rocket propellant 中文意思是什麼

rocket propellant 解釋
火箭燃料
  • 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...
  • 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。
  1. Propellant is another term for the fuel of a rocket.

    推進劑是火箭燃料的另一術語。
  2. Abstract : solid propellant rocket motors are preferred for most ballistic missiles because they need simple maintenance and can be launched quickly. but the conventional thrust termination devices limit the depletion of every stage ' s grain and increase some extra - weight. an improved method for designing a multi - stage solid rocket based depleted shutdown was provided. in order to solve the problem of lack of thrust termination devices, a device to adjust the burnout angle will match the final burnout velocity and satisfy the desired range. the method can also limit the detection from anti - ballistic missile system

    文摘:由於維護簡單和發射快速，彈道導彈多用固體火箭發動機，但繁雜的推力終止裝置使各級裝藥不能耗盡並讓結構增重.提出了一種對基於耗盡關機多級固體火箭概念設計的改進方法，此方法滿足導彈系統主要的戰技要求.為解決無推力終止裝置的末速不準問題，可在末級發動機採用姿態調整裝置，對射角進行調整，配合末速以滿足射程要求.本方法還可抑制敵方反導探測
  3. Analysis of nozzleless solid propellant rocket motor performance

    無噴管固體火箭發動機內彈道計算
  4. To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood.

    為了分析液體推進劑火箭發動機燃燒室中存在的非穩態環境，必須很好地了解穩態狀態。
  5. We shall try by means of a highly simplified development to expose certain advantages and disadvantages of solid propellant rocket systems.

    我們想通過相當簡單的推導來試圖闡明固體推進劑火箭系統的某些優缺點。
  6. 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。
  7. 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。
  8. As the air - breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition

    作為吸氣式發動機，其性能不僅取決于發動機本身結構和推進劑性能，與飛行狀態也有密切的聯系。
  9. Without any foreign assistance, china has independently developed intermediate and short - range missiles, long - range rockets, submarine - launched solid - propellant rockets, recoverable satellites, the technology to launch multiple satellites atop a single rocket, and geostationary communication satellites

    中國的中近程導彈、遠程火箭、潛艇水下發射固體燃料火箭、返回式衛星、一箭多星、地球靜止軌道通信衛星都是在沒有任何外國幫助下獨自完成的。
  10. 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。
  11. Liquid propellant rocket

    液體推進劑火箭
  12. Comparing to the direct drain cool - down process used in china, the natural precooling cycle, which may save the propellant of the precooling, simplify the prestart program, delay the ignition of the rocket and be more safe in the process of precooling as well is employed in this paper

    國外在該項領域的技術已經在實際火箭發射場得以應用，相比之下，我國仍採用排放式的預冷方法。因此，需要研究低溫液體火箭發動機循環預冷的方法，盡快實現趕超發達國家的目標。
  13. 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。
  14. Abstract : from engineering point of view, this paper presents several issues of interest and consideration strategy on failure mode analysis 、 monitoring control parameter selection of fault monitoring and detecting and hardware possibility assurance for monitoring control study of liquid propellant rocket engine for launchers

    文摘:本文從工程觀點出發，對開展運載火箭液體發動機故障監控研究所涉及到的失效模式分析、監控參數選取、故障監控方法和硬體可靠性保證措施等方面提出了若干值得注意的問題和考慮策略。
  15. Lacking of fault samples is a knotty problem in the fault detection of complex systems such as liquid - propellant rocket engines ( lre )

    在對類似於液體火箭發動機這種復雜系統的故障檢測過程中，一個非常棘手的問題是缺乏故障類樣本。
  16. In view of the fact that there are three types of a hybrid base - bleed - rocket extended - range projectile and they are different from each other in the general structural layout, their structural characteristics and the work performance of the two propellant units is analyzed in this paper

    本文針對三種總體結構布局形式不同的底排?火箭復合增程彈，分析了它們的結構特點和底排裝置、火箭裝置的工作特性，詳細討論了復合增程彈底排?火箭工作時序選擇對彈道特性的影響以及實現理論上最佳彈道的匹配條件。
  17. 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
  18. The channel scale on transpiration cooling for the platelet thrust chamber of liquid propellant rocket engine is approaching micron dimension. it is very possible that micro - scale effects will occur in the flow and heat transfer of the channel. in the past, researchs on flow and heat transfer in the platelet micro - channel are mostly based on macro - scale theory

    液體火箭發動機推力室壁面發汗冷卻通道的尺度已達微米量級，通道內的流動與換熱很可能存在微尺度效應，以前的相關研究都以宏觀尺度的理論為依據，其研究結果的合理性需要進行微尺度效應的分析。
  19. 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。
  20. Changzheng long march 2f consists of ten subsystems : rocket body, control system, propulsion system, malfunctioning detection and management system, escape system, remote monitoring system, telemetry safety system, propellant utilization system, additional system and ground facilities

    運載火箭有箭體結構控制系統動力裝置故障檢測處理系統逃逸系統遙測系統外測安全系統推進劑利用系統附加系統地面設備等十個分系統。
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