基于控制壁面压力分布的分级单边膨胀喷管设计及试验验证  

Design and Experiment Validation of Single Expansion Ramp Nozzle Based on the Control of Wall Pressure Distribution

作　　者：全志斌[1] 徐惊雷[1] 莫建伟[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2013年第3期307-310,共4页Journal of Propulsion Technology

摘　　要：提出了基于控制壁面压力分布的分级单边膨胀喷管(SERN)设计思想。在强几何限制条件下,设计了一个基准模型A,与采用分级膨胀思想设计的模型B进行对比。然后,对模型B喷管进行缩比进行了冷流试验,试验与数值模拟结果吻合良好,说明数值模拟结果可靠。模型A与模型B数值模拟的对比结果表明,模型B喷管在推力性能下降很少的前提下,冷热态俯仰力矩差较模型A下降了44.6%,有效减小了飞行器的配平难度,验证了该设计思想的正确性。There is a great change in pitch moment after the ignition of the scramjet,which has a serious impact on the attitude control of the aircraft.Design idea of two-stage-expansion SERN based on the control of wall pressure distribution was presented.Reference model A and comparison model B which is on the basis of two-stage-expansion were designed under strict geometry restricts.Then,cold-flow static testing and numerical simulation were conducted on the scaled model of B,which agreed well,indicating that the result of numerical simulation was reliable.Comparison is made between model A and model B,indicating that pitch moment difference between cold-state and hot-state of model B decreases by 44.6% than that of model A on the premise that thrust performance descends little for Model B,which effectively reduces the difficulty of the balance of aircraft and verifies the correctness of the design idea.

关 键 词：单边膨胀喷管 壁面压力分布 推力性能 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]