rocket nozzle 中文意思是什麼
rocket nozzle
解釋
火箭發動機噴管-
In this thesis, based on pershing ii surface to surface missile, a new kind of ballistic missile was designed with an additional rocket engine, which can be ignited twice. firstly, aerodynamic computational models of missile body and warhead which reentry with supersonic are built according to the task requirements ; secondly, the propulsion system model of missile is built whose first two stages are solid rocket engines and the third stage is liquid - solid combined rocket engine. the nozzle and the shape of the engine are designed to meet the needs of the populsion project ; thirdly, the trajectory model of the mass point is built and a wavy trajectory is designed & optimized ; finally, the ability of a missile ' s breaking through defence is analyzed
以美國潘興導彈為原型，增加可兩次點火的末級發動機，改裝成具有跳躍能力的地地彈道導彈；首先，根據任務需求，建立了導彈的氣動模型，並建立了彈頭再入時高超聲速氣動模型；其次，建立了導彈推進系統模型，前兩級採用了固體火箭發動機，第三級採用了固?液組合火箭發動機，並在總體方案要求下，對發動機噴管和外形進行了設計；第三部分，建立了導彈質點彈道模型，設計了一條跳躍式彈道，並對跳躍式彈道進行了優化設計；最後，對導彈進行了突防能力分析，從分析的結果可以看出，跳躍式彈道的突防能力比常規的拋物線彈道要強。 -
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 -
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 -
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。 -
The design of the rocket nozzle also has much to do with the behavior of the exhaust and the resulting velocity of the vehicle itself.
火箭噴管的設計與排氣的性能及飛行器本身的有效速度也有很大關系。 -
Finite element analysis based on ansys of ball - socket nozzle ' s pendulous socket in solid - rocket engine
的固體火箭發動機珠承噴管擺動接頭的有限元分析 -
Finite element software of ansys has been used for making a finite element analysis of a certain type of ball - socket nozzle ' s pendulous socket in solid - rocket engine
摘要本文應用ansys有限元分析軟體，完成了對某型號固體火箭發動機珠承噴管擺動接頭的有限元分析。 -
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。 -
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。 -
( 3 ) on the background of the development of an ignition rocket, some application investigations have been carried out. some parameters related to water - resistant ignition mixture, the charge of ignition rocket, such as heat - flow, density of charges, structure of charges, coating and its process, area ratio of nozzle and high temperature corrosion of the nozzle, were calculated and studied, respectively. on the basis of the above studies, an ignition rocket was successfully developed
（ 3 ）進行了應用研究，以某系列點火發動機的研製為背景，分別對耐水點火藥用作點火發動機裝藥所涉及的能量衡算、裝藥密度、裝藥結構、包覆及其工藝、喉面比及噴口燒蝕等問題進行了分析和實驗研究，在這些研究的基礎上成功地製作了一種點火發動機。 -
The results indicate that with decrease of exit area of secondary nozzle, the bypass ratio is decreasing, and the static pressure in integrated ejector combustor is increasing, and mixing condition becomes better. there exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector
結果表明：引射能力隨著二次噴管出口面積的減小而減小；整體式引射燃燒室壓強隨著二次噴管出口面積的減小而上升，混合隨之更為充分；存在一個最優的二次噴管出口面積，使發動機推力最大。 -
It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design. in the comparison between two configurations, the typical one has better performance, indicating the importance of pressure ratio
結果表明：在固定二次噴管出口面積和氧燃比的條件下，二次流（引射空氣流）流量的增加引起混合氣體出口速度的下降和總流量的增加，二者綜合作用使發動機推力增加，但增幅不大，表明在設計發動機結構和工作參數時，不必過分追求大的引射系數；兩種結構的性能對比分析表明了增壓比對引射火箭性能的提高具有重要意義；對引射火箭的熱力循環分析同樣表明，增壓比對于提高發動機性能非常關鍵。 -
The influence of primary flow and secondary nozzle geometry on ejector effect and thrust was investigated, and the approach to increase thrust of rocket ejector was found gradually
研究了一次流參數和二次噴管結構對引射效能和發動機推力的影響，找到了逐步提高推力的措施。 -
Grids method for chamber - nozzle integrated design in solid rocket engine
基於聚類分析和灰色模型的固體火箭發動機價格模型研究 -
Variation tendency of nozzle gap and contact stress was obtained in terms of multi - time computational results, and some modification suggestions, which are available for designers of solid rocket motor nozzle, were presented by the tendency
綜合多個時刻的計算結果得到發動機工作過程中噴管結構縫隙和接觸應力的變化趨勢，並據此對設計縫隙提出了修改意見，結果可為發動機噴管設計提供參考。
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