CAJ | 학술논문

针对使用RBCC发动机作为第一级动力的两级入轨飞行器，提出了一种内置中心支板的可变几何二元混压式进气道方案。该进气道工作马赫数范围0～7，设计点Ma＝5。通过调节唇口外罩角度以及喉部的高度，可改变进气道的几何构型。数值模拟结果表明：（1）该进气道通过采取变几何和吸除措施能够在Ma＝2．4下实现自起动，为引射模态向亚燃模态转级提供了必要条件；（2）采用变几何措施可显著拓宽进气道在起动状态下正常工作的马赫数范围；（3）亚燃和超燃模态典型马赫数下，进气道出口各项性能指标适中，可以满足RBCC发动机燃烧室对进口空气参数的要求；（4）通过变几何调节，还可提高进气道的抗反压能力。
침대사용RBCC발동궤작위제일급동력적량급입궤비행기，제출료일충내치중심지판적가변궤하이원혼압식진기도방안。해진기도공작마혁수범위0～7，설계점Ma＝5。통과조절진구외조각도이급후부적고도，가개변진기도적궤하구형。수치모의결과표명：（1）해진기도통과채취변궤하화흡제조시능구재Ma＝2．4하실현자기동，위인사모태향아연모태전급제공료필요조건；（2）채용변궤하조시가현저탁관진기도재기동상태하정상공작적마혁수범위；（3）아연화초연모태전형마혁수하，진기도출구각항성능지표괄중，가이만족RBCC발동궤연소실대진구공기삼수적요구；（4）통과변궤하조절，환가제고진기도적항반압능력。
A variable-geometry RBCC inlet scheme in the form of two-dimensional mixed-compression with a central strut inside was put forward for a TSTO vehicle using RBCC engine as the first stage power.The inlet can operate from Mach number 0 to 7 and the design point Mach number is 5.The geometry configuration of the inlet could be changed through adjusting the angle of cowl lip and the height of throat.The results of numerical simulation indicate:(1) the inlet self-starting can be realized at Ma=2.4 by chan-ging its configuration and bleeding,which provides a necessary condition for the transition from ejector mode to ramjet mode;( 2) the change of inlet's geometry can greatly widen the Mach number range in which the inlet operate normally at starting mode;( 3) the performance parameters of the inlet are moderate at typical flight Mach numbers in ramjet and scramjet mode,which could meet the requirement of RBCC engine combustor for entrance air parameters;( 4) adjusting its geometry configuration can also improve the in-let's resistance to back pressure.