Research on HIFiRE project's hypersonic vehicle integrated design of aerodynamic and scramjet propulsion
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摘要: 美澳通过HIFiRE项目在高超声速飞行器的气动、推进和控制等领域进行了深入探索，并对一体化设计有动力飞行器的高速性能进行了评估。以单项验证、步步推进的系列飞行试验方式，对乘波体布局以及不同动力方式开展原理研究，结合飞行试验对设计状态进行验证，取得一系列有价值的飞行数据和阶段性成果。通过梳理气动/推进一体化过程中相关飞行试验，提炼出总体设计中的关键技术和试验结论，并对有动力飞行器的发展趋势作了分析。研究显示发生转捩的单位雷诺数范围在3×106~4×106之间，适应小迎角高升力特点的乘波体与超燃冲压发动机的组合成为优选方案，所取得的成果为带超燃冲压发动机高速飞行器总体方案设计提供了一定的参考。Abstract: By the HIFiRE project, America and Australia have deeply investigated the aerodynamics, propulsion and controlling system of hypersonic aircrafts. The high-speed ability is evaluated for the integrated design of aircrafts with propulsion system. A series of valuable flight-data and staged achievements are obtained by the flight tests of single-target evaluation and step-by-step improvement, the principal study of waverider shapes and different propulsion systems, and the verification of designing condition by flight tests. The key technique and experimental conclusion are summarized for the overall design by organizing the flight tests of dynamics/propulsion integrated processes. Moreover, the developing trend is analyzed for the aircraft with propulsion system. The results show that the unit Reynolds number of the transition is between 3×106 and 4×106, and a combination of scramjet and waverider with high lift characteristics at small attack angle is the optimized design, which gives some suggestions for the overall design of high-speed aircrafts with scramjet.
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Key words:
- aerodynamic layout /
- propulsion system /
- integrated design /
- hypersonic /
- flight test
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图 15 带超燃冲压发动机高超声速飞行器项目进度图
Figure 15. Project schedule of hypersonic vehicle with scramjet
表 1 HIFiRE项目飞行试验
Table 1. Flight test of HIFiRE project
序号 机构 研究内容 飞行试验时间 飞行试验结果 气动 HIFiRE-0 DSTO 软、硬件系统，传感器及地面遥测系统，重新定位能力 2009.05.07 基本成功 HIFiRE-1 AFRL 圆锥体边界层转捩，激波/边界层干扰 2010.03.22 基本成功 HIFiRE-5 AFRL 三维效应下椭球锥转捩，C/C-SiC材料性能 2012.04.23 失败 HIFiRE-5B AFRL 三维效应下椭球锥转捩，C/C-SiC材料性能 2016.05.18 基本成功 HIFiRE-4 DSTO 乘波体滑翔飞行器布局设计及飞行控制策略 2015.10 成功 动力 HIFiRE-2 AFRL 二元超燃冲压发动机模态转换 2012.05.01 成功 HIFiRE-3 DSTO 轴对称RF超燃冲压发动机 2012.09.13 成功 HIFiRE-7 DSTO 三维REST超燃冲压发动机 2015.03.30 失败 HIFiRE-7B DSTO 三维REST超燃冲压发动机 预计2017 一体化 HIFiRE-6 AFRL 采用AFCS技术的高超声速飞行器机动性能 预计2017 HIFiRE-8 DSTO 气动/动力一体化飞行器30s可控巡航飞行 预计2017 
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