機構載荷 的英文怎麼說

中文拼音 [jīgòuzǎihé]
機構載荷 英文
force object
  • 機 : machineengine
  • 構 : Ⅰ動詞1 （構造; 組合） construct; form; compose 2 （結成） fabricate; make up 3 （建造; 架屋） bui...
  • 載 : 載Ⅰ名詞（年） year : 一年半載 six to twelve months; six months to a year; 三年五載 three to five ...
  • 荷 : 荷名詞（蓮） lotus
  • 機構 : 1 [機械工程] （機械的內部構造或一個單元） mechanism 2 （機關; 團體） organ; organization; institu...
  • 載荷 : load; loading載荷變化 load fluctuation; variation in load; 載荷裝置 load device
  1. With the help of the electronic computers, engineers employ it to figure out nearly all kinds of engineering problems ranging from astronavigation, construction, waterpower projects, ship - building and mechanical engineering etc. owing to the strong power of finite element method, one kind of software pack which based on the method is exploited and named algor feas to resolve problems on structure analysis for trusses and shells. this paper also employ algor feas software pack to analyze and compute the cableway towers, giving the accurate result on stress and displacement both in location and whole. finally, we also bring out some advice on structure improving

    在此分析過程中：首先將物理模型簡化為力學模型，主要是將塔架結構按空間桿單元簡化為空間桁架結構，目的是將力學模型變換為數學模型；這一過程主要是利用autocad2000建立塔架的計算模型；再者，利用algorfeas軟體包讀入autocad建立的塔架計算模型生成初始數據卡利用計算機進行編程進行風載計算，再將計算結論整合入algorfeas產生的初始數據卡中，生成計算數據卡；接著，利用algorfeas軟體包計算塔架在不同載荷情況下的應力圖，位移圖，並且求出在不同載荷條件下的最大位移和最大應力等；然後，對塔架的穩定性進行分析；最後；根據計算結果提出改進建議。
  2. In the dissertation ' s chapter 3 to chapter 5, the mechanical and physical performances of the engineering plastics are analyzed, the failure mode and the designing computing methods of engineering plastics member suffering the static load, dynamic load, impact load, pulse load, are studied. by the practice application and ball firing experiment of the engineering plastics key piece in the weapons, the precious experiences, for engineering plastics application and confirmation of the material performances guideline in the weapons, are obtained

    論文的第三章至第五章，分析了工程塑料物理機械性能，研究了受靜載荷、動載荷、沖擊載荷及脈沖載荷下工程塑料構件的失效模式和設計計算方法，通過工程塑料在槍械關鍵受力結構件上的實際應用和實彈射擊試驗，取得了寶貴的經驗，為高性能工程塑料在槍械上的應用和材料性能指標的確定奠定了基礎。
  3. In summary the major research work in this thesis can be drawn as follows : 1. the techncal data and research information from woridwide aviation history about bird striking to airframe have been collected and reviewed more carefully the evolutions of bird striking load models and fem numerical compatation methods to bird strike also have been sununarized. this informational research makes great help to position further thesis work scientifically 2

    本文研究工作可歸納總結為以下三個方面： 1 、較全面整理綜述了鳥體撞擊飛機結構在國內外航空史上的技術資料以及鳥撞問題理論與工程研究的歷史沿革，總結了撞擊載荷研究模型、有限元數值計算方法的發展歷程等，明確了本文研究工作的科學定位。
  4. If this load centroid is behind the elastic axis of the wing structure, then a nose-down twist of the main wing surface results.

    如果該載荷重心在機翼結構彈性軸之後，則引起主機翼表面前端向下的扭轉。
  5. First, the theory of fretting wear and studies on fretting fatigue were introduced and the parametric method was used in the process of creating the model of dovetail joints in ug software. the elastic contact problem is analyzed in finite element method ( fem ) and is used to the parameters " distribution and contact stress of the joint are obtained on the base of ansys code. with the effect factor of load frequency, the prediction method of fretting fatigue life of dovetail joint under low and high / low cycle complex load is proposed

    本文介紹了微動損傷的機理和微動疲勞壽命的研究方法；利用ug軟體對燕尾榫聯接結構創建了參數化實體模型；基於ansys軟體平臺求解彈性接觸問題，獲得了榫聯接結構接觸應力及接觸狀態量的分佈；在已有微動疲勞壽命預測模型的基礎上，引入載荷頻率影響因子，對低周、高低周復合載荷作用下的燕尾榫聯接結構進行了微動疲勞壽命的預測，與試驗結果對比表明採用本文提出的方法預測榫聯接結構的微動疲勞壽命是有效的。
  6. The working lives of this sort of mechanism are all awfully short, and most of them are used only once, such as the actuating mechanisms of missiles and fish torpedoes

    然而，有一種機械傳動機構，它們不承擔交變載荷或只承擔短期交變載荷，它們的工作壽命很短，有的使用一次就不再使用。如導彈、魚雷等武器的傳動機構。
  7. This paper is focussed on the deployable boom system ( dbs ) of geospace double star exploration project ( dsp ) of chinese accademy of sciences. the main content of the paper is as following : 1

    針對中國科學院「地球空間雙星探測計劃」的有效載荷探頭伸展機構，本文進行了機構動力學和結構動力學的理論分析和研究，主要內容如下： 1
  8. This article gives the subsistent ability and the analysis result of intensity after repair in the open field airplane composite material structure by research the intensity, rigid and repair problem under a axis compress loads on a typical three stiffened composite laminate which has a penetrability crack ( a scatter damage ) by a shrapnel

    本文通過飛機典型復合材料三加筋層壓板結構在被彈片劃開一穿透性切口（離散源損傷）后，在軸向壓縮載荷作用下所產生的強度、剛度以及修理問題展開了技術研究及探討，給出軍機復合材料加筋板在彈擊後生存力以及外場修理后強度恢復分析結果。
  9. Utilizing the characteristics of quick response, easy for automatization and easy to realize frequent commutation of the hydraulic system, this mechanism can be employed in composing the compound movement in horizontal and vertical direction, which could realize accurate simulation of the motion law for motorcycles and automobiles under the effect of random load in high frequency

    利用液壓系統反應快、便於自動化、易於實現頻繁換向的特點，該機構可用來合成水平、垂直方向的復合運動，實現對摩托車、汽車等在高頻隨機載荷作用下運動規律的精確模擬。
  10. The main research is below : ( 1 ) the influence to intensity and rigid with corner angle ( 60, 75 and 90 degree ) of crack and the board axes ( 2 ) do a fem stress / strain and crack growth simulation analysis when the corner angle of crack and the board axes is 60 degree ( 3 ) do a intensity resume analysis for the structure which is repaired with a titanium patch in a mechanical way when the corner angle of crack and the board axes is 60 degree through simulation analysis for three failure criterion, we have : ( 1 ) in 60, damage extend quickly with damage analysis in hashin criterion ; it is slower for analysis in maximum stress or hashin - rotem criterion. ( 2 ) in special term ( physical condition incision, shape or maximum load ) the compression strength of the stiffened plate will decline 45 % ~ 50 % under compression loads

    通過採用三個不同損傷判據的數值模擬模擬，得到如下結論： （ 1 ）在60時，用hashin判據進行的損傷分析，損傷擴展較快；最大應力及hashin - rotem判據進行的損傷分析，損傷擴展基本相當，且較慢； （ 2 ）在所給加筋板的物理條件、切口大小及形狀、最大載荷等一定的條件下，該加筋板在壓縮載荷作用下，其壓縮強度下降了45 50 ； （ 3 ）在本文提及到的機械連接修理方法以及載荷條件下，修理后的結構強度恢復能夠滿足戰時要求。
  11. The aircraft load calculation implies determination of the loads acting on the aircraft structure for flight maneuvers, flight in turbulence, landing and ground handling conditions

    飛機的載荷計算就是確定飛機在機動飛行、突風飛行、著陸和地面操作過程中作用在飛機結構上的載荷。
  12. Pitch control system consist of three channels which is formed by three drive units. base on need of bench, drive system scheme is designed. single channel three - loop position servo system which is formed by linear motor is simulated. then kinetic behavior of rotor and system ’ s force coupling relation is analyzed. a compensation method for dynamic load which is caused by rotor rotation is presented base on structure - invarient theory

    根據實驗臺的技術要求，設計了整個驅動系統方案。對由直線電機構成的單通道三環位置伺服系統進行了設計和模擬。分析了旋翼運動的動力學特性、系統力耦合關系，並根據結構不變性原理對由旋翼運動產生的動態載荷提出了補償方法。
  13. It supports the aircraft during parking and endures the loads during ground maneuvers. most of the vertical and horizontal kinetic energy are absorbed and dissipated by landing gear. it plays an extreme important role in preventing the airframe from vibration and excessive impact forces, improving passenger comfortable characteristics and increasing aircraft flight safety

    飛機起落架作為飛機結構的一個重要部件，承受著飛機與地面接觸時產生的靜、動載荷，吸收和消耗飛機在著陸撞擊、跑道滑行等地面運動時所產生的能量，在減緩飛機發生振動，降低飛機地面載荷，提高乘員舒適性，保障飛機飛行安全等方面發揮著極其重要的作用。
  14. Rubber components often appear interface failure due to the actions of mechanical loads and the influences of enviorment. hence, in this paper the interface failure mechanism has been studied by means of finite element method and fracture machinics. the numerical results of testpieces deformation with crack are in close agreement with experimental values

    橡膠鋼雙材料試件由於機械載荷和環境的影響經常在粘接界面發生破壞而導致結構失效，藉助有限元和斷裂力學對界面破壞機理進行研究，得到的存在初始裂紋的試件變形與實驗結果吻合較好。
  15. Based on fem analysis software ansys, a cylindrical latticed dome of an aerodrome is analyzed as an example. the progress of load - displacement for the whole structure - - cylindrical latticed dome & columns is record

    本文利用結構分析軟體ansys ，以某機場航站樓單層柱面網殼結構為例，追蹤了柱面網殼+支承柱這一整體結構的荷載-位移全過程。
  16. New type of screw mechanism with new function of load sensitive variable speed

    隨載荷變化而無級調速的新型螺旋機構
  17. Taking into account of the structure distortion, the theory and method of load calculation is researched from the perspective of engineering and airworthiness in this paper. the presented theory and method of load calculation is suitable for all kinds of civil aircraft. the load conditions and the initial parameters appropriated to the load calculation are determined according to the requirement of airworthiness

    本文從工程應用和適航性角度出發，對民用飛機結構載荷計算的理論與方法做了詳細的研究，研究了考慮結構變形的載荷計算方法，按照適航要求確定了飛機各部件載荷計算的設計情況和原始參數。
  18. Transportation loads - data collection of dynamic mechanical loads - part 1 : principles and survey on structure of the standards

    運輸載荷.動態機械載荷的數據收集.第1部分:標準結構
  19. Heat structural coupling analysis under mehanical and temperature load is analyzed by using the powerful software ansys

    利用大型通用有限元分析軟體ansys研究了在機械載荷與溫度載荷作用下的熱結構耦合問題。
  20. Firstly, itis explained that the application research of smart layer. to laod detecting and simulative damage for the model of wing - box, fbg fiber smart layer and pzt smart layer are designed, and manufactured. so, those are surface - mounted respectively on the stiffened skin of aluminum alloy and carbon fiber reinforced. data acquisition system based on different signal processing technique are designed

    針對機翼盒段試件結構載荷識別和模擬損傷監測的功能要求，結合智能夾層的設計製作工藝，設計製作了基於fbg傳感器的光纖和壓電兩種智能夾層，並分別安裝在機翼盒段試件上的鋁合金和碳纖維制蒙皮上。
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