As one of key technologies to acquire the adequate thrust to start the rbcc propulsion system , whether the ejecting technology can produce thrust augmentation in ejecting mode of rbcc is greatly related to whether the potential advantages of rbcc " s high efficiency and low cost can be realized 作為解決rbcc啟動階段動力問題的關(guān)鍵技術(shù)之一的引射技術(shù)能否在rbcc引射模態(tài)獲得理想的性能增強關(guān)系到能否真正發(fā)揮rbcc大幅度提高航天推進系統(tǒng)經(jīng)濟性與高效性的潛在優(yōu)勢。
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(jié)構(gòu)、二次流來流速度、二次燃燒組織對引射模態(tài)性能的影響,發(fā)現(xiàn)實驗樣機構(gòu)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。
It is of great significance to investigate performance characteristics and thrust augmentation mechanism in rbcc engine . this dissertation just deals with the mixing and combustion flow in a experimental strutjet rbcc in ejecting mode to investigate its performance characteristics and thrust augmentation mechanism by applying numerical simulation technique . the detail is as follows : 1 本文應用數(shù)值技術(shù)對支板式rbcc發(fā)動機,即支板火箭引射沖壓組合發(fā)動機,引射模態(tài)的燃燒與流動現(xiàn)象進行了研究,探討了rbcc引射模態(tài)的性能增強機理,主要有以下幾方面: 1