基于喷管二次流控制的推力矢量特性研究  

Research on thrust vector characteristics based on nozzle secondary flow control

作　　者：陈家兴 姬永超 白云 王刚 武锐 展杰 赵猛 CHEN Jiaxing;JI Yongchao;BAI Yun;WANG Gang;WU Rui;ZHAN Jie;ZHAO Meng(Inner Mongolia Institute of Dynamical Machinery,Hohhot 010010,China;College of Science,Inner Mongolia University of Technology,Hohhot 010051,China;The Second Military Representative Office of the Army Equipment Department in Baotou District,Baotou 014033,China)

机构地区：[1]内蒙动力机械研究所,呼和浩特010010 [2]内蒙古工业大学理学院,呼和浩特010051 [3]陆军装备部驻包头地区第二军事代表室,包头014033

出　　处：《固体火箭技术》2024年第3期321-330,共10页Journal of Solid Rocket Technology

摘　　要：通过控制二次流喷口相对位置和宽度来改变喷管出口燃气流动方向是实现推力矢量控制的方法之一。为掌握落压比(NPR)、二次流压比(SPR)以及二次流喷口相对位置(X_(j))和宽度(d)对推力矢量性能的影响,通过数值计算分析了发动机推力矢量角(δ)、推力系数(C_(f))变化规律。结果表明,随着落压比的减小,喷管可以获得更大的推力矢量角度,但推力损失更大;主流落压比不同时,喷管推力矢量效率的最小值所对应的二次流压比不同;随着二次流喷口宽度的增加,喷管的推力矢量角度逐渐增大且随着二次流压比的增大其增幅也随之变大;推力矢量效率在SPR≤0.6时,随着二次流喷口宽度的增大而减小;SPR=0.8后随着二次流喷口宽度的增大先下降后上升,SPR=1.2时随着二次流喷口宽度的增大而增大;随着二次流喷口位置向喷管出口的移动,推力矢量角仅在喷口后的气流分离由闭式变为开式时发生一次突增,而推力系数发生一次突减;随着二次流喷射角度的增大,喷管的推力矢量角度不断增大,喷管的推力系数呈现不断减小的趋势。Changing the nozzle exit gas flow direction by controlling the relative position and circumferential opening of the secondary flow orifice is one of the methods to realize the thrust vector control.In order to understand the influence of the drop pressure ratio(NPR),secondary flow pressure ratio(SPR),and the relative position(X_j) and circumferential opening(d) of the secondary flow orifice on the thrust vectoring performance,the changes of the motor thrust vector angle(δ) and thrust coefficient(C_f) with the above-mentioned aerodynamic parameters and nozzle geometry parameters were analyzed by numerical calculation.The results show that:with the reduction of the drop pressure ratio,the nozzle can obtain a larger thrust vector angle,but the thrust loss is greater;for different mainstream drop pressure ratio,the minimum value of the nozzle thrust vector efficiency corresponds to different secondary flow pressure ratio;with the increase of the secondary flow orifice circumferential opening,the nozzle thrust vector angle gradually increases,and with the increase of the secondary flow pressure ratio,the amount of increase becomes larger;when SPR≤0.6,with increase of the secondary flow orifice circumferential opening,thrust vector efficiency decreases;when SPR=0.8,with increase in the of the secondary flow orifice circumferential opening,the thrust vector efficiency first decreases and then increases;when SPR=1.2,with increase of the secondary flow orifice circumferential opening,the thrust vector efficiency increases;with the movement of secondary flow orifice position to the nozzle outlet,the sudden increase of thrust vector angle only occurs once after the orifice airflow separation from closed one to open one,and the thrust coefficient sudden decrease;with increase of the secondary flow injection angle,the nozzle thrust vector angle increases gradually,the nozzle thrust coefficient shows a trend of continuous reduction.

关 键 词：喷管 推力矢量控制 二次流喷口位置 二次流喷口宽度 推力矢量角度 推力系数 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]