置的一侧轨头节点
  97. /PNUM,NODE,1                                  ! 显示节点编号   
  98. /VIEW,1,-1                                       ! 视图方向控制
  99. /ANG,1   
  100. /REPLOT                                          ! 图形重画
  101. NPLOT                                            !  节点重画
  102. ALLSEL,ALL                                     ! 选择所有
复制代码
 楼主| 发表于 2015-10-5 21:58 | 显示全部楼层
火车过桥全过程仿真

  1. /view,1,1,1,1
  2. /eshape,1
  3. cj=1.27
  4. /prep7
  5. mp,ex,1,2e11
  6. mp,prxy,1,0.3
  7. mp,dens,1,780
  8. et,1,beam188
  9. !上下弦杆
  10. sectype,1,beam,I
  11. secdata,0.46,0.46,0.46,0.02,0.02,0.012
  12. !端斜杆
  13. sectype,2,beam,I
  14. secdata,0.6,0.6,0.46,0.02,0.02,0.012
  15. !斜杆
  16. sectype,3,beam,I
  17. secdata,0.44,0.44,0.46,0.012,0.012,0.01
  18. !竖杆
  19. sectype,4,beam,I
  20. secdata,0.26,0.26,0.46,0.012,0.012,0.01
  21. !上下纵联
  22. sectype,5,beam,I
  23. secdata,0.12,0.12,0.24,0.012,0.012,0.01
  24. !纵梁
  25. sectype,6,beam,I
  26. secdata,0.24,0.24,1.29,0.016,0.016,0.01
  27. !横梁
  28. sectype,7,beam,I
  29. secdata,0.24,0.24,1.29,0.024,0.024,0.012
  30. n,
  31. n,,6

  32. n,,0,0,8
  33. n,,6,0,8
  34. n,,6,8,8
  35. n,,0,8,8

  36. n,,0,0,16
  37. n,,6,0,16
  38. n,,6,8,16
  39. n,,0,8,16

  40. n,,0,0,24
  41. n,,6,0,24
  42. n,,6,8,24
  43. n,,0,8,24

  44. n,,0,0,32
  45. n,,6,0,32
  46. n,,6,8,32
  47. n,,0,8,32

  48. n,,0,0,40
  49. n,,6,0,40
  50. n,,6,8,40
  51. n,,0,8,40

  52. n,,0,0,48
  53. n,,6,0,48
  54. n,,6,8,48
  55. n,,0,8,48

  56. n,,0,0,56
  57. n,,6,0,56
  58. n,,6,8,56
  59. n,,0,8,56

  60. n,,0,0,64
  61. n,,6,0,64

  62. n,500,0,10,0
  63. n,508,0,10,64
  64. fill

  65. n,600,2,10,0
  66. n,601,4,10,0
  67. n,602,6,10,0

  68. !上下弦杆
  69. secnum, 1
  70. e,1,3,500
  71. e,3,7,500
  72. e,7,11,500
  73. e,11,15,500
  74. e,15,19,500
  75. e,19,23,500
  76. e,23,27,500
  77. e,27,31,500
  78. e,2,4,602
  79. e,4,8,602
  80. e,8,12,602
  81. e,12,16,602
  82. e,16,20,602
  83. e,20,24,602
  84. e,24,28,602
  85. e,28,32,602

  86. e,5,9,602
  87. e,9,13,602
  88. e,13,17,602
  89. e,17,21,602
  90. e,21,25,602
  91. e,25,29,602
  92. e,6,10,500
  93. e,10,14,500
  94. e,14,18,500
  95. e,18,22,500
  96. e,22,26,500
  97. e,26,30,500


  98. !端斜杆
  99. secnum,2
  100. e,1,6
  101. e,2,5
  102. e,29,32
  103. e,30,31
  104. !斜杆
  105. secnum,3
  106. e,6,7
  107. e,7,14
  108. e,14,15
  109. e,15,22
  110. e,22,23
  111. e,23,30
  112. e,5,8
  113. e,8,13
  114. e,13,16
  115. e,16,21
  116. e,21,24
  117. e,24,29
  118. !竖杆
  119. secnum,4
  120. e,3,6
  121. e,4,5
  122. e,7,10
  123. e,8,9
  124. e,11,14
  125. e,12,13
  126. e,15,18
  127. e,16,17
  128. e,19,22
  129. e,20,21
  130. e,23,26
  131. e,24,25
  132. e,27,30
  133. e,28,29
  134. !上纵联
  135. secnum,5
  136. e,5,6,501
  137. e,5,10,502
  138. e,6,9,501

  139. e,9,10,502
  140. e,9,14,503
  141. e,10,13,502

  142. e,13,14,503
  143. e,13,18,504
  144. e,14,17,503

  145. e,17,18,504
  146. e,17,22,505
  147. e,18,21,504

  148. e,21,22,505
  149. e,21,26,506
  150. e,22,25,505

  151. e,25,26,506
  152. e,25,30,506
  153. e,26,29,506
  154. e,29,30,506

  155. !下纵联
  156. e,1,4,500
  157. e,2,3,501

  158. e,3,8,501
  159. e,4,7,502

  160. e,7,12,502
  161. e,8,11,503

  162. e,11,16,503
  163. e,12,15,504

  164. e,15,20,504
  165. e,16,19,505

  166. e,19,24,505
  167. e,20,23,506

  168. e,23,28,506
  169. e,24,27,507

  170. e,27,32,507
  171. e,28,31,508

  172. !纵梁
  173. secnum,6

  174. n,33,2,0,0
  175. n,161,2,0,64
  176. fill
  177. e,33,34,600
  178. *repeat,128,1,1

  179. n,162,4,0,0
  180. n,290,4,0,64
  181. fill
  182. e,162,163,601
  183. *repeat,128,1,1

  184. !横梁
  185. secnum,7
  186. e,1,33,500
  187. e,33,162,500
  188. e,162,2,500

  189. e,3,49,501
  190. e,49,178,501
  191. e,178,4,501

  192. e,7,65,502
  193. e,65,194,502
  194. e,194,8,502

  195. e,11,81,503
  196. e,81,210,503
  197. e,210,12,503

  198. e,15,97,504
  199. e,97,226,504
  200. e,226,16,504

  201. e,19,113,505
  202. e,113,242,505
  203. e,242,20,505

  204. e,23,129,506
  205. e,129,258,506
  206. e,258,24,506

  207. e,27,145,507
  208. e,145,274,507
  209. e,274,28,507

  210. e,31,161,508
  211. e,161,290,508
  212. e,290,32,508

  213. d,1,all
  214. d,2,all
  215. ddele,1,rotx
  216. ddele,2,rotx
  217. d,31,all
  218. d,32,all
  219. ddele,31,rotx
  220. ddele,32,rotx
  221. ddele,31,uz
  222. ddele,32,uz

  223. /solu
  224. antype,static
  225. i=0
  226. *do,i,0,128,1  
  227. fdele,all,all
  228. sfedele,all,all,pres
  229. nsel,all
  230. nsel,s,loc,x,2,4,2
  231. nsel,r,loc,y,0
  232. nsel,r,loc,z,i*0.5
  233. f,all,fy,-cj*110000
  234. nsel,all
  235. nsel,s,loc,x,2,4,2
  236. nsel,r,loc,y,0
  237. nsel,r,loc,z,(i-3)*0.5
  238. f,all,fy,-cj*110000
  239. nsel,all
  240. nsel,s,loc,x,2,4,2
  241. nsel,r,loc,y,0
  242. nsel,r,loc,z,(i-6)*0.5
  243. f,all,fy,-cj*110000
  244. nsel,all
  245. nsel,s,loc,x,2,4,2
  246. nsel,r,loc,y,0
  247. nsel,r,loc,z,(i-9)*0.5
  248. f,all,fy,-cj*110000
  249. nsel,all
  250. nsel,s,loc,x,2,4,2
  251. nsel,r,loc,y,0
  252. nsel,r,loc,z,(i-12)*0.5
  253. f,all,fy,-cj*110000
  254. nsel,all
  255. !
  256. *if,i,le,15,then

  257. *elseif,i,le,75
  258.     nsel,s,loc,x,2,4,2
  259.     nsel,r,loc,y,0
  260.     nsel,r,loc,z,0,(i-15)*0.5,1
  261.     esln
  262.     esel,u,sec,,7
  263.     sfbeam,all,1,pres,cj*46000
  264. *elseif,i,gt,75
  265.     nsel,s,loc,x,2,4,2
  266.     nsel,r,loc,y,0
  267.     nsel,r,loc,z,(i-75)*0.5,(i-15)*0.5,1
  268.     esln
  269.     esel,u,sec,,7
  270.     sfbeam,all,1,pres,cj*46000
  271.     nsel,all

  272.     nsel,s,loc,x,2,4,2
  273.     nsel,r,loc,y,0
  274.     nsel,r,loc,z,0,(i-75)*0.5,1
  275.     esln
  276.     esel,u,sec,,7
  277.     sfbeam,all,1,pres,cj*40000
  278. *endif
  279. allsel
  280. outres,all,all
  281. solve
  282. *enddo
  283. finish
  284. /post26
  285. numvar,50
  286. timerange,1,130
  287. !下弦
  288. esol,2,1,1,smisc,1,fx1
  289. esol,3,2,3,smisc,1,fx2
  290. esol,4,3,7,smisc,1,fx3
  291. esol,5,4,11,smisc,1,fx4
  292. esol,6,5,15,smisc,1,fx6
  293. esol,7,6,19,smisc,1,fx7
  294. esol,8,7,23,smisc,1,fx8
  295. esol,9,8,27,smisc,1,fx9
  296. !上弦
  297. esol,10,23,6,smisc,1,fx23
  298. esol,11,24,10,smisc,1,fx24
  299. esol,12,25,14,smisc,1,fx25
  300. esol,13,26,18,smisc,1,fx26
  301. esol,14,27,22,smisc,1,fx27
  302. esol,15,28,26,smisc,1,fx28
  303. !端斜杆
  304. esol,16,29,6,smisc,1,fx29
  305. esol,17,32,30,smisc,1,fx32
  306. !斜杆
  307. esol,18,33,6,smisc,1,fx33
  308. esol,19,34,7,smisc,1,fx34
  309. esol,20,35,14,smisc,1,fx35
  310. esol,21,36,15,smisc,1,fx36
  311. esol,22,37,22,smisc,1,fx37
  312. esol,23,38,30,smisc,1,fx38
  313. !竖杆
  314. esol,24,45,6,smisc,1,fx45
  315. esol,25,47,7,smisc,1,fx47
  316. esol,26,49,14,smisc,1,fx49
  317. esol,27,51,15,smisc,1,fx51
  318. esol,28,53,22,smisc,1,fx53
  319. esol,29,55,26,smisc,1,fx55
  320. esol,30,57,30,smisc,1,fx57


  321. prval,2,3,4,5,6,7,8,9
  322. prval,10,11,12,13,14,15
  323. prval,16,17
  324. prval,18,19,20,21,22,23
  325. prval,24,25,26,27,28,29,30






  326. /view,1,1,1,1
  327. /eshape,1
  328. cj=1.27
  329. /prep7
  330. mp,ex,1,2e11
  331. mp,prxy,1,0.3
  332. mp,dens,1,780
  333. et,1,beam188
  334. !上下弦杆
  335. sectype,1,beam,I
  336. secdata,0.46,0.46,0.46,0.02,0.02,0.012
  337. !端斜杆
  338. sectype,2,beam,I
  339. secdata,0.6,0.6,0.46,0.02,0.02,0.012
  340. !斜杆
  341. sectype,3,beam,I
  342. secdata,0.44,0.44,0.46,0.012,0.012,0.01
  343. !竖杆
  344. sectype,4,beam,I
  345. secdata,0.26,0.26,0.46,0.012,0.012,0.01
  346. !上下纵联
  347. sectype,5,beam,I
  348. secdata,0.12,0.12,0.24,0.012,0.012,0.01
  349. !纵梁
  350. sectype,6,beam,I
  351. secdata,0.24,0.24,1.29,0.016,0.016,0.01
  352. !横梁
  353. sectype,7,beam,I
  354. secdata,0.24,0.24,1.29,0.024,0.024,0.012
  355. n,
  356. n,,6

  357. n,,0,0,8
  358. n,,6,0,8
  359. n,,6,8,8
  360. n,,0,8,8

  361. n,,0,0,16
  362. n,,6,0,16
  363. n,,6,8,16
  364. n,,0,8,16

  365. n,,0,0,24
  366. n,,6,0,24
  367. n,,6,8,24
  368. n,,0,8,24

  369. n,,0,0,32
  370. n,,6,0,32
  371. n,,6,8,32
  372. n,,0,8,32

  373. n,,0,0,40
  374. n,,6,0,40
  375. n,,6,8,40
  376. n,,0,8,40

  377. n,,0,0,48
  378. n,,6,0,48
  379. n,,6,8,48
  380. n,,0,8,48

  381. n,,0,0,56
  382. n,,6,0,56
  383. n,,6,8,56
  384. n,,0,8,56

  385. n,,0,0,64
  386. n,,6,0,64

  387. n,500,0,10,0
  388. n,508,0,10,64
  389. fill

  390. n,600,2,10,0
  391. n,601,4,10,0
  392. n,602,6,10,0

  393. !上下弦杆
  394. secnum, 1
  395. e,1,3,500
  396. e,3,7,500
  397. e,7,11,500
  398. e,11,15,500
  399. e,15,19,500
  400. e,19,23,500
  401. e,23,27,500
  402. e,27,31,500
  403. e,2,4,602
  404. e,4,8,602
  405. e,8,12,602
  406. e,12,16,602
  407. e,16,20,602
  408. e,20,24,602
  409. e,24,28,602
  410. e,28,32,602

  411. e,5,9,602
  412. e,9,13,602
  413. e,13,17,602
  414. e,17,21,602
  415. e,21,25,602
  416. e,25,29,602
  417. e,6,10,500
  418. e,10,14,500
  419. e,14,18,500
  420. e,18,22,500
  421. e,22,26,500
  422. e,26,30,500


  423. !端斜杆
  424. secnum,2
  425. e,1,6
  426. e,2,5
  427. e,29,32
  428. e,30,31
  429. !斜杆
  430. secnum,3
  431. e,6,7
  432. e,7,14
  433. e,14,15
  434. e,15,22
  435. e,22,23
  436. e,23,30
  437. e,5,8
  438. e,8,13
  439. e,13,16
  440. e,16,21
  441. e,21,24
  442. e,24,29
  443. !竖杆
  444. secnum,4
  445. e,3,6
  446. e,4,5
  447. e,7,10
  448. e,8,9
  449. e,11,14
  450. e,12,13
  451. e,15,18
  452. e,16,17
  453. e,19,22
  454. e,20,21
  455. e,23,26
  456. e,24,25
  457. e,27,30
  458. e,28,29
  459. !上纵联
  460. secnum,5
  461. e,5,6,501
  462. e,5,10,502
  463. e,6,9,501

  464. e,9,10,502
  465. e,9,14,503
  466. e,10,13,502

  467. e,13,14,503
  468. e,13,18,504
  469. e,14,17,503

  470. e,17,18,504
  471. e,17,22,505
  472. e,18,21,504

  473. e,21,22,505
  474. e,21,26,506
  475. e,22,25,505

  476. e,25,26,506
  477. e,25,30,506
  478. e,26,29,506
  479. e,29,30,506

  480. !下纵联
  481. e,1,4,500
  482. e,2,3,501

  483. e,3,8,501
  484. e,4,7,502

  485. e,7,12,502
  486. e,8,11,503

  487. e,11,16,503
  488. e,12,15,504

  489. e,15,20,504
  490. e,16,19,505

  491. e,19,24,505
  492. e,20,23,506

  493. e,23,28,506
  494. e,24,27,507

  495. e,27,32,507
  496. e,28,31,508

  497. !纵梁
  498. secnum,6

  499. n,33,2,0,0
  500. n,161,2,0,64
  501. fill
  502. e,33,34,600
  503. *repeat,128,1,1

  504. n,162,4,0,0
  505. n,290,4,0,64
  506. fill
  507. e,162,163,601
  508. *repeat,128,1,1

  509. !横梁
  510. secnum,7
  511. e,1,33,500
  512. e,33,162,500
  513. e,162,2,500

  514. e,3,49,501
  515. e,49,178,501
  516. e,178,4,501

  517. e,7,65,502
  518. e,65,194,502
  519. e,194,8,502

  520. e,11,81,503
  521. e,81,210,503
  522. e,210,12,503

  523. e,15,97,504
  524. e,97,226,504
  525. e,226,16,504

  526. e,19,113,505
  527. e,113,242,505
  528. e,242,20,505

  529. e,23,129,506
  530. e,129,258,506
  531. e,258,24,506

  532. e,27,145,507
  533. e,145,274,507
  534. e,274,28,507

  535. e,31,161,508
  536. e,161,290,508
  537. e,290,32,508

  538. d,1,all
  539. d,2,all
  540. ddele,1,rotx
  541. ddele,2,rotx
  542. d,31,all
  543. d,32,all
  544. ddele,31,rotx
  545. ddele,32,rotx
  546. ddele,31,uz
  547. ddele,32,uz

  548. /solu
  549. antype,static
  550. i=0
  551. *do,i,0,128,1  
  552. fdele,all,all
  553. sfedele,all,all,pres
  554. nsel,all
  555. nsel,s,loc,x,2,4,2
  556. nsel,r,loc,y,0
  557. nsel,r,loc,z,i*0.5
  558. f,all,fy,-cj*110000
  559. nsel,all
  560. nsel,s,loc,x,2,4,2
  561. nsel,r,loc,y,0
  562. nsel,r,loc,z,(i-3)*0.5
  563. f,all,fy,-cj*110000
  564. nsel,all
  565. nsel,s,loc,x,2,4,2
  566. nsel,r,loc,y,0
  567. nsel,r,loc,z,(i-6)*0.5
  568. f,all,fy,-cj*110000
  569. nsel,all
  570. nsel,s,loc,x,2,4,2
  571. nsel,r,loc,y,0
  572. nsel,r,loc,z,(i-9)*0.5
  573. f,all,fy,-cj*110000
  574. nsel,all
  575. nsel,s,loc,x,2,4,2
  576. nsel,r,loc,y,0
  577. nsel,r,loc,z,(i-12)*0.5
  578. f,all,fy,-cj*110000
  579. nsel,all
  580. !
  581. *if,i,le,15,then

  582. *elseif,i,le,75
  583.     nsel,s,loc,x,2,4,2
  584.     nsel,r,loc,y,0
  585.     nsel,r,loc,z,0,(i-15)*0.5,1
  586.     esln
  587.     esel,u,sec,,7
  588.     sfbeam,all,1,pres,cj*46000
  589. *elseif,i,gt,75
  590.     nsel,s,loc,x,2,4,2
  591.     nsel,r,loc,y,0
  592.     nsel,r,loc,z,(i-75)*0.5,(i-15)*0.5,1
  593.     esln
  594.     esel,u,sec,,7
  595.     sfbeam,all,1,pres,cj*46000
  596.     nsel,all

  597.     nsel,s,loc,x,2,4,2
  598.     nsel,r,loc,y,0
  599.     nsel,r,loc,z,0,(i-75)*0.5,1
  600.     esln
  601.     esel,u,sec,,7
  602.     sfbeam,all,1,pres,cj*40000
  603. *endif
  604. allsel
  605. outres,all,all
  606. solve
  607. *enddo
  608. finish
  609. /post26
  610. numvar,50
  611. timerange,1,130
  612. !下弦
  613. esol,2,1,1,smisc,1,fx1
  614. esol,3,2,3,smisc,1,fx2
  615. esol,4,3,7,smisc,1,fx3
  616. esol,5,4,11,smisc,1,fx4
  617. esol,6,5,15,smisc,1,fx6
  618. esol,7,6,19,smisc,1,fx7
  619. esol,8,7,23,smisc,1,fx8
  620. esol,9,8,27,smisc,1,fx9
  621. !上弦
  622. esol,10,23,6,smisc,1,fx23
  623. esol,11,24,10,smisc,1,fx24
  624. esol,12,25,14,smisc,1,fx25
  625. esol,13,26,18,smisc,1,fx26
  626. esol,14,27,22,smisc,1,fx27
  627. esol,15,28,26,smisc,1,fx28
  628. !端斜杆
  629. esol,16,29,6,smisc,1,fx29
  630. esol,17,32,30,smisc,1,fx32
  631. !斜杆
  632. esol,18,33,6,smisc,1,fx33
  633. esol,19,34,7,smisc,1,fx34
  634. esol,20,35,14,smisc,1,fx35
  635. esol,21,36,15,smisc,1,fx36
  636. esol,22,37,22,smisc,1,fx37
  637. esol,23,38,30,smisc,1,fx38
  638. !竖杆
  639. esol,24,45,6,smisc,1,fx45
  640. esol,25,47,7,smisc,1,fx47
  641. esol,26,49,14,smisc,1,fx49
  642. esol,27,51,15,smisc,1,fx51
  643. esol,28,53,22,smisc,1,fx53
  644. esol,29,55,26,smisc,1,fx55
  645. esol,30,57,30,smisc,1,fx57


  646. prval,2,3,4,5,6,7,8,9
  647. prval,10,11,12,13,14,15
  648. prval,16,17
  649. prval,18,19,20,21,22,23
  650. prval,24,25,26,27,28,29,30
复制代码
 楼主| 发表于 2015-10-5 21:59 | 显示全部楼层
斜齿轮命令流
  1. *set,cn,0.5        !法面顶隙系数
  2. *set,pi,3.1415929
  3. *set,b,20          !齿宽
  4. *set,b1,10         !螺旋角
  5. *set,mn,2          !法向模数
  6. *set,z,24          !齿数
  7. *set,r,z*mn/cos(b1/180*pi)/2  !分度圆半径
  8. *set,rb,22.859     !基圆半径
  9. *set,ra,r+cn*mn    !齿顶圆半径     
  10. /prep7
  11. csys,0
  12. *do,i,1,11
  13. x=rb*(cos(4.5*(i-1)*pi/180)+4.5*(i-1)*pi/180*sin(4.5*(i-1)*pi/180))
  14. y=rb*(sin(4.5*(i-1)*pi/180)-4.5*(i-1)*pi/180*cos(4.5*(i-1)*pi/180))
  15. k,i,x,y
  16. *enddo
  17. *do,i,1,9,2
  18. spline,i,i+1,i+2
  19. *enddo
  20. k,12,rb-cn
  21. l,1,12
  22. lsel,all
  23. lcomb,all
  24. numcmp,all
  25. wprota,-3.304           !齿根对应的圆周角的一半
  26. csys,4
  27. lsymm,y,1
  28. wpcsys,1,0
  29. csys,1
  30. l,2,4
  31. l,1,3
  32. lfillt,1,3,0.5
  33. lfillt,2,3,0.5
  34. lsel,all
  35. al,all
  36. k,9,r
  37. k,10,r,b1,b
  38. l,9,10
  39. vdrag,1,,,,,,7
  40. vgen,z,1,,,,360/z
  41. vsel,all
  42. vadd,all
  43. numcmp,all
  44. cylind,ra,,,b
  45. vsbv,2,1
  46. numcmp,all
  47. cylind,10,,,20             !轴孔
  48. vsbv,1,2
  49. numcmp,all
  50. block,-3,3,,12.8,,20        !键槽
  51. vsbv,1,2
复制代码
 楼主| 发表于 2015-10-5 21:59 | 显示全部楼层
叶片冲撞分析命令流
  1. fini
  2. /clear
  3.   
  4. ! blade.inp is a supplement to Chapter 11 (ANSYS/LS-DYNA Seminar)
  5.   
  6. /title, Implicit-to-Explicit Sequential Solution
  7.   
  8. ! Stress Initialization to Prescribed Geometry followed by Full Transient
  9.   
  10. ! This is a simplified attempt to analyze the scenario when a  
  11. !  jet engine fan blade snaps off and tears the engine apart
  12.   
  13. /uis,abort,off  ! do not display annoying status boxes...
  14.   
  15. ! ===========================================================================
  16.   
  17. /filnam,implicit            ! implicit (ANSYS) portion of analysis
  18.   
  19. /prep7   
  20. /view,,1,2,3  
  21. /ang,1  
  22.   
  23. ! Note:  Only SHELL181 elements are used in this example, but other element
  24. !        types (e.g., SOLID185) can also be used.  However, there is a set of  
  25. !        companion element types that exist, which make the transition from/to
  26. !        implicit to/from explicit "automatic" (etchg used instead of emodif):
  27. !
  28. !        LINK8      ===>  LINK160
  29. !        BEAM4      ===>  BEAM161
  30. !        SHELL181  <===>  SHELL163  (181 accepts 163 stresses & thicknesses)
  31. !        SOLID185  <===>  SOLID164  (185 accepts 164 stresses at 5.6)
  32. !        COMBIN14   ===>  COMBI165
  33. !        MASS21     ===>  MASS166
  34. !        LINK10     ===>  LINK167
  35. !
  36. !        The LS-DYNA link and beam elements require a third node, which is  
  37. !        not always used in ANSYS, so these elements must be checked by the  
  38. !        user.  Also, SHELL181 accepts thickness and stress information from
  39. !        LS-DYNA.  Prior to 5.6, it accepted the thicknesses and element  
  40. !        force and moment information from SHELL163, which was then used to  
  41. !        calculate the stresses that were already determined in LS-DYNA.
  42. !        If more than 5 integration points are used through the thickness  
  43. !        (trapezoidal rule), then the old method of force and moment data  
  44. !        is used.  SOLID185 should have KEYOPT(2)=1 (i.e., uniform reduced  
  45. !        integration with hourglass control) to be consistent with SOLID164.   
  46.   
  47. ! It's best to think in terms of "parts" when the model is being created,  
  48. ! because ANSYS/LS-DYNA requires part definitions for many of its commands
  49. ! (EDLOAD, EDCGEN, EDREAD, etc).  By issuing the EDPART,Create command,
  50. ! ANSYS/LS-DYNA automatically creates parts that are based on unique sets
  51. ! of MAT, REAL, and TYPE numbers used by elements (listed sequentially via
  52. ! the ELIST command).  These part lists can be updated after the model has
  53. ! been changed (EDPART,Update) or listed (EDPART,List) at any time before  
  54. ! the SOLVE or EDWRITE,ANSYS/TAURUS/both commands are issued, at which  
  55. ! point, the part list is set.
  56.   
  57. et,1,SHELL181               ! implicit shell elements for engine hub
  58. et,2,SHELL181               ! implicit shell elements for blade platform
  59. et,3,SHELL181               ! implicit shell elements for engine blades
  60. et,4,SHELL181               ! implicit shell elements for engine duct  
  61. /eshape,1                   ! show element thicknesses (to check model)
  62.   
  63. r,1,0.50                    ! thickness of hub (flywheel shape)
  64. r,2,0.50                    ! fan blade platform thickness
  65. r,3,0.25                    ! fan blade average thickness
  66. r,4,0.75                    ! engine duct (housing) thickness
  67.   
  68. ! Note:  Only small strains using linear material properties are allowed
  69. !        in the implicit analysis, since only the resulting displacements  
  70. !        will be used in the stress initialization portion (first part)  
  71. !        of the explicit analysis.  In other words, no path dependent  
  72. !        features are allowed in the implicit run.   
  73.   
  74. mp,  ex,1,30.0e6            ! modulus of hub (psi)
  75. mp,dens,1,7.33e-4           ! mass density of hub (lbf-sec^2/in^4)
  76. mp,nuxy,1,0.30              ! Poisson's ratio (unitless)
  77.   
  78. mp,  ex,2,30.0e6            ! modulus of blade platform (psi)
  79. mp,dens,2,7.33e-4           ! mass density of blade platform (lbf-sec^2/in^4)
  80. mp,nuxy,2,0.30              ! Poisson's ratio (unitless)
  81.   
  82. mp,  ex,3,30.0e6            ! modulus of blade (psi)
  83. mp,dens,3,7.33e-4           ! mass density of blade (lbf-sec^2/in^4)
  84. mp,nuxy,3,0.30              ! Poisson's ratio (unitless)
  85.   
  86. mp,  ex,4,30.0e6            ! modulus of engine duct (psi)
  87. mp,dens,4,7.33e-4           ! density of duct not used (lbf-sec^2/in^4)
  88. mp,nuxy,4,0.30              ! Poisson's ratio (unitless)
  89.   
  90. k,1,0,0,0                   ! create simplified jet engine geometry  
  91. k,2,0,0,1  
  92. l,1,2                       ! line #1 used to generate geometry...  
  93. lgen,2,1,,,5,0,0            ! inner radius of hub (line #2)  
  94. ldiv,2                      ! divide line #2 in half into lines #2 and #3  
  95. lgen,2,2,3,,5,0,0           ! outer radius of hub (lines #4 and #5)
  96. l,5,7                       ! line #6 represents web of hub
  97. local,11,1,0,0,0.5,0,0,90.0 ! local cs to twist blade
  98. lgen,2, 4, 5,,0, -5.0,1.0   ! root of blade (break point at radius = 11")  
  99. lgen,2, 7, 8,,0,-12.5,1.5   ! create lines to "skin" blade...  
  100. lgen,2, 9,10,,0,-12.5,1.5
  101. lgen,2,11,12,,0,-12.5,1.5
  102. lgen,2,13,14,,0,-12.5,1.5
  103. lgen,2,15,16,,0,-12.5,1.5
  104. lgen,2,17,18,,0,-12.5,1.5
  105. lsel,s,line,,7,20,1
  106. lesize,all,,,2              ! specify esize = 0.25" for blades ("axially")
  107. lsel,all
  108.   
  109. csys,0                      ! return to global coordinate system
  110. kmodif,1,0,0,-2             ! move end-points of origin line for duct
  111. kmodif,2,0,0, 3             ! duct axial length will be 5" for model...
  112. lgen,2, 1,,,21,0,0          ! line #21 at 21" radius (engine duct or housing)
  113. a,6,7,10,9                  ! platform at base of blade (area #1)
  114. a,7,8,11,10                 ! area #2
  115. askin,7,9,11,13,15,17,19    ! twisting shape of blade "skinned" (area #3)
  116. askin,8,10,12,14,16,18,20   ! area #4
  117.   
  118. csys,1                      ! use global cylindrical cs to copy blades, etc.  
  119. lesize,2,,,1                ! specify esize = 0.5" at inner hub radius
  120. lesize,3,,,1                ! specify esize = 0.5" at inner hub radius
  121. arotat,2,3,,,,,1,2,360,4    ! ring at hub inner radius (areas #5 - #12)
  122. lesize,6,,,5                ! specify esize = 1" along hub web (radially)  
  123. arotat, 6,,,,,,1,2,360,4    ! hub disk (web) section (areas #13 - #16)
  124. lesize,4,,,2                ! specify esize = 0.25" at hub outer radius
  125. lesize,5,,,2                ! specify esize = 0.25" at hub outer radius
  126. arotat,4,5,,,,,1,2,360,4    ! ring at hub outer radius (areas #17 - #24)
  127. lesize,21,,,5               ! specify esize = 1" for engine duct (axially)
  128. arotat,21,,,,,,1,2,360,4    ! engine housing (duct) ring (areas #25 - #28)
  129. nummrg,kp
  130.   
  131. type,1                      ! engine hub element type  
  132. real,1                      ! constant hub thickness used throughout
  133. mat,1                       ! engine hub material
  134. esize,,9                    ! coarse mesh used (hub will become rigid body)
  135. amesh,5,12                  ! mesh hub inner ring
  136. amesh,13,16                 ! mesh hub web (disk)
  137. amesh,17,24                 ! mesh hub outer ring
  138.   
  139. type,2                      ! blade platform element type  
  140. real,2                      ! platform thicker than adjoining blade
  141. mat,2                       ! blade platform material
  142. esize,,4                    ! 4 divisions along length of blade platform
  143. amesh,1,2                   ! mesh platform at base of blade (copy below)
  144.   
  145. type,3                      ! fan blade element type   
  146. real,3                      ! constant fan blade thickness used (I know ...)
  147. mat,3                       ! fan blade material (only linear properties here)
  148. esize,,36                   ! 36 divisions (esize = 0.25") along blade length   
  149. amesh,3,4                   ! mesh fan blade (copy below)
  150.   
  151. agen,36,1,4,1, 0,10.0,0     ! generate all of the engine blades and platforms
  152.   
  153. type,4                      ! engine duct element type (not used here...)
  154. real,4                      ! constant thickness cylindrical shape used
  155. mat,4                       ! engine duct material  
  156. esize,,9                    ! use 36 element divisions circumferentially  
  157. amesh,25,28                 ! mesh the engine housing (duct or shroud)
  158. nummrg,kp
  159.   
  160. csys,0                      ! return to global coordinate system
  161. nummrg,node                 ! clean up any "loose ends" in the model...
  162. nummrg,kp
  163.   
  164. ! Note:  No nodes or elements may be introduced for the first time in the  
  165. !        explicit portion of an implicit-to-explicit sequential analysis.   
  166. !        All entities must be pre-defined in the implicit portion of the run,
  167. !        even if they are not used there.  All of these elements in question  
  168. !        must have all of the degrees of freedom (DOFs) of all of their   
  169. !        nodes set to zero in the implicit run.  Then, in the explicit run,  
  170. !        the elements are converted to the companion type and the DOFs from
  171. !        the implicit run are deleted (and re-specified, as necessary).  In
  172. !        this example, the pressure loading on the engine duct (100 psi?) is
  173. !        a second order effect and, is therefore, not modeled in the implicit
  174. !        part of the sequential solution.  Another example would be the
  175. !        bird in a bird-strike analysis, which would probably best be modeled
  176. !        with SOLID185 elements and then completely restrained here.  In the
  177. !        explicit run, the SOLID185 elements would be converted to SOLID164
  178. !        elements and the DOFs would be deleted.  The corresponding keyopts,  
  179. !        real constants, material properties, boundary conditions, and  
  180. !        loading would still need to be defined in the explicit analysis...
  181.   
  182. esel,s,type,,4              ! engine housing elements     
  183. nsle                        ! engine housing nodes
  184. d,all,all,0.0               ! fix all DOFs of unused entities
  185. nsel,all
  186. esel,all
  187.   
  188. fini
  189. /solu
  190. antype,static
  191.   
  192. ! outpr,all,all
  193. outres,all,all
  194.   
  195. omega,,,420.0               ! engine spin load (420.0 rad/sec = 4,010.7 rpm)  
  196. esel,s,type,,1              ! engine hub elements (rigid body in explicit run)
  197. nsle                        ! engine hub nodes (not concerned with hub)
  198. d,all,all,0.0               ! fix engine hub to allow loading of fan blades  
  199. nsel,all
  200. esel,all
  201.   
  202. save
  203. eplot
  204. solve                       ! default solver used, but others OK, too
  205. fini
  206.   
  207. /post1
  208. set,last
  209. /eshape,0
  210. /graphics,full
  211. /dscale,,1   
  212. shell,bottom                ! results for bottom layer of shell element
  213. plnsol,s,eqv                ! blade maximum von Mises stress at root
  214. shell,top                   ! results for top layer of shell element
  215. plnsol,s,eqv                ! blade maximum von Mises stress at root
  216. fini
  217.   
  218. ! ===========================================================================
  219.   
  220. /filnam,explicit            ! explicit (LS-DYNA) portion of analysis
  221.   
  222. /prep7
  223. etchg,ite                   ! convert SHELL181 elements to SHELL163 elements
  224.                             !  default settings automatically specified...
  225.   
  226. ! Note: The EMODIF command may be used instead of the ETCHG command, but
  227. !       the latter is more automatic for "companion" elements (refer to the
  228. !       ANSYS/LS-DYNA User's Guide - Release 5.6 for details).  In both cases,
  229. !       the shell element thicknesses, etc. still need to be re-specified...
  230.   
  231. r,1,,3,0.50                 ! hub (3 int. pts. through 0.5" thickness)
  232. r,2,,3,0.50                 ! blade platform (same as above)
  233. r,3,,5,0.25                 ! blades (5 int. pts. through 0.25" thickness)
  234. r,4,,5,0.75                 ! duct (5 int. pts. through 0.75" thickness)   
  235.   
  236. edint,5                     ! saves data for all 5 layers (blades and duct)
  237.   
  238. esel,s,type,,1              ! hub elements
  239. nsle                        ! hub nodes
  240. ddele,all,all               ! remove imposed displacements from implicit run
  241. edmp,rigid,1,7,4            ! convert hub to rigid body (only rotz = free)
  242. nsel,all
  243. esel,all
  244.   
  245. ! Simulate one blade snapping off by unselecting a row of elements along the
  246. ! root.  Alternatively, areas #1 and #2 could have been cleared (ACLEAR,1,2).
  247.   
  248. asel,s,area,,1,2            ! blade platform areas of blade #1  
  249. esla                        ! elements of first platform
  250. nsle                        ! corresponding nodes
  251. nsel,r,loc,x,10.7,11.1      ! reselect nodes of outer row of elements
  252. esln,s,1                    ! select elements with all nodes active
  253. cm,esnap,elem               ! row of elements to be unselected before SOLVE
  254.   
  255. asel,s,area,,3,4            ! blade #1 (projectile)
  256. esla                        ! elements of first blade
  257. cm,eproj,elem               ! element component for EDHIST command
  258. nsle                        ! nodes of first blade
  259. cm,nproj,node               ! node component for EDHIST command
  260. asel,all
  261. nsel,all
  262. esel,all
  263.   
  264. ! Use nonlinear (plastic) material properties for the fan blades:
  265.   
  266. !  Note:  First convert engineering stress versus engineering strain data
  267. !         into true stress versus true (hencky) strain data.  Then subtract
  268. !         off the elastic true strain from the total true strain to find
  269. !         the plastic true strain, which is used with the total true stress
  270. !         in LS-DYNA *MAT_PIECEWISE_LINEAR_PLASTICITY material model #24.
  271.   
  272. !--------------------------------------------------------------------------
  273. !  Stress-Strain Data used with Piecewise Linear Plasticity (Power Law 8):
  274. !--------------------------------------------------------------------------
  275. !           Total     Total      Total      Total      Elastic    Plastic
  276. ! Stress/   Eng.      Eng.       True       True       True       True
  277. ! Strain    Stress    Strain     Stress     Strain     Strain     Strain
  278. ! Point     (psi)     (in/in)    (psi)      (in/in)    (in/in)    (in/in)
  279. !--------------------------------------------------------------------------
  280. !   1           0     0.0000          0     0.0000     0.0000     0.0000
  281. !   2      60,000     0.0020     60,120     0.0020     0.0020     0.0000
  282. !   3      77,500     0.0325     80,020     0.0320     0.0027     0.0293
  283. !   4      83,300     0.0835     90,260     0.0802     0.0030     0.0772
  284. !   5      98,000     0.1735    115,000     0.1600     0.0038     0.1562
  285. !   6      98,300     0.2710    124,940     0.2398     0.0042     0.2356
  286. !   7      76,400     1.2255    170,030     0.8000     0.0057     0.7943
  287. !--------------------------------------------------------------------------
  288.   
  289. ! Note: The first point on the stress/strain curve is NOT entered.
  290. !       Start with the second point (where ordinate = yield stress).
  291. !       Also, please follow the limits imposed by the *SET command.
  292.   
  293. *dim,strn,,6  ! define array for effective plastic true strain data
  294. *dim,strs,,6  ! define array for effective total true stress data
  295.   
  296. strn(1)= 0.0, 0.0293, 0.0772, 0.1562, 0.2356, 0.7943  ! strain (in/in)
  297. strs(1)= 60120., 80020., 90260., 115000., 124940., 170030.  ! stress (psi)
  298.   
  299. edcurve,add,1,strn,strs  ! load curve #1: abscissa=strain & ordinate=stress
  300. tb,plaw,3,,,8            ! specify power law #8 for material (MAT) #3
  301. tbdata,1,60120.0         ! yield stress, psi  
  302. tbdata,3,0.30            ! set material failure at 30% true plastic strain
  303. tbdata,6,1               ! use load curve #1 for stress/strain data
  304.   
  305. ! Note: Strain rate effects can be included by specifying the necessary
  306. !       strain rate parameters and the load curve defining the strain rate
  307. !       scaling effect on the yield stress.  Please refer to Chapter 7  
  308. !       (Material Models) of the ANSYS/LS-DYNA User's Guide for a complete  
  309. !       description of this material model.
  310.   
  311. ! Use nonlinear (plastic) material properties for the engine duct, too:
  312.   
  313. tb,plaw,4,,,8            ! specify power law #8 for material #4 (duct)
  314. tbdata,1,60120.0         ! yield stress, psi  
  315. tbdata,3,0.50            ! set material failure at 50% true plastic strain
  316. tbdat,6,1                ! use load curve #1 for stress/strain data
  317. esel,s,type,,4           ! engine duct elements
  318. nsle                     ! engine duct nodes
  319. ddele,all,all            ! remove imposed displacements from implicit run
  320. nsel,all
  321. esel,all
  322.   
  323. ! Allow GUI to recognize batch-defined material input
  324.   
  325. mpmod,1,7
  326. mpmod,2,1
  327. mpmod,3,28
  328. mpmod,4,28
  329.   
  330. edcgen,ag                   ! automatic general contact
  331.   
  332. fini
  333. /solu
  334.   
  335. ! Using the REXPORT command, write the displacements (and rotations  
  336. ! and temperatures) determined in the ANSYS implicit analysis to the  
  337. ! ASCII "drelax" file.  This command also sets the "m=drelax" option  
  338. ! in the lsdyna script, prompting LS-DYNA to read the drelax file in.   
  339.   
  340. rexport,dyna,,,,,implicit,rst  
  341.    
  342. ! By issuing the EDDRELAX command, a stress initialization to a  
  343. ! prescribed geometry analysis is requested.  In a sequential  
  344. ! implicit-to-explicit run, a "dynamic relaxation"  analysis is  
  345. ! performed in the pre-transient portion of the explicit analysis  
  346. ! to preload the structure by imposing the deformed geometry over  
  347. ! 101 time steps (with damping).  The time during these 101 time  
  348. ! steps can be thought of as "pseudo" time, since the time interval  
  349. ! for the transient event begins at time equal to zero.  Please  
  350. ! note that, although the temperatures are being written to the  
  351. ! "drelax" file, they are not currently being used.  They will be  
  352. ! supported in a later release.  The remaining fields of the  
  353. ! EDDRELAX command are ignored in an implicit-to-explicit analysis.
  354.   
  355. eddrelax,ansys              ! request stress initialization analysis...
  356.   
  357. ! Impart initial spin velocity to nodes after stress initialization done
  358.   
  359. esel,s,type,,1,3,1          ! spinning engine components
  360. nsle                        ! nodes of hub, blade platforms, and blades
  361. cm,nrots,node               ! nodes initially spinning at 420.0 rad/sec
  362.   
  363. edivelo,nrots, 0,0,0, 420, 0,0,0, 90,90,0  ! Phase field set automatically  
  364.   
  365. nsel,all
  366. esel,all
  367.   
  368. ! Continue spinning load on hub (converted to a rigid body now).
  369.   
  370. *dim,etime,,2               ! dimension explicit time array
  371. *dim,spin,,2                ! dimension spin loading array
  372. etime(1)=0.00               ! run time array out past termination time...  
  373. etime(2)=0.02               ! time array duration = 0.02 seconds
  374. spin(1)=0.00                ! extending load curves facilitates restarts...
  375. spin(2)=8.40                ! 8.4 radians in 0.02 seconds = 420 rad/sec
  376.   
  377. ! Note:  The EDPART command is used to create, update, and list part IDs  
  378. !        needed by the EDLOAD, EDCGEN, etc. commands.  Please see Chapter  
  379. !        3 of the ANSYS/LS-DYNA 5.6 User's Guide for more information  
  380. !        concerning this topic.
  381.   
  382. edpart,create               ! create and list parts (part #1 = rigid body  
  383.                             ! hub, #2=platforms, #3=blades, and #4=duct)
  384.   
  385. ! Below, "rbrz" is used to apply a rigid body rotation about the z-axis,
  386. ! since there is no straight-forward method to apply an omega to the rigid  
  387. ! body at 5.6 (without editing the explicit.k input file).  The load curve  
  388. ! specified is the equivalent of a constant omega of 420 radians per second.  
  389.   
  390. edload,add,rbrz,,1,etime,spin,0  ! Phase = 0 for sequential run (on part #1)
  391.   
  392. ! The phase parameter on the EDLOAD command was added at ANSYS/LS-DYNA 5.4.
  393. ! The default value of zero is used for explicit transient loading in both  
  394. ! a sequential implicit/explicit analysis and in an explicit-only analysis.   
  395. ! In these cases, the load curve is applicable to the LS-DYNA transient  
  396. ! portion of the run.  The other two phase options are not valid in a  
  397. ! sequential analysis.  They are used for explicit-only cases of stress  
  398. ! initialization by dynamic relaxation (phase=1) OR stress initialization
  399. ! by dynamic relaxation followed by a transient analysis (phase=2).
  400.   
  401. nsel,s,loc,y,20.1,21.1      ! nodes on duct at wing attachment point
  402. d,all,  ux,0.0,,,,  uy,  uz ! fix duct in translation to wing
  403. d,all,rotx,0.0,,,,roty,rotz ! fix duct in rotation to wing
  404. nsel,all
  405. esel,all
  406.   
  407. cmsel,u,esnap        ! unselect row of elements to "snap off" blade
  408.   
  409. time,0.010           ! termination time (can continue with EDSTART)
  410. edrst,50             ! write data to results file 52 times (50+2)
  411. edhtime,50           ! write data to history file 52 times (50+2)
  412. edhist,eproj         ! elements belonging to snapped off blade
  413. edhist,nproj         ! nodes belonging to snapped off blade
  414. edenergy,1,1,1,1     ! output energies (hourglass, sliding interface ...)   
  415. edout,glstat         ! output LS-DYNA global energy file (ASCII)
  416. !!!edopt,add,,both      ! write results for both ANSYS and LS-TAURUS/LS-POST  
  417. edopt,add,,ansys     ! write results for just ANSYS  
  418.   
  419. !!!edwrite,both,,k      ! create LS-DYNA input file (explicit.k)  
  420. edwrite,ansys,,k      ! create LS-DYNA input file (explicit.k)  
  421.   
  422. save
  423.   
  424. /eof
  425.   
  426. ! Note:  If the LS-DYNA solver is run directly (from outside of ANSYS),
  427. !        issue:  /ansys56/bin/lsdyna56  i=explicit.k  m=drelax
  428.   
  429. solve   ! overwrites the existing "explicit.k" input file and solves ...
  430.   
  431. fini
  432. /post1   
  433. /dscale,,1                  ! set displacement magnification to one
  434. /view,,0.1,-0.75,0.65
  435. set,first
  436. layer,5                     ! top layer of shell element
  437. plnsol,s,eqv                ! von Mises equivalent stress plot
  438. layer,1                     ! bottom layer of shell element
  439. plnsol,s,eqv                ! von Mises equivalent stress plot
  440.   
  441. andata,0.5,,2,1,33,2,0,1    ! animate every other frame up to substep 33 ...
  442.   
  443. fini
  444. /exit
  445.   
  446. !2345678901234567890123456789012345678901234567890123456789012345678901234567890
  447.   
  448. ! Note:  Stress data is available for each layer.  For the fan blades and  
  449. !        engine duct, five integration points are used (real constant NIP)  
  450. !        and the results are saved for each layer (EDIMT,5).  However,  
  451. !        strain data is only available for the top and bottom layers.   
  452. !        Although the LAYER,1 command gives both stress and strain data  
  453. !        for the bottom layer, the LAYER,2 command gives stress data for  
  454. !        the second layer, but gives strain data for the top layer (#5).   
  455. !        To get stress data for the top layer, issue LAYER,5.  Also, the  
  456. !        explicit results are for the integration point locations, which  
  457. !        are at the midplane of a given layer.  To approximate surface  
  458. !        stresses and strains, a sufficient number of integration points  
  459. !        (layers) must be used through the thickness...
复制代码
 楼主| 发表于 2015-10-5 22:00 | 显示全部楼层
一个转动的分析模型


  1. 命令:/prep7  
  2. et,1,164  
  3. et,2,164  
  4. mp,ex,1,10e6  
  5. mp,dens,1,2.7e-4  
  6. mp,nuxy,1,.334  
  7.   
  8. mp,ex,2,30e6  
  9. mp,dens,2,2.7e-4  
  10. mp,nuxy,2,.292  
  11.   
  12. block,-10,10,-10,10,10,15  
  13. cylind,5,10,0,5
  14.   
  15. cylind,0,5,-10,10
  16. esize,1  
  17. mshape,1,3d
  18. mshkey,1
  19. type,1
  20. mat,1
  21. vmesh,1 type,2
  22. mat,2
  23. vmesh,2  
  24.   
  25. edcgen,assc,, ,0.5
  26. esel,s,mat,,2
  27. nsle,s
  28. cm,box,node
  29. alls
  30. da,3,ux
  31. da,3,uy
  32. da,3,uz
  33.   
  34. da,4,ux
  35. da,4,uy
  36. da,4,uz
  37.   
  38. finish  
  39. /sol  
  40. *dim,t,array,2  
  41. *dim,r,array,2  
  42. t(1)=0,1 0
  43. d(1)=10,1 0
  44. edload,add,OMGZ,,box,t,r  
  45. time,1 0
  46. edrst,10  
  47. edhtime,10  
  48. edout,glstat  
  49. edout,matsum  
  50. edout,rcforc  
  51. edout,rbdout  
  52.   
  53. solve  
  54. finish  
  55. /post1  
  56. set,last  
  57. plnsol,s,eqv  
  58. finish
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