火箭推力室 的英文怎麼說
中文拼音 [huǒjiàntuīlìshì]
火箭推力室
英文
rocket thrust chamber-
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。The results of static firing test shows that the thermal erosion properties, mechanical properties, tand thermal shock resistance of the c / sic composites can meet a demand for thermal - structure application in the area of aerospace such as liquid rocket thruster
試驗發動機地面熱試車結果表明，該c / sic復合材料的力學性能、燒蝕性能和熱震性能優良，可滿足宇航工程中諸如液體火箭發動機推力室等對熱結構材料的使用性能要求。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。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。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。Design method of multiperforated grain for single - chamber dual - thrust rocket motor
火箭發動機單室雙推力多孔裝藥設計方法In this paper, the characteristics of tripropellant rocket engine was studied in two different ways : experiment and simulation
本文從實驗、模擬兩個方面對三組元液體火箭發動機推力室的工作過程進行了研究。分享友人