ATR动力飞行器的变几何进气道设计研究

摘要

A variable-geometry inlet scheme is proposed to meet the demands of a Ma 0.6 ～ 3.0 air turbo rocket (ATR) powered vehicle,especially seeking the aerodynamic devices to balance the inlet performance within the broad velocities and to control the distortion of the inlet exit for an engine compressor.The inlet consists of a translate-movable half-cone center body for conducting adjustment of the throat area and the captured mass flow.Also the pressure distortion is decreased by using of a spoiler and a lattice grid.With computational fluid dynamics (CFD) analyses,the drive positions of the inlet center body are determined for every operating condition,and then the flow structures and the performance parameters are discussed in detail.The rationality of the inlet design is indicated by the favorable parameters,like the suitable total pressure recovery and steady pressure distortion less than 5％.A wind-tunnel test is conducted between Ma 0.6 and Ma 2.0 to preliminarily verify the inlet scheme design and the numerical simulations.The consistency of the experiment and the analysis further demonstrates the correctness of the missile-borne variable-geometry inlet.%针对飞行器总体和空气涡轮火箭(ATR)发动机的设计要求,提出一种中心半锥体可调节的变几何进气道方案,探索了Ma 0.6～3.0宽速域性能平衡、类航发需求的出口畸变控制等设计方法.通过中心体的平移进行喉道面积调节并兼顾流量需求,扩张段设置扰流片和格栅来控制流动畸变,相应方案结构简单紧凑、具有实用性.采用计算流体力学(CFD)方法模拟确定了各工况下进气道中心体的驱动位置,分析进气道的流场特性和性能参数.数值模拟结果体现了进气道波系配置、边界层放气和控制流动畸变措施的合理性,总压恢复和流量捕获符合设计指标,出口稳态畸变指数不大于5％.完成变几何进气道方案的Ma 0.6～2.0风洞试验研究,获得了典型超/亚声速工况下进气道的主要性能,初步验证了弹用变几何进气道方案设计的正确性.