飛機壽命 的英文怎麼說

中文拼音 [fēijīshòumìng]
飛機壽命 英文
aircraft life span
  • 飛 : Ⅰ動詞1 （鳥、蟲等在空中活動） fly; flit 2 （利用動力機械在空中行動） fly 3 （在空中飄浮遊動） fly...
  • 機 : machineengine
  • 飛機 : airplane; plane; aeroplane; kite; bird; aircraft
  1. The active vibration control aimed at aircraft empennage has huge practical values in the aspects of adding the fatigue life of vertical tail, increasing the capability and availability of the aircraft, reducing the through - life - support costs and so on

    飛行器垂直尾翼的振動主動控制對于提高尾翼的疲勞壽命、飛行器的機動性以及減小飛行器的維護成本具有較大的實際意義。
  2. Based on the aircraft structure fatigue theory, the article discussed the theoretical basis of methods that are usually used for aircraft structure fatigue crack - forming life estimation, i. e. the stress severity factor approach ( normal stress approach ), the local stress & strain approach, detail fatigue rating approach ( dfr ). also the processes of life estimation of these approaches are studied in the article

    文章在簡要介紹飛機結構疲勞強度理論的基礎上，對目前飛機結構勞疲勞裂紋形成壽命估算常用的應力嚴重系數法（名義應力法） ，局部應力應變法，細節疲勞額定值dfr法的理論依據作了較詳細的論述，同時對這些估算方法進行壽命估算的過程與步驟也作了詳盡的闡述。
  3. In order to prolong the service life of aging aircraft and ensure aircraft safety, it need replace and repair damaged components

    為了延長老齡化飛機使用壽命確保飛機的飛行安全，必須對含缺陷構件進行更換或者修理。
  4. We use the stressed fraction that is the most representational and sensitive to corroding to making experiment in combined type equivalent environment spectrum. we can calculate the velocity of corroding, protection period and basal body corroding expansion lifespan, first repair time and the interval of repair period

    本文以模擬試驗結果和使用中腐蝕損傷數據統計處理為主要依據，並同時滿足安全性和經濟性兩方面的要求，在確定機體使用壽命時，以疲勞定壽結果為主、日歷定壽為輔，綜合給出飛機機體使用壽命。
  5. Research on fatigue life using aircraft structure passed higher load test

    利用做過高載試驗的飛機結構進行疲勞壽命研究
  6. The life span of most commercial aeroplanes is said to be around 30 years ; and so, just as there was a 1970s explosion in aircraft production, now there ' s a big jump in the number of planes beyond use

    大部分商用客機的壽命據悉約卅年左右，因此，一如1970年代，飛機暴量生產，今天也有一大堆飛機已經無用武之地。
  7. At the base of getting a great deal of structure corrode damage data and through statistic fitting method, discovered the rule between outboard wing corroded depth and lifespan at different airport. then we can calculate the inoxidizing coating lifespan, basal body corroding expansion lifespan and first repair time

    在獲得使用中結構腐蝕損傷的大量數據的基礎上，通過統計擬合的方法，取得不同機場飛機外翼長桁腐蝕深度與日歷壽命的統計規律的基礎上，進而可以求得防護層的有效壽命、基體腐蝕擴展壽命。
  8. Fatigue life analysis of the leading - edge flap on x model aircraft

    某型飛機前緣機動襟翼使用壽命分析
  9. Under these approaches, the 1if e of the lower flange connection region between a rib 6 and rib 8 of the front bar of some aircraft are estimated and the fatigue life of simulator of the connection region is experimentally tested and the estimation results and the experimental results are compared

    通過用這些壽命估算方法對某型飛機前墻6 8肋段下緣條連接區進行壽命估算與該段連接區模擬試驗件進行疲勞試驗結果分別進行了分析比較。
  10. If this achievement is applied into the planes on active duty, it will reduce the maintenance cost 17 million ~ during the full lifetime

    其成果在現役飛機上推廣后，在全壽命期內可降低維修費用1700萬元。
  11. During the course of the life estimation, if the experimental parameters can be carefully chosen, aircraft structure life estimation has a positive effect on the structure fatigue des ign

    在壽命估算過程中，只要比較精確地選取各方法所需的經驗參數，飛機結構所估算的最終結果對飛機結構抗疲勞設計和型號定壽有很大的指導意義。
  12. These engineering projects are : civil jet aircraft ; long life and high reliability communication satellite ; 1000 mw nuclear power station ; quasi - high speed railway ; magnetic suspention railway ; xingjiang - shanghai gas pipeline building engineering ; large scale hydropower station

    這些工程項日是噴氣式民航飛機、長壽命高可靠性通信衛星、 100萬千瓦核電站、提速鐵路、磁懸浮鐵路、西氣東輸工程和巨型水電站。
  13. In this paper, the design technical management and synthesis of engineering specialty in each stage of airplane life span is discussed emphasisly, in the light of the development of a certain medium - range aifto - ground missile bomber and a certain air4o - ship missile bomber. the principle and method of engineering system engineering is adopted to the management of airplane design technique. by drawing on the experience of advanced management from foreign airplane ' s abstract development, the standardized method of the design technical management and synthesis of engineering specialty in each stage of airplane life span is presented in this paper

    本文結合某型中程空地導彈機和某型空艦導彈機不同階段的研製，對飛機壽命周期各階段設計技術管理和工程專業的綜合進行了重點研究，把工程系統工程的原理和方法應用到飛機設計技術管理中，借鑒了國外飛機研製的先進管理方法，提出了飛機壽命周期各階段設計技術管理和工程專業綜合的規范化方法。
  14. Several key problems and their technical settlements were expounded emphatically, such as the accelerated corrosion test technique for aircraft structure under laboratory conditions, the evaluation technique for corrosion damage of anticorrosive coats, the distribution characteristics and their variation regularities of the corrosion damage and fatigue life, the corrosion equivalent relationship between the accelerated environment and the service environment, and the methods for theoretical analysis of the calendar life

    重點對腐蝕環境下飛機結構加速腐蝕試驗技術、防腐塗層腐蝕損傷評定技術、腐蝕損傷和疲勞壽命的分佈特性及其變化規律、腐蝕當量關系和日歷壽命理論分析方法等幾個關鍵問題及其技術途徑進行了闡述和探討。
  15. From the work done above, we can get the following conclusion " all these life estimation approaches can be smoothly used to predict the life of aircraft, but they have their own limits

    通過上述工作，得到如下結論：各壽命估算方法都能較順利估算飛機結構的裂紋形成壽命，但各壽命估算方法又都有自身的缺點。
  16. As the damage tolerance technique has being widely and deeply adopted in the design and life prediction of aircraft structures, the development of high performance and more suitable software used in damage tolerance design and assessment is more urgent. while at the same time the existing domestic software is not well suitable for requirements in engineering

    隨著損傷容限技術在飛機結構設計和壽命評估中的廣泛採用，研製高性能且實用的損傷容限分析與評定軟體系統越來越迫切，而國內現有的損傷容限分析軟體經實踐證明其性能和適用性不能很好滿足工程需要，特別是結構剩餘強度和裂紋擴展分析程序。
  17. The long - term life and low cycle fatigue life of low pressure turbine blade for an aeroengine under real loading spectrum is analyzed by using this method

    用該方法對某型發動機低壓渦輪工作葉片在實際飛行載荷譜作用下的持久壽命和低循環疲勞壽命進行了分析。
  18. Considering kept the effect of all the evaluation factors, multiplication - addition type s fuzzy operator is adopted in the analysis for the life of entirety oil - vessel used in plane, and ahp method is applied to get the evaluation indexes weights

    在對飛機整體油箱的壽命分析中，考慮到保留所有評判因素的影響，採用了乘、加型模糊運算元，並用層次分析（ ahp ）法來確定評價指標權重。
  19. In first part of the thesis, by a review of the research on aircraft sonic fatigue, the formulas for calculating natural frequencies of the typical aircraft skin - panel structure with four edges simply - supported or four edges fixed - supported were drawn, the response of displacement and stress was analysed under the condition of random white noise loading with the steady - state or unsteady - state. the procedure how to use data of s - n curve under constant loading for predicating the fatigue life of skin - panel subjected to random loading was shown

    通過對聲疲勞問題研究的回顧，根據典型飛機蒙皮壁板模型，整理了四邊固支，四邊簡支兩種邊界條件下多階模態固有頻率，非平穩及平穩隨機白噪聲載荷下的位移和應力響應，以及如何從等幅s ? n曲線求得隨機載荷應力下的疲勞壽命。
  20. They had only a lifetime of about 10 flying hours and production never reached the output necessary

    其發動機壽命只有大約10個飛行小時，而且從未達到過。
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