[author_cn_name].[cn_title][J].空军工程大学学报:自然科学版,[year_id],[volume]([issue]):[start_page]-[end_page] 下挂式空射系统机箭分离阶段离散阵风响应分析-Response Analysis of Discrete Gust of Hanging Type Air Launch System on Separation Phase
文章摘要
舒杰,张登成,张艳华,张久星.下挂式空射系统机箭分离阶段离散阵风响应分析[J].空军工程大学学报:自然科学版,2018,19(4):43-47
下挂式空射系统机箭分离阶段离散阵风响应分析
Response Analysis of Discrete Gust of Hanging Type Air Launch System on Separation Phase
  
DOI:10.3969/j.issn.1009-3516.2018.04.008
中文关键词: 下挂式空射火箭  机箭分离  离散阵风  网格速度
英文关键词: hanging type air launch vehicle  separation of carrier and rocket  discrete gust  grid velocity method
基金项目:国家自然科学基金(61374145)
作者单位
舒杰,张登成,张艳华,张久星 1.空军工程大学航空工程学院,西安,7100382.93756部队,天津,300130 
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中文摘要:
      下挂式空射系统机箭分离阶段运载火箭处于动力飞行阶段,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,并与阵风条件下机箭分离气动特性进行了对比分析,结果表明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。
英文摘要:
      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 destroyed after encountering discrete gust and may cause launch to fail, raising a higher requirement for the design of the control rate.
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