摘要
下挂式空射系统机箭分离阶段运载火箭处于无动力飞行阶段,高空阵风会对其运动轨迹产生较严重的干扰。为研究下挂式空中发射运载火箭机箭分离阶段系统的离散阵风响应,引入"网格速度"思想来计入阵风的影响,采用有限体积法求解非定常Euler和N-S方程,对机箭分离过程进行了动网格仿真分析。通过模块化方式搭建了机箭系统离散阵风响应仿真平台,平台由火箭状态及网格更新模块、力与力矩CFD解算模块、飞行状态参数求解模块和离散阵风干扰模块组成。仿真计算了机箭系统穿越1-cos离散阵风区的动态响应,并与无阵风条件下机箭分离气动特性进行了对比分析,结果表明无阵风条件下机箭分离后机箭系统可以较好地满足火箭的点火要求;在遭遇离散阵风后,机箭系统稳定性被破坏,可能导致发射失败,这对于机箭系统的控制率设计提出了更高的要求。
The rocket is in unpowered flight at the separation phase of missile and rocket of air launch system and the trajectory is prone to interference from the upper level gust.In order to research the responses of discrete gust of air launch system at separation phase,the influence of gust is simulated by using the grid velocity method,the finite volume method is used to solve unsteady Euler and N-S equation,and the separation process is calculated by using CFD dynamic grid.The simulation platform is built by the modular method,including update module of rocket＇s status and grid,CFD calculation module of force and moment,solution of flight status parameters and discrete gust interference module.The separation process under 1-cos gust disturbance is calculated by using the simulation platform,and the aerodynamic characteristics of the rocket and the carrier with or without gust disturbance are compared and analyzed.The results show that the air launch system can satisfy the requirement of rocket ignition after the separation of missile and rocket in the absence of gusts.After a discrete gust of wind,stability of the air launch system is de-stroyed after encountering discrete gust and may cause launch to fail,raising a higher requirement for the design of the control rate.
作者
舒杰
张登成
张艳华
张久星
SHU Jie;ZHANG Dengcheng;ZHANG Yanhua;ZHANG Jiuxing(Aeronautics Engineering College,Air Force Engineering University,Xi＇an 710038,China;Unit 93756,Tianjin 300130,China)
出处
《空军工程大学学报（自然科学版）》
CSCD
北大核心
2018年第4期43-47,53,共6页
Journal of Air Force Engineering University(Natural Science Edition)
基金
国家自然科学基金(61374145)
关键词
下挂式空射火箭
机箭分离
离散阵风
网格速度
hanging type air launch vehicle
separation of carrier and rocket
discrete gust
gridvelocity method
