火箭推进

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.

引言
1 空射滑翔式弹道飞行器弹道优化方法
2 固体火箭发动机推力特性影响分析
3 结论

图1 典型飞行剖面图
Fig.1 Typical flight profile

图2 典型固体发动机推力形式<br/>Fig.2 Typical thrust types of solid rocket motor

图2 典型固体发动机推力形式
Fig.2 Typical thrust types of solid rocket motor

表1 单推力方案参数<br/>Tab.1 Parameters of single thrust schemes

表1 单推力方案参数
Tab.1 Parameters of single thrust schemes

图3 单推力方案攻角-时间曲线<br/>Fig.3 Angle of attack-time curve of single thrust schemes

图3 单推力方案攻角-时间曲线
Fig.3 Angle of attack-time curve of single thrust schemes

表2 弹道关键参数对比(单推力方案)<br/>Tab.2 Comparison of ballistic key parameters(single thrust schemes)

表2 弹道关键参数对比(单推力方案)
Tab.2 Comparison of ballistic key parameters(single thrust schemes)

图4 单推力方案速度-时间曲线<br/>Fig.4 Velocity-time curve of single thrust schemes

图4 单推力方案速度-时间曲线
Fig.4 Velocity-time curve of single thrust schemes

图5 单推力方案射程-高度曲线<br/>Fig.5 Range-altitude curve of single thrust schemes

图5 单推力方案射程-高度曲线
Fig.5 Range-altitude curve of single thrust schemes

表3 双脉冲方案参数<br/>Tab.3 Parameters of dual-pulse thrust schemes

表3 双脉冲方案参数
Tab.3 Parameters of dual-pulse thrust schemes

图6 双脉冲方案攻角-时间曲线<br/>Fig.6 Angle of attack-time curve of dual-pulse thrust schemes

图6 双脉冲方案攻角-时间曲线
Fig.6 Angle of attack-time curve of dual-pulse thrust schemes

表4 弹道关键参数对比(双脉冲方案)<br/>Tab.4 Comparison of ballistic key parameters(dual-pulse thrust schemes)

表4 弹道关键参数对比(双脉冲方案)
Tab.4 Comparison of ballistic key parameters(dual-pulse thrust schemes)

图7 双脉冲方案速度-时间曲线<br/>Fig.7 Velocity-time curve of dual-pulse thrust schemes

图7 双脉冲方案速度-时间曲线
Fig.7 Velocity-time curve of dual-pulse thrust schemes

图8 双脉冲方案射程-高度曲线<br/>Fig.8 Range-altitude curve of dual-pulse thrust schemes

图8 双脉冲方案射程-高度曲线
Fig.8 Range-altitude curve of dual-pulse thrust schemes

图9 双脉冲方案动压-时间曲线<br/>Fig.9 Dynamic pressure-time curve of dual-pulse thrust schemes

图9 双脉冲方案动压-时间曲线
Fig.9 Dynamic pressure-time curve of dual-pulse thrust schemes

表5 单室双推力方案参数<br/>Tab.5 Parameters of single-chamber double-thrust schemes

表5 单室双推力方案参数
Tab.5 Parameters of single-chamber double-thrust schemes

图10 单室-双推方案攻角-时间曲线<br/>Fig.10 Angle of attack-time curve of single-chamber double-thrust schemes

图10 单室-双推方案攻角-时间曲线
Fig.10 Angle of attack-time curve of single-chamber double-thrust schemes

表6 弹道关键参数对比(单室-双推方案)<br/>Tab.6 Comparison of ballistic key parameters(single-chamber double-thrust schemes)

表6 弹道关键参数对比(单室-双推方案)
Tab.6 Comparison of ballistic key parameters(single-chamber double-thrust schemes)

图11 单室-双推方案速度-时间曲线<br/>Fig.11 Velocity-time curve of single-chamber double-thrust schemes

图11 单室-双推方案速度-时间曲线
Fig.11 Velocity-time curve of single-chamber double-thrust schemes

图12 单室-双推方案射程-高度曲线<br/>Fig.12 Range-altitude curve of single-chamber double-thrust schemes

图12 单室-双推方案射程-高度曲线
Fig.12 Range-altitude curve of single-chamber double-thrust schemes

图13 单室-双推方案动压-时间曲线<br/>Fig.13 Dynamic pressure-time curve of single-chamber double-thrust schemes

图13 单室-双推方案动压-时间曲线
Fig.13 Dynamic pressure-time curve of single-chamber double-thrust schemes

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备注

引言

1 空射滑翔式弹道飞行器弹道优化方法

2 固体火箭发动机推力特性影响分析

3 结论

期刊信息