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[1]梁俊龙,张贵田,秦艳平.基于高阶WENO格式的喷管动态特性仿真分析[J].火箭推进,2015,41(04):29-36.
　LIANG Junlong,ZHANG Guitian,QIN Yanping.Simulated analysis on nozzle dynamic characteristics based on high-order WENO scheme[J].Journal of Rocket Propulsion,2015,41(04):29-36.
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基于高阶WENO格式的喷管动态特性仿真分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 41 期数: 2015年04期 页码: 29-36 栏目: 研究与设计 出版日期: 2015-09-30
Title:
Simulated analysis on nozzle dynamic characteristics based on high-order WENO scheme
作者:
梁俊龙1; 张贵田1; 秦艳平2
1. 西北工业大学 燃烧、热结构与内流场重点实验室，陕西 西安 710072； 2. 西安航天动力研究所，陕西 西安 710100
Author(s):
LIANG Junlong1;  ZHANG Guitian1;  QIN Yanping2
1. State Key Laboratory of Combustion, Thermal Structure and Inner Flow Field, Northwestern Polytechnical University, Xi’an 710072, China; 2. Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
关键词:
喷管; 高阶有限体积法;  WENO格式; 动态特性; 激波探测
Keywords:
nozzle;  high-order finite volume method;  WENO scheme;  dynamic characteristic;  shock wave detection
分类号:
V434-34
文献标志码:
A
摘要:
喷管的动态特性分析是进行高品质控制系统设计、控制参数优化、控制规律验证的基础。为了分析喷管的动态特性，针对轴对称收扩喷管，基于一维变截面非稳态无粘流动控制方程，利用有限体积Roe类型的高精度WENO格式对控制方程进行离散，采用三阶强稳定型龙格库塔方法进行时间方向的积分，利用激波探测函数实时捕获激波位置，建立了喷管的一维动态特性仿真程序。通过与理论解析解的对比验证了仿真程序和激波探测函数的正确性。在欠膨胀状态下，获得了喷管入口总压、总温扰动下，喷管进出口压力和推力的阶跃响应特性，对比分析了各扰动因素对推力响应特性的影响。进一步分析了扩张段存在激波的情况下，在不同的扰动下激波运动和推力等参数的变化规律，能够为推力控制系统分析提供参考。
Abstract:
Dynamic characteristic analysis of the nozzle is a foundation to conduct the high-quality controller design, parameter optimization and control law verification. To investigate the dynamic characteristics, the finite volume Roe type high-accuracy weighted essentially non-oscillatory (WENO) scheme combined with shock wave detection function is adopted to accurately capture the shock wave location and establish the simulation program of one-dimensional dynamic characteristics for the nozzle based on the one- equations. The correctness of simulation program and shock wave detection function was verified by contrast of the theoretical analytical solution. Under disturbances from inlet total temperature and total pressure, the step response features of thrust and pressure at inlet/outlet of the nozzle were obtained, and the effect of each disturbance factor on the thrust response characteristics was analyzed. Furthermore, the change rule of the shock wave motion and the thrust is analyzed when the shock wave exits at the divergent section, which is valuable to design the thrust controller.

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更新日期/Last Update: 1900-01-01