固体火箭发动机特性对空射滑翔式弹道飞行器性能影响分析  

Analysis of the influence of solid rocket motor characteristics to air-launched glide ballistic vehicle performance

作　　者：余家泉 张程[1] 袁亚 黄慧慧 YU Jiaquan;ZHANG Cheng;YUAN Ya;HUANG Huihui(China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《火箭推进》2022年第1期61-68,共8页Journal of Rocket Propulsion

基　　金：高校联合创新基金(CALT20190103)。

摘　　要：为研究空射滑翔式弹道飞行器固体火箭发动机特性对飞行器综合性能的影响,构建了基于序列二次优化法(SQP)的弹道优化模型,设计了多套不同推力形式、不同特性参数的固体火箭发动机方案。通过开展空射滑翔式弹道飞行器弹道仿真分析,获取了不同动力特性下的最优爬升攻角变化规律,对比分析了相关弹道特征指标。结果表明:采用长时间-小推力的推力形式,能够增加飞行器弹道顶点速度和射程能力;采用多脉冲或单室-双推力的推力形式,能够减小飞行器飞行动压,对降低飞行器承载及防热结构质量十分有利。In order to investigate the effects of solid rocket motor(SRM)characteristics to the comprehensive performance of the air-launched glide ballistic vehicle,a ballistic optimization model based on sequential quadratic programming(SQP)method was constructed,and several SRM schemes with different thrust types and different parameters were designed.By the ballistic simulation analysis of air-launched glide ballistic vehicle,the optimum climbing attack angle variation laws under different SRM characteristics were obtained,and the key ballistic indicators were contrasted.It is found that vehicle has larger ballistic apex velocity and longer range with the thrust mode of long time-low thrust;and the max flight dynamic pressure is lower with dual-pulse or single-chamber double-thrust thrust type,which is beneficial to reduce the weight of load bearing structure and thermal protection structure.

关 键 词：空中发射 滑翔式弹道飞行器 序列二次优化法 固体火箭发动机 推力形式 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]