摘要
为了掌握固体火箭发动机典型喷管喉衬材料的抗过载烧蚀性能,通过地面旋转模拟过载实验系统,开展了20g和30g高横向过载下的三种喉衬材料抗过载烧蚀性能研究。结果表明,在高横向过载下喷管喉衬会出现偏烧蚀现象,即过载区域喉部烧蚀厚度远大于非过载区域;与非过载区域相比,过载区域喉部烧蚀率显著增大,且过载区域喉部烧蚀率随着横向过载的增加而显著增大,20g横向过载下,高强石墨材料的喉部烧蚀率增大到12.43倍,30g横向过载下,高强石墨材料的喉部烧蚀率增大到20.53倍;在高横向过载下,轴编C/C抗过载烧蚀性能最好,无纬布针刺C/C次之,高强石墨最弱。在高过载和非过载下,喉衬材料的烧蚀性能优劣将发生根本变化,在过载下固体发动机喷管设计过程中应该予以重视。
In order to understand the anti-acceleration erosion(ablation)capability of typical nozzle throat materials in solid rocket motor(SRM),a simulation system of rotating overload test was designed and implemented.Various kinds of experiments were conducted to investigate the anti-acceleration ablation capability of three kinds of throat materials under 20 g and 30 g lateral acceleration.Results show that the erosion thickness of nozzle throat in the acceleration direction is significantly higher than that in the non-acceleration direction,which is defined as throat deviant erosion.Compared with non-acceleration region,a sharp rise in the nozzle throat’s ablation rate is observed in the acceleration region as the lateral acceleration increases.In the case studied in this paper,the nozzle throat’s erosion rate of high strength graphite in the acceleration direction is 12.43 and 20.53 times greater than those in the non-acceleration direction when the lateral acceleration reaches 20 g and 30 g,respectively.Under high lateral acceleration,in-plane C/C composite has a better anti-acceleration ablation capability,following C/C composite using a needled perform and high strength graphite,respectively.Furthermore,the erosion capability of throat materials may has a fundamental change under acceleration and non-acceleration conditions,which should be taken into account during the design of nozzle under high lateral acceleration condition.
作者
王立武
田维平
郭运强
林志远
WANG Li-wu;TIAN Wei-ping;GUO Yun-qiang;LIN Zhi-yuan(Science and Technology on Combustion,Internal Flow and Thermo-Structure Laboratory,Northwestern Polytechnical University,Xi'an 710072,China;Xi’an Institute of Aerospace Propulsion,Xi'an 710025,China;Research Institute of Aerospace Propulsion,Xi'an 710025,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2020年第10期2367-2373,共7页
Journal of Propulsion Technology
关键词
固体火箭发动机
烧蚀
过载
喷管
喉衬材料
Solid rocket motor
Erosion
Acceleration
Nozzle
Throat material
