solid-propellant rocket motor 中文意思是什麼

solid-propellant rocket motor 解釋
固體燃料火箭發動機
  • solid : adj 1 固體的；實心的，實質的，密實的。2 【數學】立體的，立方的，三維的。3 結實的，堅強的，堅固的...
  • propellant : n. 推進物，推進劑；（槍炮的）發射火藥；噴氣燃料。 high-energy propellant 高能燃料。 work horse propellant 【火箭】通用燃料。
  • 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. Analysis of nozzleless solid propellant rocket motor performance

    無噴管固體火箭發動機內彈道計算
  2. 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。
  3. 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。
  4. 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。
  5. In this paper, simple reacting flow model in solid - propellant ducted rocket combustor based on eddy break - up model is established. the model is used to simulate the three - dimensional combustion flowfields in an experimental motor. some factors how to affect the combustion efficiency are discussed in the paper, including air intake and gas generator nozzle

    本文基於簡單反應的旋渦分裂模型，建立了固體火箭沖壓發動機補燃室內的湍流燃燒模型，並在該模型下對某實驗發動機進行了三維數值模擬，研究了補燃室設計參數包括進氣道出口設計參數和燃氣發生器噴管設計參數對燃燒效率的影響。
  6. Study on strap - on pressure propellant loading process for solid rocket motor

    固體發動機捆綁式加壓成型裝藥工藝研究
  7. The scraping coat technique for the thin layer propellant loading processing in mini inside radius solid rocket motor, precuring - bonding technique and secondary vacuum - pressure casting are developed and used to load the big slenderness ration ( 12. 5 / 1 ) solid rocket motor with thin web, internal insertion radial concentric dual - layer propellant

    探索出小口徑薄層藥刮塗成型工藝、預固化粘結技術，二次真空加壓澆注，實施了大長細比（ 12 5 1 ）發動機薄肉厚內嵌式徑向同心雙層裝藥。
  8. It is an effective new processing way for loading of the solid rocket motor with high loading density, high propellant mass fraction propellant

    為今後高裝填密度、高質量比的發動機裝藥開拓出一條新途徑。
分享友人
分享到 Line

分享到臉書