燃烧加热脉冲风洞气动/推进一体化试验研究

Aero-Propulsion Integration Test in Combustion Heated Impulse Facility

关键词:  高超声速飞行器  超燃冲压发动机  高焓脉冲风洞  气动/推进一体化试验  试验数据修正

Key words:  Hypersonic vehicle  Scramjet  High enthalpy impulse facility  Aero-propulsion integration test  Test data correction

摘要:

吸气式高超声速飞行器的机体与超燃冲压发动机高度耦合，使得一体化气动性能预测非常困难，但是能够开展一体化带动力试验的地面设备很少。中国空气动力研究与发展中心(CARDC)研制了一种氢氧燃烧加热高焓脉冲风洞，其有效试验时间大大超过长时间激波风洞，采用模型-天平一体化设计实现了在几百毫秒内进行高精度测力，重复性测力误差小于2%。结合数值计算进行了支架干扰、来流污染凝结、壁温等影响及试验数据修正研究。典型升力体高超声速飞行器气动/推进一体化试验结果表明:在燃烧加热脉冲设备的300 ~ 600ms有效试验时间内，能够有效获得飞行器的升力、阻力(推力)和力矩特性，试验数据与CFD计算结果基本吻合。

Abstract:

Airframe and Scramjet engine are highly coupled for the air-breathing hypersonic vehicle，making aerodynamics prediction very difficult，but the facilities available for aero-propulsion integration test are very few. A kind of hydrogen-oxygen combustion heated high enthalpy impulse facility which has much longer test duration than long-duration shock tunnels was invented by China Aerodynamics Research and Development Center (CARDC). The test model and balance are integrated designed to obtain high accuracy forces during hundreds of millisecond，and the repeatability error of measured forces is less than 2%. The model support interference，wall temperature effects，incoming flow vitiation and condensation influences were corrected by numerical analysis. The lift，drag (thrust) and moment were effectively obtained from the aero-propulsion integration test of a typical hypersonic vehicle in combustion heated impulse facility within 300 ~ 600ms duration and the test results had good agreements with the CFD predictions.