摘要
为降低传统大扩张比喷管在低空飞行时喷管内燃气过膨胀带来的推力损失,提出一种具有自适应高度补偿功能的可渗透壁喷管。对采用不同壁面开孔方式的可渗透喷管进行数值模拟,对比并分析喷管的全弹道推力性能。计算结果显示,可渗透喷管在低空下的推力补偿效果明显,比冲增益最高达10%,在高空下的推力损失低至1%,高度平均比冲增益最高达1.5%。在孔隙率、壁面开孔形状相同的情况下,壁面开孔尺度越小可渗透喷管的推力性能越好,但总体上不同壁面开孔尺度的可渗透喷管的全弹道性能差异为0.6%。产生性能差异的主要原因是相同孔隙率的情况下,低空通过小尺度孔进入喷管的气流更均匀,对可渗透段内壁面压强的提升以及分离激波的削弱效果更好,因此带来的低空推力补偿效果更好。在孔隙率、壁面开孔尺度相同的情况下,采用圆柱孔的可渗透喷管的推力性能要优于圆锥孔的可渗透喷管。综合性能最好的圆柱孔可渗透喷管与综合性能较差的渐缩型圆锥孔可渗透喷管的全弹道性能相差约3.3%。
In order to reduce the thrust loss caused by overexpansion of gas in conventional nozzle with large expansion ratio at low altitude,a permeable wall nozzle with adaptive altitude-compensating is proposed.The permeable nozzles with different wall perforated method are numerically simulated.The full ballistic thrust performance of nozzle is compared and analyzed.The calculation results are as follows.The thrust compensation effect of the permeable nozzle at low altitude is obvious,the specific impulse gain is up to 10%,and the thrust loss at high altitude is as low as 1%.The overall performance is significantly improved,and the height average specific impulse is improved by up to 1.5%.When the porosity and the wall perforated shapes are the same,the thrust performance of the permeable nozzle with smaller hole diameter is better.But in general,the difference of total ballistic performance of permeable nozzles with various hole diameters is 0.6%.The main reason for the per⁃formance difference is that with the same porosity,the smaller the hole diameter,the more the number of perfo⁃rated hole and the more uniform the perforated hole distribution.At low altitude,the air flow into the nozzle through the permeable section is more uniform.The effect of increasing the wall pressure in permeable section and weakening the separation shock wave is better.Therefore,the low altitude thrust compensating effect is bet⁃ter.When the porosity and the hole diameter are the same,the thrust performance of the permeable nozzle with cylindrical holes is better than that of the permeable nozzle with conical holes.The difference in total ballistic per⁃formance between the permeable nozzle with cylindrical holes and the permeable nozzle with convergent conical holes is about 3.3%.
作者
王革
李程珂
薛玉琴
宋振
关奔
杨泽南
WANG Ge;LI Chengke;XUE Yuqin;SONG Zhen;GUAN Ben;YANG Zenan(College of Aerospace and Civil Engineering,Harbin Engineering University,Harbin 150001,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2024年第10期75-85,共11页
Journal of Propulsion Technology
基金
中央高校基本科研业务费专项资金(3072022CFJ0203)
国家自然科学基金青年基金(12002102)。
关键词
固体火箭发动机
高度补偿喷管
内弹道
可渗透喷管
数值计算
Solid rocket motor
Altitude-compensating nozzle
Interior ballistics
Permeable nozzle
Numerical calculation
