三扰流片推力矢量固体火箭发动机推力调节特性研究  

Thrust control characteristics of solid rocket motor with three jet tabs

作　　者：张汝衡 杨军 姚保江 杨石林 张兵峰 ZHANG Ruheng;YANG Jun;YAO Baojiang;YANG Shilin;ZHANG Bingfeng(The 41st Institute of the Fourth Academy of CASC,Xi'an 710025,China;The Fourth Academy of CASC,Xi'an 710025,China)

机构地区：[1]中国航天科技集团有限公司四院四十一所,西安710025 [2]中国航天科技集团有限公司第四研究院,西安710025

出　　处：《固体火箭技术》2023年第5期663-672,共10页Journal of Solid Rocket Technology

摘　　要：为研究三扰流片推力矢量发动机进行推力调节时的矢量特性,采用重叠网格技术对三扰流片推力矢量装置展开数值模拟;将数值结果采用RBF(Radial Basis Function Neural Network)神经网络方法进行拟合,提出了一种依据舵机位移计算主推力和侧向力的推力矢量计算方法;最后,进行了原理样机推力开环试验。数值研究结果表明,舵机位移在12.5 mm以内时,发动机主推力曲线台阶变化明显;舵机位移为10.5 mm时,喷管尾部流场内开始出现斜激波交会形成马赫盘,马赫盘前移逐渐贴附于喷管口的现象。从拟合得到的侧向力计算式可以看出,三扰流片组合差动受到的侧向力,以及喷管内流动不对称产生的喷管内侧向力均为驱动扰流片旋转的舵机位移的函数。点火试验结果表明,拟合计算得到的发动机主推力和侧向力与试验实测值之间的偏差在4%以内,验证了所提出的推力矢量计算方法的正确性。In order to research the thrust vector characteristics of SRM with three jet tabs,the jet tab thrust vector device was numerically simulated by using overlapping mesh technology.The numerical results were fitted by RBF neural network method,and a thrust vector calculation method was proposed to calculate the main thrust and lateral force according to the displacement of steering gear.Finally,the open-loop thrust test of the prototype was carried out.The numerical results show that when the displacement of the steering gear is less than 12.5 mm,the steps of the motor's main thrust curve change obviously;when the displacement of steering gear is 10.5 mm,the Mach disk is formed by oblique shock wave intersection in the flow field at the nozzle tail,and the Mach disk moves forward and gradually attaches to the nozzle exit.It can be seen from the fitting formula that the lateral force caused by the differential combination of the jet tab and the inner nozzle force caused by the asymmetric flow in the nozzle are both functions of the displacement of the steering gear driving the tab rotation.The firing test results show that the deviation between the main thrust and lateral force calculated by fitting and the measured values is within 4%,which verifies the correctness of the thrust vector calculation method proposed in this paper.

关 键 词：扰流片 推力矢量 差动 数值模拟 神经网络 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]