R - rocket motor 中文

rocket motor 火箭發動機。

火箭發動機。 “rocket“ 中文翻譯： n. 【植物；植物學】芝麻菜；紫花南芥。 “motor“ 中文翻譯： n. 1.原動者；原動力。 2.發動機；馬達；電動機；【 ...“motor; rocket“ 中文翻譯：火箭發動機“advanced solid rocket motor“ 中文翻譯：先進固體燃料火箭發動機“aerojet rocket motor“ 中文翻譯：空氣噴氣火箭發動機“aircraft rocket motor“ 中文翻譯：飛機火箭發動機“annular rocket motor“ 中文翻譯：環形火箭發動機“apogee rocket motor“ 中文翻譯：在遠地點打開的火箭發動機“arc-jet rocket motor“ 中文翻譯：電弧噴射火箭發動機“bi-fuel rocket motor“ 中文翻譯：二元燃料火箭發動機“bipropellant liquid rocket motor“ 中文翻譯：二元推進劑液體火箭發動機“chamber; rocket motor“ 中文翻譯：火箭發動機燃燒室“cooled rocket motor“ 中文翻譯：冷卻式火箭發動機“drill rocket motor“ 中文翻譯：訓練用火箭發動機“end-burning rocket motor“ 中文翻譯：端面燃燒火箭發動機“four-engined rocket motor“ 中文翻譯：四燃燒室火箭發動機“gas-pressurized rocket motor“ 中文翻譯：氣體擠壓供油式火箭發動機; 氣壓式液體火箭發動機“gimbaling rocket motor“ 中文翻譯：萬向架支座火箭發動機“gimballing rocket motor“ 中文翻譯：框架固定式火箭發動機, 萬向架[常平架]支座火箭發動機“ion rocket motor“ 中文翻譯：離子火箭發動機“lift of rocket motor“ 中文翻譯：火箭發射機的升力“liquid rocket ablative motor“ 中文翻譯：有燒蝕防熱系統的液體火箭發動機“liquid-fuel rocket motor“ 中文翻譯：液體燃料火箭發動機“liquid-propellant rocket motor“ 中文翻譯：液體推進劑火箭發動機“operational rocket motor“ 中文翻譯：作戰型火箭發動機

rocket plane
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。
New insight also was offered on chinese solid rocket motor technology work , important for both missile and space launch applications 研究還提供了對于導彈和航天發射都具有重要影響的固體火箭發動機技術工作。
It is an effective new processing way for loading of the solid rocket motor with high loading density , high propellant mass fraction propellant 為今后高裝填密度、高質量比的發動機裝藥開拓出一條新途徑。
Structure strength of flanged connection for rocket motors must be guaranteed in bolt - up and operating conditions 火箭發動機法蘭連接結構首先要求各連接元件在預緊和操作情況下不發生強度破壞。
An example of solid rocket motor design proved that the recad system software is effective and convenient in solid rocket motor design 經過實例測試，證明該軟件系統具有一定的實用價值。
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，并進行了實驗研究。
Coupling computation on radial vibration of chamber structure and internal ballistic property for solid rocket motor 固體火箭發動機燃燒室結構徑向振動與內彈道性能的耦合計算
Progress and prospect in technology of monitoring and testing for health and failure determination in solid rocket motor 固體火箭發動機狀態監測和失效判定技術的發展和展望
A . ciucci , et al . numerical analysis of ignition transients in solid rocket motors 余貞勇，固體火箭發動機翼槽內火焰傳播機理研究，西北工業大學博士論文， 2000 . 3 。
The experiment research of the energy characteristics of the solid propellant of the over - storage solid rocket motors 超期貯存發動機固體推進劑能量特性試驗研究
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。
Study on hybrid orbit self - adaptive guidance scheme of solid rocket motor based on depleted shutdown 基于固體火箭發動機耗盡關機的混合軌道自適應制導方案研究
The influence of tail grain configuration on the ignition pressurization of a small - scale solid rocket motor 小型固體發動機尾部藥型對點火升壓過程的影響
Application of infrared thermal imaging device in temperature measurement of solid rocket motor plume 紅外熱像儀在固體火箭發動機羽焰測溫中的應用
The low frequency burning oscillation of the 85 % h202 - pe hybrid rocket motor is discussed 研究了85 hzoz ? pe固液火箭發動機的低頻振蕩燃燒現象。
A ga to resolve process route optimization of solid rocket motor shell is studied 研究了基于遺傳算法的固體發動機殼體工藝流程面向成本優化問題。
Design optimization of chamber pressure and nozzle area expansion ratio of solid rocket motors 固體火箭發動機燃燒室壓強及噴管擴張比優化設計
Application of finite elements analysis in the sealing design of solid propellant rocket motor 有限元分析在固體火箭發動機密封性設計中的應用
Three - dimension incompressible and nearly incompressible analysis of solid rocket motor grain 固體火箭發動機藥柱不可壓和近似不可壓三維分析

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rocket motor

rocket motor 火箭發動機。

rocket plane

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。

New insight also was offered on chinese solid rocket motor technology work , important for both missile and space launch applications 研究還提供了對于導彈和航天發射都具有重要影響的固體火箭發動機技術工作。

It is an effective new processing way for loading of the solid rocket motor with high loading density , high propellant mass fraction propellant 為今后高裝填密度、高質量比的發動機裝藥開拓出一條新途徑。

Structure strength of flanged connection for rocket motors must be guaranteed in bolt - up and operating conditions 火箭發動機法蘭連接結構首先要求各連接元件在預緊和操作情況下不發生強度破壞。

An example of solid rocket motor design proved that the recad system software is effective and convenient in solid rocket motor design 經過實例測試，證明該軟件系統具有一定的實用價值。

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，并進行了實驗研究。

Coupling computation on radial vibration of chamber structure and internal ballistic property for solid rocket motor 固體火箭發動機燃燒室結構徑向振動與內彈道性能的耦合計算

Progress and prospect in technology of monitoring and testing for health and failure determination in solid rocket motor 固體火箭發動機狀態監測和失效判定技術的發展和展望

A . ciucci , et al . numerical analysis of ignition transients in solid rocket motors 余貞勇，固體火箭發動機翼槽內火焰傳播機理研究，西北工業大學博士論文， 2000 . 3 。

The experiment research of the energy characteristics of the solid propellant of the over - storage solid rocket motors 超期貯存發動機固體推進劑能量特性試驗研究

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。

Study on hybrid orbit self - adaptive guidance scheme of solid rocket motor based on depleted shutdown 基于固體火箭發動機耗盡關機的混合軌道自適應制導方案研究

The influence of tail grain configuration on the ignition pressurization of a small - scale solid rocket motor 小型固體發動機尾部藥型對點火升壓過程的影響

Application of infrared thermal imaging device in temperature measurement of solid rocket motor plume 紅外熱像儀在固體火箭發動機羽焰測溫中的應用

The low frequency burning oscillation of the 85 % h202 - pe hybrid rocket motor is discussed 研究了85 hzoz ? pe固液火箭發動機的低頻振蕩燃燒現象。

A ga to resolve process route optimization of solid rocket motor shell is studied 研究了基于遺傳算法的固體發動機殼體工藝流程面向成本優化問題。

Design optimization of chamber pressure and nozzle area expansion ratio of solid rocket motors 固體火箭發動機燃燒室壓強及噴管擴張比優化設計

Application of finite elements analysis in the sealing design of solid propellant rocket motor 有限元分析在固體火箭發動機密封性設計中的應用

Three - dimension incompressible and nearly incompressible analysis of solid rocket motor grain 固體火箭發動機藥柱不可壓和近似不可壓三維分析