航天推进技术研究院主办
[1]刘亚洲,曹晨,胡海峰,等.双钟形喷管在分离工作阶段的吸气阻力分析[J].火箭推进,2024,50(02):88-97.[doi:10.3969/j.issn.1672-9374.2024.02.009]
LIU Yazhou,CAO Chen,HU Haifeng,et al.Analysis of the aspiration drag in dual-bell nozzles during separation operating mode[J].Journal of Rocket Propulsion,2024,50(02):88-97.[doi:10.3969/j.issn.1672-9374.2024.02.009]
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LIU Yazhou,CAO Chen,HU Haifeng,et al.Analysis of the aspiration drag in dual-bell nozzles during separation operating mode[J].Journal of Rocket Propulsion,2024,50(02):88-97.[doi:10.3969/j.issn.1672-9374.2024.02.009]
双钟形喷管在分离工作阶段的吸气阻力分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
50
期数:
2024年02期
页码:
88-97
栏目:
目次
出版日期:
2024-05-30
- Title:
- Analysis of the aspiration drag in dual-bell nozzles during separation operating mode
- 文章编号:
- 1672-9374202402-0088-10
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 在低空工作阶段产生于回流区的吸气阻力对双钟形喷管的性能具有不可忽视的影响。采用仿真手段对不同设计参数的双钟形喷管的吸气阻力进行了研究,获得了其在不同飞行高度下的阻力系数。研究结果表明,吸气阻力并不总是如已有文献认为的随飞行高度的增加而不断减小。延伸段顺压梯度分布的双钟形喷管的吸气阻力随飞行高度的增加不断减小; 延伸段等压或逆压梯度分布的双钟形喷管的吸气阻力随飞行高度的增加呈现出先减小后增加的趋势,拐点出现在2 km处。该现象出现的原因在于,不同构型的双钟形喷管在0～8 km左右的分离工作阶段,回流区轴向尺寸和回流与大气间的压力差随飞行高度的变化趋势不同。此外,增加基础段长度和面积比、减小延伸段长度和面积比均有利于减小吸气阻力,阻力系数的减小幅度为1%～2%。
- Abstract:
- The performance of dual-bell nozzles is affected by the aspiration drag generated in the recirculation zone during low-altitude operation. Dual-bell nozzles with different design parameters were studied by simulation to gain the aspiration drag at various flight altitudes. Results show that the aspiration drag does not always decrease with the increasing flight altitude as existing research reported. The aspiration drag of dual-bell nozzles with negative wall pressure gradient extension decreases with increasing flight altitude, while the aspiration drag of dual-bell nozzles with zero and positive wall pressure gradient extensions firstly decreases and then increases with the increase of flight altitude, and the inflection altitude appears at 2 km. These phenomena are caused by opposite varying trends for the axial size of the recirculation zone and the difference between the ambient pressure and the wall pressure in the recirculation zone during the ascent of flight altitude 0-8 km. Moreover, the aspiration drag can be reduced by increasing the length and area ratio of the base section and decreasing these parameters of nozzle extensions, the reduction in drag coefficient is about 1%-2%.
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备注/Memo
收稿日期:2023- 08- 26 修回日期:2023- 11- 26
基金项目:国家自然科学基金(52005385)
作者简介:刘亚洲(1994—),男,博士,工程师,研究领域为液体火箭发动机技术。
通信作者:胡海峰(1986—),男,博士,研究员,研究领域为液体火箭发动机技术。
更新日期/Last Update:
1900-01-01