strain cycle 中文意思是什麼

strain cycle 解釋
應變循環
  • strain : vt 1 用力拉，拉緊，抽緊，扯緊。2 使緊張；盡量使用（肌肉等）。3 強迫，強制；濫用，盡量利用。4 拉傷...
  • cycle : n 1 循環，周期，一轉。2 周時，周年，年紀。3 （詩、故事等的）始末。4 自行車，三輪車，摩托車。5 【...
  1. While cyclic deformation experiment under constant strain control is performed in 400, the material shows the continuous hardening until cyclic invalidation. ( 3 ) back stress attained by kwl " s method is used to analyse the bauschinger effect during an incremental step cyclic test and cyclic deformation test under constant strain control, it is shown that back stress increases with increasing plastic strain and the numbers of cycle, and the back stress is uniform, regardless of tension or compression conditions. ( 4 ) as far as recrystallized zircaloy - 4 plate is concerned, the back stress in transverse direction is higher than that in rolling direction due to the higher schmid factor in rolling direction

    對于再結晶狀態的zr一4合金板材試樣來說， t方向（橫向）試樣的背應力要高於r方向（軋制方向）的背應力，原因在於r方向的schmid因子高於t方向的schmid因子; 400下， zr一4合金的背應力要明顯低於室溫下的背應力;含氫200pg / g的zr一4合金的背應力大小與無滲氫的zr一4合金背應力相比，無明顯區別;固溶處理后， zr一4合金的背應力大小發生了變化，在較高塑性應變下，背應力均高於固溶處理前的背應力。
  2. The experimental results is shown as followings : ( 1 ) the cyclic flow stress - strain curves in an incremental step test could be expressed as the power law relation : ( 2 ) when the strain amplitude is lower during cyclic deformation tests under constant strain control, softening firstly appears, then gradually hardens with the increasing numbers of cycle ; when the strain amplitude is higher, hardening firstly appears, then gradually softens

    試驗結果表明： （ 1 ）循環流變應力與應變的相互關系曲線均符合冪律關系式： （ 2 ）在室溫下進行恆應變幅循環變形過程中，當所控制的應變幅較小時，該材料首先出現循環軟化，之後隨循環周次的增加直至循環失效前該材料出現了硬化現象。當應變幅較大時，該材料開始出現硬化，然後隨循環周次的增加才出現軟化。
  3. In this paper, the high - temperature low - cycle fatigue life and fatigue crack propagation life tests are carried on the cylindrical axial symmetry specimens having precrack or non - precrack with different types of notches of 16mnr steel in common use in the petrochemical industry contacting coke drum equipment, the stress / strain and the range of stress / strain of dangerous points are received through stress analysis of the specimens using finite element program under multi - axial stress state. at last, the equations of evaluating the high - temperature low - cycle fatigue life and the fatigue crack propagation life are found through using the least - square regression method

    本文採用無預裂紋和帶預裂紋環狀缺口圓柱形試樣，進行了石化焦炭塔設備常用材料16mnr多維應力狀態下不同缺口形式的高溫低周疲勞總壽命試驗及裂紋擴展壽命試驗，並利用有限元程序對試樣缺口周圍及裂紋尖端附近進行了軸對稱多維應力狀態下的應力、應變場分析，來評價材料不同條件下的高溫低周疲勞總壽命和裂紋擴展壽命，最後利用最小二乘回歸方法，得到了該材料高溫低周疲勞總壽命和裂紋擴展壽命評價方程。
  4. A new test method to achieve the dynamical rock failure with medium strain rate by low - cycle - index fatigue loading

    用低周疲勞加載實現中等應變速率下巖石動態破壞的新方法
  5. Specimens ’ cracking load under dead - load, fatigue failure characteristic, fatigue life, deflection of span - centre, fatigue flexural rigidity, maximal crack width, development of cracks and strain of concrete and steel bars have been investigated. the influence of fatigue cycle characteristic, ratio of reinforcement, kinds of aggregate and concrete compressive strength on the specimens ’ fatigue behavior has been also investigated

    對試件的靜載下開裂荷載、疲勞破壞特徵、疲勞壽命、疲勞荷載作用下的跨中撓度、截面疲勞抗彎剛度、裂縫開展情況及最大裂縫寬度、鋼筋及混凝土在循環荷載作用下應變等內容進行了研究，分析了疲勞循環特徵值、縱筋配筋率、骨料種類、混凝土抗壓強度等因素對試件疲勞性能的影響。
  6. However, the die attach layer delaminated after 500 cycles and pcb cracked in the underfilled samples after long time cycling. c - sam is employed to investigate the delamination in the underfilled samples. highly concentrated stress - strain induced by the cte mismatch between the bga component and the pcb board, coarsened grain and two kinds of intermetallic compounds ( nisn / nisns ) which formed during reflow and thermal cycle and their impact on the reliability of solder joints are discussed in this paper

    充膠樣品粗化尤為嚴重； ? ni - sn金屬間化合物包括兩層：其中，靠近ni焊盤的那層比較平整，同時， eds結果分析表明其化學式近似為nisn ，而靠近焊料的那層呈板條狀，化學式近似為nisn _ 3 ，文獻表明其為亞穩相； ?充膠使得樣品最大應力范圍降了接近一個數量級並降低了dnp的作用，同時，器件失效模式變為晶元粘接層分層； ? c - sam結果表明本論文採用的充膠樣品，晶元粘接層分層起始於500周左右，而經過2700周循環的樣品，分層幾乎擴展到整個界面。
  7. The close genetic relationship of goose parvoviruse and aav allows the examination of the molecular biological properties of the nonstructural proteins of gpv. after the gpv infected the cell the viral life cycle was regulated by the nonstructural proteins encoded by the virus. according to the published of gpv b strain genome nucleotide sequences in genbank and a pair of specific primers were disigned with oligo4. 1

    本研究根據genbank發表的gpvb株全基因序列，藉助oligo4 . 1軟體設計一對引物，採用pcr技術擴增gpvh1株非結構蛋白ns2基因，並與pmd18 - t載體連接后測序，結果表明：鵝細小病毒h1株ns2基因核苷酸全長1356bp ，編碼451個氨基酸殘基，與gpvb株的ns2基因相比，核苷酸數目相同，有17個堿基、 6個氨基酸的差異；同源性分析表明：二者核苷酸序列同源性為98 . 75 ，推導氨基酸序列同源性為98 . 67 。
  8. Fatigue strength coefficient decreases linearly during the cyclic course ; fatigue strength exponent increases ; fatigue ductility coefficient first goes up till the maximum value at 50 % total life, and then goes down ; fatigue ductility exponent decreases during the first half cycle till its minimum value at 50 % total life and then increases in the rest cycle course ; cycle strength coefficient and cycle strain hardening exponent both decrease during the total cycle course

    結果表明： 6個基本疲勞特性參數在循環過程中都呈顯出規律性變化。疲勞強度系數呈線性減小趨勢；疲勞強度指數呈線性增大特徵；疲勞延性系數是一個先增后降的過程；而疲勞延性指數隨循環進行由初始減小到逐漸增大；循環強度系數和循環應變硬化指數在整個循環過程中都趨于減小。
  9. Through research into the low - cycle fatigue behavior of gh4145 / sq, we found out that the control of strain at any level is not a stable course but has three obvious stages. the first stage is a rapid cyclic hardening course for any strain control

    對gh4145 / sq合金在總應變幅控制下的對稱拉壓低周疲勞研究表明：在循環形變過程中合金主要表現為初始疲勞硬化、隨后疲勞軟化及最終失穩斷裂三個階段，疲勞硬化軟化行為與作用應變幅相關。
  10. It is very important to study the correlation of cyclical strain on the side of hole with fatigue life cycle for understanding the material damage and micro - crack initiation, and for preventing macro - crack initiation and propagation

    研究孔邊循環應變與疲勞循環次數的相關性，對于研究材料損傷及微裂紋的產生，預防宏觀裂紋的產生及擴展具有十分重要的意義。
  11. In this thesis, the strain - hardening model of contact surface layer, the numerical theories and computational methods for shakedown analyses of contact body are systematically studied and applied to the aero - gear. the mentality is that the effects of the surface hardening and contact fatigue on contact surface layer under cycle contact loading are investigated by using shakedown analysis methods considering in a quantitative way the details of stress - inelastic strain responses, residual stress and residual strain computations

    在國家「航空基金」 、 「總裝預研基金」等課題的資助下，本文以接觸體安定分析與接觸表面層疲勞裂紋萌生壽命預測一般演算法研究為手段，深入、系統研究了接觸體安定分析的數值理論和計算方法，全面研究了影響航空齒輪表面強化層失效的原因並提出了齒輪表面強化層裂紋萌生壽命的預測方法。
  12. The study on high - temperature low - cycle fatigue life and fatigue crack propagation life under multi - axial stress state shows that the fatigue life and fatigue crack propagation life can be characterized by the equivalent plastic strain range p, the equivalent creep strain range c and the equivalent strain range, and do n ' t exit notch dependency, non - notch - dependency equations being given in the paper

    ） _ c和當量應變范圍（ ? ）進行多維應力狀態高溫低周疲勞總壽命及裂紋擴展壽命評價是可行的，且不存在缺口依存性。並給出無缺口依存性的疲勞總壽命評價方程。
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