摘要
远程高超声速飞行器处于极为恶劣的气动加热与振动耦合环境中,长时间的高温与振动载荷相互叠加会导致飞行器热防护材料出现裂纹、错位、剥离或脱落,甚至会引发致命的安全事故。因此热防护材料在极端高温环境下的地面热/振联合试验测试,对于高超声速飞行器的安全可靠性设计极为重要。建立高温与振动复合试验环境,设法解决轻质多孔隔热材料在强振动下,表面温度难于准确测量与控制的难题,制作水冷式隔热装置保护价格昂贵的振动激励设备等,实现了1 500℃高温环境下高超声速飞行器轻质隔热材料的热/振联合试验。得到非金属隔热材料陶瓷纤维板内部的断裂形貌及裂纹断面特征。根据试验前、后材料的表观及微观变化以及内部结合剂的变化等试验结果,对材料进行改进。经过试验测试后,达到了使用要求。本文建立的1 500℃极端高温环境下的热/振联合试验系统及试验结果为远程高超声速飞行器热防护材料的抗振动能力评估、隔热效果确定以及材料性能的改进提供了重要支撑。
The long-range hypersonic vehicle is in an extremely harsh aerodynamic heating and vibration coupling environment.The combination of the severe high-temperature and long-time vibration environment can cause cracks,misalignment,peeling or falling off of the aircraft’s thermal protection materials,and even lead to fatal safety accidents.Therefore,the ground thermal/vibration test of thermal protection materials in ultra-high temperature environment is extremely important for the safety and reliability design of hypersonic vehicles.In this paper,a high-temperature heat/vibration combined test system is established.The difficulty of measuring and controlling the surface temperature of lightweight porous insulation materials under the strong vibration is solved.Water-cooled heat insulation device is designed to protect the expensive vibration excitation equipment.The experiment realizes the thermal/vibration test of insulation materials for hypersonic vehicle at1 500 ℃,obtaining the fracture morphology and crack section characteristics of the non-metallic insulating material of ceramic fiber plate.The test results of the appearance and microscopic changes of the materials before and after the test and the changes of the internal binder show that the material property is improved and the performance requirement is satisfied.The thermal/vibration combined test system under extreme high-temperature environment up to 1 500 ℃ and the test results provide an important basis for the evaluation of the anti-vibration capability,the determination of the thermal insulation effect,and the improvement of the material property of the thermal protection material for the long-range hypersonic vehicle.
作者
吴大方
林鹭劲
吴文军
孙陈诚
WU Dafang;LIN Lujin;WU Wenjun;SUN Chencheng(School of Aeronautic Science and Engineering,Beihang University,Beijing 100083,China;Science and Technology on Advance Functional Composites Laboratory,Aerospace Research Institute of Materials&Processing Technology,Beijing 100076,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2020年第7期210-219,共10页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(11427802)。
关键词
高超声速飞行器
高温
振动
隔热材料
热/振联合试验
hypersonic vehicle
high-temperature
vibration
thermal protection materials
thermal/vibration test
