一种火箭发射场坪流场的环形线汇描述方法  

A Method for Calculating Flow Field of Launch Site by Using the Ring-Sink Model

作　　者：谢建 权辉 谢政 XIE Jian;QUAN Hui;XIE Zheng(Military Key Laboratory for Armament Launch Theory &Technology,Rocket Force University of Engineering,Xi'an 710025,China)

机构地区：[1]火箭军工程大学兵器发射理论与技术军队重点实验室,西安710025

出　　处：《宇航学报》2018年第12期1401-1407,共7页Journal of Astronautics

基　　金：国家自然科学基金(51475462)

摘　　要：针对火箭发射场坪流场分布规律,基于势流法提出环形线汇描述方法,推导了环形线汇流场的速度势和速度的计算公式,建立了流场的FLUENT仿真模型并进行计算,将环形线汇理论计算结果与仿真结果进行对比。结果表明,不同火箭半径和入口流速对环形线汇和FLUENT仿真两种方法计算结果的相关性没有影响,随着箭井间隙增大,两种方法计算结果的相关度减小;环形线汇方法能够描述发射场坪流场变化趋势,在箭井间隙较小且误差允许时可以作为发射场坪流场的简化描述方法。The method using the ring-sink model based on the potential flow method is proposed to research the flow field of a launch site.The formulas for the velocity potential and the velocity in the ring-sink model are derived,and the model simulated by FLUENT is established.The values of the two methods using the formulas and FLUENT are compared. The results show that different rocket radii and inlet velocities have no impacts on the correlations of results from the two methods,which decrease when the space between the rocket and the silo wall increases,and the method using the ring-sink model is capable of describing the trends of the flow field and substituting for the launch site for simplified calculations when the space between the rocket and the silo wall is small and the residuals are acceptable.

关 键 词：发射场坪 势流法 环形线汇 FLUENT 箭井间隙 

分 类 号：V411.8[航空宇航科学与技术—航空宇航推进理论与工程]