ducted rocket 中文意思是什麼

ducted rocket 解釋
沖壓火箭復合式發動機
  • ducted : 管道中的
  • 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...
  1. Mayer a e h j, stowe r a. experimental study into mixing in a solid fuel ducted rocket combustion chamber [ r ]. aiaa 2000 - 3346

    餘勇，陳小前，等.三維實驗固體火箭沖壓發動機燃燒室湍流反應流數值模擬[ j ] .國防科技大學學報， 2002 ， （ 5 ）
  2. The solid - propullant ducted rocket, which combines the advantages of solid propullant rocket and ramjet propulsion, is a new kind of combined propulsion system. it offers considerable advantages for missile propulsion, such as high specific impulse, high speed, light weight, long range, high maneuver and simple structure. as the major direction of the propulsion system for supersonic missile, the ducted rocket has good prospects

    它將固體火箭技術和沖壓技術有機結合在一起，具有比沖高、速度快、重量輕、射程遠、機動性能好和結構簡單等諸多優點，最大限度地滿足了新一代導彈對其動力裝置提出的要求，是超聲速導彈動力裝置的一個主要發展方向，有著廣闊的研究前景。
  3. 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。
  4. It is a key technique for ducted rocket to make the second combustor operate at high efficiency and stability

    實現補燃室高效率、穩定、可靠的工作，是固體火箭沖壓發動機的關鍵技術問題。
  5. In addition, the usaf continues to fund development work of the aerojet ( formerly atlantic research ) variable flow ducted rocket ramjet system as a future propulsion option for an extended range aam

    此外，美國空軍繼續投資于航空噴氣研究所（原來的大西洋研究所）的可變噴流管火箭發動機系統，將其作為增程空空導彈的未來推進選項。
  6. The results showed that the environmental pressure and catalysts have various actions on the thermal decomposition characteristics of the propellant and its ingredients. the burning rates of the gap / tmo fuel - rich propellants were measured by use of the pipe - connected unchoked ducted rocket testing facility

    實驗結果表明，在不同壓強下，貧氧推進劑各組分的熱分解特徵有所不同；在同一壓強下， tmo催化劑對貧氧推進劑中不同組分的催化作用不盡相同；同一催化劑，在不同壓強下對同一組分的催化能力也不同。
  7. An experimental unchoked ducted rocket motor system is designed in this paper, and some experiments are finished

    本文還完成了實驗小型非壅塞固體火箭沖壓發動機設計，並進行了實驗研究。
  8. Study of the unchoked ducted rocket engine and fuel - rich propellant

    非壅塞固體火箭沖壓發動機及其貧氧推進劑
分享友人
分享到 Line

分享到臉書