CAJ | 학술논문

基于传统的“等压面假设”理论,建立了RBCC发动机主火箭的引射性能分析模型,研究了主火箭总压与RBCC发动机的匹配性。研究结果表明,若隔离段通道面积比小于0.65,在主火箭总压较低条件下,隔离段内二次流容易达到壅塞,无法进一步提高空气流量；在地面静止状态下,随主火箭总压增加,空气流量逐步增大,等压面上形成Fabri壅塞后,进一步增加主火箭总压,反而会降低空气流量；在火箭引射模态下,RBCC发动机的工作状态可细分为引射作用占主导地位的进气道亚临界状态和临界状态、冲压作用占主导地位的进气道超临界状态,其分界马赫数分别约为0.7和1.5。
기우전통적“등압면가설”이론,건립료RBCC발동궤주화전적인사성능분석모형,연구료주화전총압여RBCC발동궤적필배성。연구결과표명,약격리단통도면적비소우0.65,재주화전총압교저조건하,격리단내이차류용역체도옹새,무법진일보제고공기류량；재지면정지상태하,수주화전총압증가,공기류량축보증대,등압면상형성Fabri옹새후,진일보증가주화전총압,반이회강저공기류량；재화전인사모태하,RBCC발동궤적공작상태가세분위인사작용점주도지위적진기도아림계상태화림계상태、충압작용점주도지위적진기도초림계상태,기분계마혁수분별약위0.7화1.5。
Based on the traditional “pressure equal plane” hypothesis, ejection performance analysis model for RBCC primary rocket was established. Operation match between primary rocket and RBCC engine was investigated.The results show that:If the ar-ea ratio of isolator cross section is less than 0.65, flow choke will appear in isolator under lower total pressure of primary rocket, limiting further improvement of air mass flow.For ground static condition, the air mass flow increases with the increase total pressure of primary rocket. If fabric choke appears,further increasing total pressure of primary rocket will cause descending of air mass flow. During rocket ejector mode, the operation of RBCC engine can be divided into 3 different states, inlet sub-critical state dominated by ejecting effect, inlet critical state dominated by ejecting effect, inlet super-critical state dominated by ram effect, while the criti-cal Mach number for these states are 0.7 and 1.5 respectively.