基于零维内弹道模型的变推力发动机喉栓型面设计与工作特性研究  

Pintle Profile Design Method Based on Zero-Dimensional Interior Ballistic Model and Performance for Variable Thrust Motor

作　　者：邓恒[1] 李志浩 张时空 杨梦洁 李卫鹏 严鸥鹏 DENG Heng;LI Zhi-hao;ZHANG Shi-kong;YANG Meng-jie;LI Wei-peng;YAN Ou-peng(Xi’an Modern Control Technology Research Institute,Xi’an 710065,China;College of Astronautics,Northwesten Polytecnical University,Xi’an 710072,China)

机构地区：[1]西安现代控制技术研究所,陕西西安710065 [2]西北工业大学航天学院,陕西西安710072

出　　处：《推进技术》2022年第11期34-43,共10页Journal of Propulsion Technology

摘　　要：为简化内弹道性能与喉栓行程的关系,提高变推力发动机喉栓型面的设计能力,基于零维内弹道模型,提出了喉栓型面位置修正设计方法,使用该方法可以根据预设内弹道调节规律开展喉栓型面设计。以推力随喉栓行程线性变化为例完成了喉栓型面的设计,分析了主要变量偏差对推力的影响,结合数值模拟和地面试验验证了喉栓型面设计方法的正确性和设计构型的推力线性调节规律,研究了喉栓设计构型的动态调节特性。结果表明,设计构型喉栓在稳态条件下具备较好的推力-喉栓行程线性关系,在动态调节过程中,喉栓正向运动时推力过冲小于2%,反向运动时推力过冲可较锥形喉栓降低65%以上。To simplify the relation between interior ballistic performance and pintle position,and improve the design ability of variable thrust motor pintle profile,a pintle profile design method based on 0-dimensional internal ballistic model was proposed,which could be used to design pintle profile according to preset internal ballistic regulation.A pintle profile was designed to meet the requirement of thrust varying linearly with pintle position.The influence of deviation of main variables on thrust was analyzed.The correctness of design method and the linear regulation of thrust were verified using numerical simulation and ground test.The influence of main parameters on thrust and transient thrust variation characteristics of designed profile were studied.Results show that thrust varies linearly with pintle position while the designed profile working in steady-state conditions.In transient conditions,the thrust overshoot of the designed profile in forward motion is less than 2%,and the thrust overshoot in reverse motion is more than 65% lower than that of the conical profile.

关 键 词：变推力发动机 喉栓 型面设计 内弹道性能 动态调节特性 

分 类 号：V435.3[航空宇航科学与技术—航空宇航推进理论与工程]