thrust nozzle 中文意思是什麼
thrust nozzle
解釋
推力噴管-
We had nozzle failure. then the thrust manifold went all haywire
噴射器出了問題.推進器都出了故障 -
The truncated nozzle is found to have a higher thrust.
截斷的噴管具有較大的推力。 -
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。 -
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。 -
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。 -
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。 -
More than 200 different condition 3d viscosity steady flow fields in the thrust vectoring nozzle at different nozzle pressure ratio and different nozzle area ratio and different geometric defected angle is calculated by the program developed. and the related performance parameters are acquired by numerical simulation
利用該程序計算了某矢量噴管在不同的壓比、面積比和幾何偏轉角下的200多種三維有粘流場，獲得了矢量噴管的性能數據。 -
The main works and contribution of this paper are as follows : 1. central type finite volume method proposed by jameson a. is investigated and the boundary condition of the method is improved. compared with the testing data it is proved that the program for 3d viscosity steady flow in thrust vectoring nozzle developed is correct and reasonable
研究了jamson提出了中心型有限體積法，並改進了其在邊界上的處理，通過驗證計算驗證了本文發展的矢量噴管三維有粘流動計算程序的正確性。 -
The energy equation of the thrust chamber wall was developed by omitting radical heat conduction and only considering the radiation heat transfer of the four chambers, the radiation leakage through nozzle exit, the axial and circular heat conduction
忽略徑向導熱，考慮推力室外向的相互及自身輻射交換、內壁經噴口的輻射泄漏以及周向和軸向的傳導熱量，建立了推力室壁的能量方程。 -
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。 -
The unsteady flow as thrust vectoring nozzle deflecting dynamically is investigated. the method of calculating the unsteady flow in the nozzle is given and the flow of the nozzle in the maximum power setting and maximum a / b power setting of the engine is calculated
研究了矢量噴管動態偏轉過程中氣流的非定常流動和矢量噴管非定常流動計算方法，計算了矢量噴管在發動機某中間狀態和加力狀態下的非定常流場。 -
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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