旋转飞行器固体火箭发动机内涡核流动的数值分析

Numerical analysis of vortex core flow in spinning solid rocket motor

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。

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.