推力噴管 的英文怎麼說

中文拼音 [tuīlìpēnguǎn]
推力噴管 英文
propelling nozzle
  • 推 : 動詞1 （向外用力使物體移動） push; shove 2 （磨或碾） turn a mill or grindstone; grind 3 （剪或削...
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 噴 : 噴動詞1. （液體等受壓力而射出） spurt; spout; gush; jet 2. （噴灑） spray; sprinkle
  • 管 : Ⅰ名詞1 （管子） pipe; tube 2 （吹奏的樂器） wind musical instrument 3 （形狀似管的電器件） valve;...
  • 推力 : visatergo; soot; propulsive force; thrust; momentum thrust
  1. Deere k a. computational investigation of the aerodynamic effects on fluidic thrust vectoring. aiaa 2000 - 3598

    喬渭陽，蔡元虎.基於次流噴射控制推力矢量噴管的實驗及數值研究.航空動力學報， 2001 ， 16 （ 3 ）
  2. The truncated nozzle is found to have a higher thrust.

    截斷的噴管具有較大的推力。
  3. 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。
  4. A three layers thruster was designed. the middle layer was chamber, the top layer was ignition circuit and the bottom layer contained a diaphragm with several nozzles. it could integrate 4 micro - thruster which diameter was 0. 8mm on the diaphragm with 10 * 10 * 2mm

    在實驗中，設計了三層的推力器結構，中間為藥室，上層和下層為點火電路和帶噴管的蓋片，可以在10 10mm和2mm厚的板上集成了4個直徑為0 . 8mm的微推力器。
  5. Based on the empirical equations used for calculating the cost of main and distribution pipes of gravity sprinkler irrigation project, equations for calculating. 4. economical hydraulic gradient, pipe length and the minimum cost of the main pipe were derived through theoretical analysis and mathematical transformation

    3 .在建立的自壓噴灌工程主幹管和配水管道的造價計算經驗公式基礎上，通過理論分析和數學變換，推導得出了自壓噴灌主幹管經濟水力坡度、經濟管長和最低造價計算公式。
  6. Abstract : this paper briefly presents th e application of advanced brazing techniques for a larye number of assemblies of space vehicles, such as thrust chamber and turbine rotor of launch rock et engine, titanium tube of satellite, attitude control engine injector and wave guide component of satell ite, reflector, tube and honeycomb panel of manned spacecraft, main engine nozzl e and preburner of space shuttle as well as the pipeline systems of space statio n

    文摘:簡略地介紹了先進釬焊技術在航天器部件，例如運載火箭發動機的推力室和渦輪轉子、人造衛星的鈦導管、姿控發動機噴注器和波導器件、載人飛船的反射器、導管和蜂窩壁板、航天飛機的主發動機噴管和預燃室以及空間站的管路系統等的廣泛應用情況。
  7. The effects of such elements as primary flow total pressure, flow rate, degree of fuel rich, nozzle structure, flying speed and secondary combustion on ejecting mode performance were researched. it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0. 7. to deeply analyze thrust augmentation mechanism in low speed range, the research was further continued by changing secondary combustion organization and aft - body configuration

    研究了一次流總壓、流量、富燃程度、噴管結構、二次流來流速度、二次燃燒組織對引射模態性能的影響，發現實驗樣機構型在0 . 7ma以上的飛行條件下可以獲得推力增強，而在0 . 7ma以下無推力增強。
  8. The application background of thrust vectoring technology on aircraft and its advantages are analyzed. the main characteristics of some type of vectoring nozzles are discussed, the expression of thrust vectoring force and moment are set up. then, the nonlinear motion equations of aircraft with three axes of thrust vectoring are deduced

    本文主要針對推力矢量飛機非線性飛行控制的理論和應用問題進行了一定的探索和研究，進行的主要工作有： 1 、研究了推力矢量在飛機上的應用背景和收益，分析了現有推力矢量噴管的主要形式和特點，給出了推力矢量力、力矩的數學模型，並在此基礎上推導了帶三軸推力矢量飛機的非線性運動方程，為控制律的設計奠定基礎。
  9. With the rapid development of micro - satellite technology in china, micro nozzle being the key component of the micro - propulsion system has been paid much effort of research, in this realm, the simulation of rarefied flow in the micro nozzle is the key step for the design and performance improving of micro nozzle

    隨著我國微小衛星研製的大力發展，作為微推進系統關鍵部件的微噴管研究成了重要的研究課題之一，對微噴管內流場稀薄氣流的模擬分析是微噴管設計和性能改善所需要解決的關鍵問題。
  10. Chapter ii : latent capacity and present conditions of water resource. first, the author introduced the total amount and distribution of water resource in the east and central area of gansu, and then discussed the current utilization and contradiction between supply and demand of water resource. and last, the author posed the measures and countermeasures of exploiting water resource. chapter iii : latent capacity and present conditions of land resource. first the author introduced the total amount and distribution of land resource. and then discussed the current conditions utilization and latent capacity of land resource

    對東中部地區的水資源總量、分佈和特點進行定量和定性的分析，以灌區水資源利用及供需矛盾為突破口，對水資源潛力開發的幾個關鍵問題進行了分析：加強與水資源相關的基礎問題的研究；強化水資源危機的意識，建立節水工農生產體系；建立流域水資源統一管理機構；強化節水農業科技成果的推廣轉化；逐步推行噴、微灌高新節水技術；充分利用化學調控技術提高作物抗旱性和水分利用效率；大力發展以集雨節灌技術為核心的集水農業。
  11. Cfd is also used to get the data of performance parameters of the nozzle at different nozzle pressure ratio, different nozzle area ratio and different geometric defected angle. the theory of function approximation is used to establish the transient model of thrust vectoring with the data calculated

    本文通過cfd計算獲得矢量噴管的性能參數，如流量系數、推力系數以及有效推力矢量角等與矢量噴管壓比、面積比以及幾何偏轉角之間的關系數據，並利用函數逼近理論建立了矢量噴管的動態數學模型。
  12. The comparision of the computation result and the experimental data shows that prediction of ka series propeller by surface panel method is feasible

    本文嘗試建立一種面元法預報導管螺旋槳水動力性能的方法，為設計導管螺旋槳和研究泵噴射推進裝置建立基礎。
  13. The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation, indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design

    表明在引射火箭設計時，應結合引射火箭的結構和流動參數對二次噴管出口面積進行優化設計，以達到最佳推力性能。
  14. The experimental results indicates that the secondary mass flow increases with increasing of primary mass flow rate, but the bypass decrease because the primary mass flow rate increase more rapidly than secondary mass flow. the expansion configuration shows low thrust property due to low pressure in flow path. the secondary nozzle changes the pressure distribution in ejector combustor, and decreases bypass ratio, but obtain more completely mixing

    結果表明：二次流流量隨著一次流流量的增加而增加，由於二次流流量的增加速度低於一次流，引射系數減小；在純擴張式結構實驗中，引射燃燒室壓強很低，難以實驗推力增強；二次噴管改變了引射燃燒室的壓強分佈，降低了引射系數，改善了混合狀況能；對于本文的實驗結構，存在一個最優的二次噴管出口面積，使引射火箭推力最大，同數值模擬結果相吻合。
  15. Engineering drawing system can draw two dimension curve graphs, main detail drawing and assembly drawing. the curve of internal trajectory and dynamic simulation of particle external trajectory. the detail drawing includes the graph of chamber, grain design, connection body, nozzle, some standard part

    工程繪圖可以繪制二維曲線圖和零部件圖，其中二維曲線包括有內彈道壓（推）力?時間曲線、質點外彈道動態模擬曲線；零部件圖包括有標準螺栓與螺紋孔、燃燒室結構圖、裝藥設計截面圖、連接底結構圖、噴管結構圖及火箭發動機總體裝配圖。
  16. When liquid propellants are used the fuel and oxidize are fed under pressure to one or more combustion chambers and expanded to atmosphere through convergent-divergent nozzles.

    當使用液體推進劑時，在壓力作用下，燃料和氧化劑輸送到一個或幾個燃燒室中，並通過收斂-打散噴管，排到大氣中。
  17. 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。
  18. 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。
  19. 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。
  20. And establishing the model of the thrust vectoring nozzle is the base for researching thrust vectoring technique and engine performance with vectoring nozzle, especially the integration of flight and propulsion system control ( ifpsc ). so thrust vector modeling is very important and meaningful

    矢量噴管是實現推力矢量的關鍵部件，建立其數學模型是推力矢量技術尤其是開展帶矢量噴管的發動機研究以及飛推一體化綜合控制研究的基礎，具有十分重要的意義。
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