摘要
添加降速剂和调节RDX/AP含量是调节NEPE推进剂燃速的两种常用途径。采用水下声发射燃速测试仪、密闭燃烧器、BSFϕ75 mm发动机等测试方法,研究了低燃速NEPE推进剂静态高压燃烧性能规律和发动机动态高压燃烧稳定性。研究发现,NEPE推进剂的中低压区燃速随着降速剂含量增大而显著降低,高压区燃速降低幅度相对较小,燃速⁃压强(r⁃p)曲线在15 MPa和45 MPa出现两个拐点,而且降低RDX含量对降低高压段燃速作用显著。BSFϕ75 mm发动机试车结果表明,低RDX含量的C1配方(28%)最大工作压强不超过20 MPa,而高RDX含量(38%)的C4配方最大工作压强达到30 MPa。发动机稳定燃烧的最大压强随NEPE推进剂的燃速降低而下降,主要原因是低燃速推进剂铝粉燃烧效率降低使凝聚相燃烧产物含量和粒度增大。
Adding burning rate inhibitor and adjusting RDX/AP content are usually used to adjust the burning rate of NEPE propellant.The high pressure combustion performance of low burning rate NEPE propellant and high pressure combustion stability of the solid rocket motor(SRM)were investigated by means of underwater acoustic emission combustion rate tester,sealed burner and BSFϕ75 mm motor.The results show that the burning⁃rate in middle and low pressure range decrease greatly with the increase of the content of burning rate inhibitor,while the burning rate in the high pressure zone decreased slightly.Moreover,there are two inflec⁃tion points near 15 MPa and 45 MPa on the r⁃p curve.Moreover,the burning rate in the high pressure zone decrease significantly with the decrease of RDX content.The results of BSFϕ75 mm motor show that the C1 formula with a low RDX content(28%)has a maximum working pressure of 20 MPa,while the C4 formula with a high RDX content(38%)has a maximum working pressure of 30 MPa.The maximum pressure of stable combustion decrease with the decrease of the burning rate of NEPE propellant,which is mainly due to the decreased of aluminum powder combustion efficiency in low burning rate propellant and the increased content and particle size of condensed combustion products.
作者
唐泉
鲁锐华
王小英
杨品高
曹满山
尹欣梅
TANG Quan;LU Ruihua;WANG Xiaoyin;YANG Pingao;CAO Manshan;YIN Xinmei(Science and Technology on Aerospace Chemical Power Laboratory,Xiangyang 441003,China;Hubei Institute of Aerospace Chemical-Technology,Xiangyang 441003,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2021年第4期461-465,共5页
Journal of Solid Rocket Technology
基金
装备预研领域重点基金。
关键词
低燃速
高压燃烧性能
降速剂
NEPE推进剂
low burning rate
high pressure combustion performance
burning⁃rate inhibitor
NEPE propellant
