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尕永婧, 王浩苏, 张青松, 徐珊姝, 吴义田. 垂直着陆过程推进剂流动行为特性及影响分析[J]. 深空探测学报(中英文), 2021, 8(1): 42-50. DOI: 10.15982/j.issn.2096-9287.2021.20200012
引用本文: 尕永婧, 王浩苏, 张青松, 徐珊姝, 吴义田. 垂直着陆过程推进剂流动行为特性及影响分析[J]. 深空探测学报(中英文), 2021, 8(1): 42-50. DOI: 10.15982/j.issn.2096-9287.2021.20200012
GA Yongjing, WANG Haosu, ZHANG Qingsong, XU Shanshu, WU Yitian. Propellant Flow Characteristics in Tank and Related Impact Analysis During the Vertical Landing Stage[J]. Journal of Deep Space Exploration, 2021, 8(1): 42-50. DOI: 10.15982/j.issn.2096-9287.2021.20200012
Citation: GA Yongjing, WANG Haosu, ZHANG Qingsong, XU Shanshu, WU Yitian. Propellant Flow Characteristics in Tank and Related Impact Analysis During the Vertical Landing Stage[J]. Journal of Deep Space Exploration, 2021, 8(1): 42-50. DOI: 10.15982/j.issn.2096-9287.2021.20200012

垂直着陆过程推进剂流动行为特性及影响分析

Propellant Flow Characteristics in Tank and Related Impact Analysis During the Vertical Landing Stage

  • 摘要: 可回收技术是实现运载火箭可重复使用的关键技术之一,采用垂直着陆的方式实现子级回收是当前研究的热点和难点,而运载火箭在起飞和垂直着陆过程中,对贮箱内推进剂的管理有较高的要求。首先调研分析了运载火箭回收技术的国内外研究现状及趋势,然后采用Flow 3D数值模拟的方法,研究了运载器垂直着陆过程中,贮箱内推进剂的流动行为特性;并对部分发动机在关机时刻的横向过载与轴向过载变化对箱内推进剂流体行为特性的影响进行了研究分析。结果表明:轴向过载变化一定的情况下,箱内推进剂的晃动幅值与横向干扰幅值相关,并且在部分发动机关机或其他轴向力突然减小的情况下,推进剂晃幅会被大幅放大,建议运载器在垂直起降过程中尽量保证飞行姿态,避免出现大幅横向干扰。

     

    Abstract: Reusable technology is one of the key factors to realize the launch vehicle reusability. It is a hot spot in current research to achieve the sub-stage reusability by vertical landing. During the process of launch vehicle taking-off and vertical landing, the propulsion system is not only required to provide thrust in the ascent, but also to realize the smooth deceleration and control of vertical landing. It is required that the rocket engine shall be improved to possess multiple-start and in-depth thrust regulating capability and also have higher requirements to propellant management. During the vertical landing process, the propellant flow characteristics in tank are greatly affected by the acceleration of the vehicle. If there are some lateral disturbance, the propellant in the tank will move violently due to severe acceleration decrease and may affect the normal operation of the rocket engine. In this paper, the propellant flow behavior during the vertical landing process is investigated with Flow 3D numerical simulation, and the influence of the lateral and axial acceleration on the propellant flow behavior during the engine shutdown process is analyzed. The results show that the sloshing amplitude of the propellant is related to the amplitude of the lateral disturbance when the axial acceleration changes to a certain extent, and the sloshing amplitude of the propellant will be greatly enlarged when axial forces suddenly decrease. It is suggested that in the process of vertical taking-off and landing, the attitude of vehicle should be guaranteed as much as possible to avoid large lateral disturbance.

     

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