旋转飞行器固体火箭发动机内涡核流动的数值分析

推进技术 ›› 2011, Vol. 32 ›› Issue (1): 86-90.

旋转飞行器固体火箭发动机内涡核流动的数值分析

郜冶,刘平安,杨丹

哈尔滨工程大学航天工程系,黑龙江哈尔滨 150001;哈尔滨工程大学航天工程系,黑龙江哈尔滨 150001;哈尔滨工程大学航天工程系,黑龙江哈尔滨 150001

发布日期:2021-08-15
作者简介:郜冶(1953—),男,博士,教授,研究领域为固体火箭发动机内流场数值仿真。E-mail:gaoye66@126.com
基金资助:
国家自然科学基金(10972063)；中央高校基本科研业务基金(HEUCF100203)。

Numerical analysis of vortex core flow in spinning solid rocket motor

Dept. of Aerospace Engineering, Harbin Engineering Univ.,Harbin 150001,China;Dept. of Aerospace Engineering, Harbin Engineering Univ.,Harbin 150001,China;Dept. of Aerospace Engineering, Harbin Engineering Univ.,Harbin 150001,China

Published:2021-08-15

摘要/Abstract

摘要： 为分析旋转飞行器固体火箭发动机内涡核流动,采用数值计算的方法对发动机流场进行模拟。计算结果显示发动机的旋转增强了轴向涡核流动,随着涡核的不断延伸,在喷管入口处,由于潜入式喷管结构以及喷喉直径较小,振荡运动随之加强。涡核在流经喷管时的不断增强,在喷管区域形成了非对称的压力形式,并且产生了实际中的扰动侧向力,最终导致了飞行器的章动不稳定性。

关键词: 旋转固体发动机;涡核流动;扰动侧向力;章动不稳定性

Abstract: The method of numerial calculation was adopted to simulate the flow field of solid rocket motor in order to analyse the vortex core flow in spinning solid rocket motor. The calculation results show that the spining of solid rocket motor enhanced the axial vortex core flow.When the vortex core extends to inlet of nozzle,its oscillatory motion enhanced. The vortex core constantly strengthens and forms asymmetric pressure distribution when flowing through nozzle,so the actual lateral disturbance force produces and finally leads to coning instability of aircraft.

Key words: Spinning solid rocket motor; Vortex core flow; Lateral disturbance force; Coning instability

郜冶,刘平安,杨丹. 旋转飞行器固体火箭发动机内涡核流动的数值分析[J]. 推进技术, 2011, 32(1): 86-90.