探空火箭减阻杆气动特性分析  

Analysis of Aerodynamic Characteristics Using Spikes of Sounding Rocket

作　　者：常耀予 刘帆 张家齐 Chang Yaoyu;Liu Fan;Zhang Jiaqi(Onespace Technology Group Co.,Ltd.,Beijing 100176,China)

机构地区：[1]重庆零壹空间航天科技有限公司,北京100176

出　　处：《航空科学技术》2020年第11期83-88,共6页Aeronautical Science & Technology

摘　　要：为了研究减阻杆对探空火箭气动力特性,通过采用SST两方程湍流模型、有限体积法求解N-S方程,对探空火箭高速流场进行数值模拟。计算结果显示,减阻杆能有效减小火箭阻力。亚跨声速(Ma0.8~1.2)最大减阻25%;高超声速(≥Ma6)阶段,最大减阻量35%,减阻效果随迎角增大而降低,到12°迎角时减阻量为12%。压跨声速及高超声速全箭升阻比增量随马赫数增大均增加,高超声速阶段升阻比增大18%。同时采用工程方法结合数值预示结果,评估减阻杆带来的气动热影响,结果显示,气动支杆的存在使得端头的平均热流密度下降了51%,并与飞行试验结果进行对比分析。计算得到热流结果与飞行实测热流结果相当,热环境预示比较准确,对于高超声速阶段的飞行器被动热防护技术研究具有良好的指导价值。In order to study the aerodynamic of sounding rocket with drag-reduction spike,the Navier-Stokes equations are solved by finite volume method based on the k-ωSST turbulent flow model.On this basis,the flow field of the hypersonic projectile is simulated.The calculation results show that the spike can effectively reduce the drag of sounding rocket.The study shows the maximum drag reduction of sub-sonic speed is 25%,and the maximum drag reduction of hypersonic phase is 35%.The drag reduction effect decreases with the increase of the angle of attack,and the drag reduction amount is 12%when the angle of attack is 12 degrees.The calculation results show there is a positive correlation between drag ratio and Mach number.Specifically,the drag ratio increases by 18%in hypersonic phase.At the same time,the engineering method is used to evaluate the aerothermal effect by the drag reduction spike,and compared with the flight test results.The theoretical value of heat flow is equivalent to the measured value of heat flow in the flight test,and the thermal circumstance prediction is comparatively accurate.

关 键 词：减阻杆 气动热 气动力 高超声速 探空火箭 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]