固冲发动机射流控制可调进气道研究  

Study on jet controlling inlet of solid rocket ramjet

作　　者：冯喜平[1] 林志远[1] 郑亚[1] 李进贤[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2010年第4期396-400,共5页Journal of Solid Rocket Technology

摘　　要：针对固定几何形状固冲发动机超音速进气道在超额定状态下工作时品质降低问题,提出从补燃室引入燃气喷入外压缩面和喉道实现对进气道外压缩波系和有效喉道面积进行调节的方案,采用数值模拟方法摸索了实现调节的燃气喷射规律,验证了方案的可行性。研究表明,采用射流控制方案可实现固冲发动机进气道调节,通过调节可使外压缩波系保持封口,进气道工作在额定状态,均化了入口流场;喉部射流注入可有效减小主流的流通面积,提高内收缩比,并减小了喉道出口下壁面附面层厚度,进气道出口总压恢复提高显著。To solve the problem of performance reduction for fixed-geometry inlet of solid rocket ramjet working at overrated design mach number,a jet controlling inlet scheme was proposed,which bring the gas from second-combustion chamber to external compression face and throat to adjust the external shocks and effective throat area.By using the numerical method,adjusting regularity was obtained and the feasibility of this scheme was validated.The results show that shock-on-lip conditions could be maintained,initial flow field was homogenized,effective throat flow area and boundary layer thickness at lower wall of throat outlet could be reduced,so compression ratio and the total pressure recovery are increased significantly.

关 键 词：固冲发动机 可调进气道 射流控制 数值模拟 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]