Study on head configurations increasing aerodynamic rolling stability of ground-based hypersonic testing system

高超声速地面试验系统头部气动滚转增稳构型研究

¹ Norinco Group Testing and Research Institute, Xi'an 710086, China
² School of Aerospace Engineering, Xi'an Jiaotong University, Xi'an 710049, China

Received: 25 December 2023

Abstract

Rocket sled testing is a typical high speed, high dynamic and high credibility ground-based high-speed testing technique, which has the ability to simulate the actual operating conditions. The monorail rocket sled is a better choice of the ground-based hypersonic testing system, as its light-weighted and low drag force characteristics. However, the rolling of the rocket sled caused by the impact load is unavoidable in high-speed situation, and the unstable rolling of the rocket sled would cause the severe damage. To prevent the unstable rolling of the monorail rocket sled, this study firstly studied the flow mechanism causing the static rolling stability of a quasi-hypersonic rocket sled using computational fluid dynamics which is that two unsymmetrical quasi-convergent flow channels were formed and cause the velocity and pressure difference on the two sides of the rocket sled. The restoring rolling moment will be introduced by the pressure difference, which is proportional to the rolling angle causing the static rolling stability. Secondly, two designing concepts were promoted from this flow mechanism to increase the static rolling stability including expanding the operating area of the quasi-convergent flow pipe as well as designing secondary quasi-convergent flow pipe. Finally, two configurations named stability-enhancing rudder and quasi-wing were designed in this paper referring to the above designing concepts. 40% rolling stability incensement was reached by stability-enhancing rudder, while 91% was achieved by quasi-wing.

摘要

火箭橇试验是一种可模拟实际工况地面高速、高动态、高可信度的试验技术, 单轨火箭橇系统具有质量轻、阻力小的特点, 是发展高超声速地面试验系统的优选橇型。但其沿单根滑轨高速滑行时受到冲击而产生滚转的现象不可避免, 若发生滚转失稳将导致火箭橇系统出现严重失效。为防止单轨火箭橇系统发生滚转失稳, 采用计算流体力学方法以类高超声速单轨火箭橇模型为研究对象, 对其两侧空间流场进行研究, 探究影响单轨火箭橇系统滚转静稳定性的流动机理, 发现火箭橇系统发生滚转时, 其头部锥形结构会在两侧形成非对称类收缩流道, 直接影响火箭橇头部两侧流速及静压分布, 产生滚转恢复气动力矩, 且随着滚转角增大, 滚转恢复力矩呈增大趋势, 最终形成单轨火箭橇滚转静稳定性。从滚转增稳流动机理出发, 提出2种局部气动增稳外形设计思想, 包括: ①扩大非对称类收缩流道作用面积实现气动增稳; ②设计二次类收缩流道实现气动增稳。对应这2种外形设计思想分别设计出增稳舵构型和头部类翼构型, 两构型均实现了滚转增稳效果, 其中前者增稳40%, 而后者增稳91%。

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