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跨速域强地效水平助推滑跑气动机理研究(跨域飞行器关键技术专刊)

王文杰,赵旭,杨龙,李濠君,向粤   

  1. 北京理工大学
  • 收稿日期:2022-11-09 修回日期:2023-01-20 出版日期:2023-02-06 发布日期:2023-02-06
  • 通讯作者: 王文杰
  • 基金资助:
    国家自然科学基金青年基金

Study on aerodynamic mechanism of strong ground effect on horizontal boost run cross velocity domain

  • Received:2022-11-09 Revised:2023-01-20 Online:2023-02-06 Published:2023-02-06
  • Contact: Wenjie WANG

摘要: 火箭橇水平助推滑跑短时间内可实现高超声速,不仅是当前高速地面动态试验的主要手段,更是未来可重复使用单级入轨水平发射的重要依托载体。针对有效载荷与橇车分离时避免出现抬/低头问题、火箭橇测试的传感器布局方案设计等关键问题,基于高精度湍流数值理论与复杂激波系干涉理论,以高超声速标准模型作为有效载荷,开展火箭橇水平助推滑跑系统的气动机理研究。通过对跨速域滑跑时结构内部涡系演化、局部流场特征与系统气动特性分析,揭示不同连接方案对有效载荷的影响机制、结构表面压力分布变化规律等。结果表明:低马赫数时低压区压力脉动呈周期性变化,容易引起气动激励振动;不同马赫数下低压区位置发生明显改变、作用范围随马赫数提高而扩大,尾迹涡相对稳定;改变连接距离和连接高度均使低压区涡的位置发生大幅改变。

关键词: 跨速域, 水平助推滑跑, 内部涡系, 激波干涉, 火箭橇

Abstract: The rocket sled can realize supersonic speed in a short time with horizontal boost sliding, which is not only the main means of current high-speed ground dynamic test, but also an important supporting carrier for the future reusable Single Stage to Orbit (SSTO) for the horizontal launch. Aiming at the key problems such as raising/lowering the head of the payload when it is separating from the sled, and the sensor layout scheme design for rocket sled testing, based on the high-precision turbulent numerical theory and the complex shock wave system interference theory, the hypersonic standard model is used as the payload to carry out the research on the aerodynamic mechanism of the rocket sled horizontal boost sliding system. By analyzing the evolution of vortex system, local flow field characteris-tics and overall aerodynamic characteristics of the structure at sliding speed across the speed domain, the influence mechanism of different connection schemes on the payload and the variation law of the structure surface pressure distribution are revealed. The results show that at low Mach number, the pressure fluctuation in the low pressure region changes periodically, which is easy to cause aerodynamic vibration; At different Mach numbers, the location of the low pressure zone changes obviously and the region expands with high velocity, and the wake vortex is rela-tively stable; Changing the connection distance and connection height can greatly change the vortex position in the low-pressure region.

Key words: Cross speed domain, Horizontal boost sliding, Internal vortex system, Shock wave interference, Rocket sled

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