rocket motor 中文意思是什麼

rocket motor 解釋
火箭發動機。

  • rocket : n 火箭；火箭彈，火箭發動機；火箭式投射器；〈英俚〉斥責。 a carrier [freight] rocket 載運火箭。 an...
  • motor : n 1 原動者；原動力。2 發動機；馬達；電動機；【火箭】助推器；汽車。3 【解剖學】運動肌；運動神經。a...
  1. Bipropellant liquid rocket motor

    二元推進劑液體火箭發動機
  2. Four nozzles, canted outboard, split the exhaust of the solid rocket motor into four equal tails.

    四個向外傾斜的噴管把固體火箭發動機的排氣流分成四個相等的尾巴。
  3. Design method for aft - end igniter of small - scale solid rocket motor

    小型固體火箭發動機尾部點火器設計方法
  4. Design optimization for solid rocket motor based on graph morphing

    基於圖形變形法的固體火箭發動機優化設計
  5. Web - based integrated design platform for solid rocket motor

    的固體火箭發動機集成設計平臺
  6. Calculation of nozzle efficiency for solid rocket motor

    固體火箭發動機燃燒室噴管一體化網格生成
  7. Uncertainty optimization design of solid rocket motor grain

    固體火箭發動機裝藥不確定性優化設計
  8. Analysis of nozzleless solid propellant rocket motor performance

    無噴管固體火箭發動機內彈道計算
  9. This paper described a cold gas simulation of solid rocket motor with submerged nozzle. a two - dimension model with rectangular channel was designed, which can simulate different flow conditions at three periods after ignition

    本文從冷流模擬的角度出發，設計了通道為矩形的含潛入噴管發動機冷流模型，可以模擬發動機工作過程中三個不同時刻的流動狀態。
  10. Hence, it is very significant to analyze the mechanism and extend law of interface debond of solid rocket motor

    因此，研究固體火箭發動機界面脫粘的機理和擴展規律，是固體火箭發動機結構完整性分析的重要課題。
  11. Interface debond between propellant and liner is a key form of failure of the structure integrity in the analysis of solid rocket motor

    在固體火箭發動機結構完整性分析中，襯層/推進劑藥柱粘接界面的脫粘是完整性被破壞的關鍵形式之一。
  12. Because the propellant grain is viscoelastic material, the liner and adiabatic layer are also viscoelastic one, the interface debond problem is actually interface crack about elastic - viscoelastic or bi - viscoelastic materials. research about this problem relates to the knowledge of viscoelastic mechanics and interface fracture and combustion. numerical analysis method about interface debond on solid rocket motor is researched in this paper

    由於固體火箭發動機的推進劑藥柱是一種粘彈性材料，襯層和絕熱層也具有粘彈性性質，因此其界面脫粘問題實際上是彈性-粘彈性或雙粘彈性各向同性材料界面裂紋問題，對該問題的研究涉及到粘彈性力學、界面斷裂力學和燃燒學等相關學科。
  13. During its storage, transportation, maintenance and service, the solid rocket motor ( srm ) may encounter many incidents such as being dropped onto the ground while being hoisted up, crashing when vehicle turns over during transportation, being struck heavily in takeoff or landing accident while being carried by airplane, impacting with launch platform or buildings when there is abnormality during launch of multiple - stage rocket. impact of great intensity takes place in such accidents, which will lead to srm ignition or explosion

    固體火箭發動機在貯存、運輸、維護及使用過程中可能遇到各種意外機械撞擊激勵，例如:吊裝過程中跌落，運輸過程中因交通事故發生翻覆碰撞，機載固體導彈掛飛時因載機發生起降事故導致高速沖撞，多級火箭發射初期因發射異常與發射架或地面建築物發生碰撞等，固體火箭發動機將受到劇烈機械撞擊載荷作用，導致其著火燃燒甚至爆炸。
  14. The improvement to internal ballistic calculation precision of solid rocket motor ( srm ) is important to capture target of missile. and to accomplish it ' s task. calculation of burning surface of propellant grain is essential to interinal ballistic performance calculation

    提高固體火箭發動機內彈道的計算精度對導彈準確捕獲目標、完成任務有著重要的作用，而發動機工作時瞬態燃面計算是內彈道性能計算的基礎。
  15. The surrogate kw and rocket motor separation for the navy ' s theater wide missile defense system are shown at the high speed test track at holloman air force base in new mexico during a test on june 24, 1999

    美國海軍導彈防禦動能彈頭的替代彈頭， 1999年六月24日在美國新墨西哥州和羅曼空軍基地，圖為推動器與彈頭分離。
  16. Through malfunction of the tests of 810 research institute, the combustion performance of the hybrid motor and model about regression rate have been studied in the dissertation. the main aspects are as follows : the performance of the hno3 + n2o4 - htpb hybrid rocket motor were all discussed

    本文結合航天科技集團公司810研究所正在研製的ak - 20l / htpb + al組合固液火箭發動機，開展了固液火箭發動機混合燃燒特性的數值模擬工作，在此基礎上給出固體燃料退移速率預示模型及預示結果。
  17. Reliability analysis of solid rocket motor grains with response surface methodology

    固體火箭發動機藥柱點火過程結構可靠性的響應面法
  18. It is important to develop experiment techniques to simulate flow field in the study of solid rocket motor with high acceleration

    本文以高過載固體火箭發動機研製需求為背景，圍繞高過載發動機內流場的地面模擬試驗技術展開研究。
  19. Research on grouting repair technique for grain cracks of solid rocket motor

    固體火箭發動機藥柱裂紋灌漿修補技術研究
  20. Gap design of solid rocket motor nozzle was analysized through thermal and structure analysis

    摘要通過熱和結構計算，對固體火箭發動機噴管縫隙設計進行了分析。
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