类X-37B航天器气动力天地相关性数值模拟

doi:10.7527/S1000-6893.2020.24010

先进空间运输系统气动设计专栏

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

类X-37B航天器气动力天地相关性数值模拟

马率, 张露, 刘钒, 孙俊峰, 崔兴达

中国空气动力研究与发展中心计算空气动力研究所, 绵阳 621000

收稿日期:2020-03-24 修回日期:2020-05-07 发布日期:2020-06-18
通讯作者: 马率 E-mail:tuboshu2002@163.com

Numerical simulation of correlation analysis of X-37B-like spacecraft's aerodynamic datum between flight and ground prediction

MA Shuai, ZHANG Lu, LIU Fan, SUN Junfeng, CUI Xingda

Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2020-03-24 Revised:2020-05-07 Published:2020-06-18

摘要/Abstract

摘要： 随着高性能计算机的发展，CFD已成为飞行器设计和流场分析不可缺少的重要手段，风洞试验与飞行数据的天地相关性问题正是其中一项重要的研究内容，X-37B作为继航天飞机之后美国发展的最成功的可跨大气层在轨飞行器，从气动特性角度分析其大气层内飞行走廊的状态对中国类似航天器的研制具有重要的借鉴意义。首先，对计算类X-37B布局飞行器的网格无关性及网格修正开展了研究，在此基础上提出的网格规模影响修正方法对该类飞行器的计算结果修正经过验证是可信的；然后，分别对比分析了雷诺数的影响和试验状态支架干扰的影响，完成了基于数值模拟的高空飞行与风洞试验气动特性差异分析。结果表明，网格规模主要对亚声速来流计算状态压差产生的轴向力影响较大，对法向力系数、俯仰力矩系数和纵向压心影响较小；雷诺数对该类飞行器气动特性特别是轴向力系数、阻力系数和升阻比有较大的影响，但随着马赫数的增加，影响特性开始变的非常复杂；由于风洞试验状态支杆存在，亚跨声速来流条件对该类飞行器的底阻影响很大，需要采取一定的方法和手段对支杆影响进行修正。

关键词: X-37B航天器, 飞行走廊, 天地相关性, 网格收敛性, 雷诺数, 支杆

Abstract: X-37B is the most successful trans-atmospheric orbital vehicle in the US after the space shuttle. Analyzing the aerodynamic characteristics in its flight corridor can provide significant reference for the development of similar spacecraft in China. With the progress of HPC, CFD has become an important method in aircraft design and flow field analysis, in which the correlation between the flight and ground data is part of the validation function. The grid independence and correction of an X-37B-like aircraft have been studied, followed by the research on the Reynolds number effect and support interference effect. The difference between the high-altitude aerodynamic data and wind-tunnel results are computed and studied. The grid scale has a significant effect on the axial drag in the subsonic flow, and a minor effect on the normal force and pitching moment. The Reynolds number has a significant effect on the axial force, drag force and lift-drag ratio, while the effect becomes complex as the Mach number increases. The presence of the support sting in the wind tunnel has a remarkable effect on the aircraft base drag under subsonic and transonic inflow conditions, and correction of the support effect should be modified in a certain way.

Key words: X-37B aircraft, flight corridor, correlation between flight and ground data, grid convergence, Reynolds number, support sting

中图分类号:

V211.3

马率, 张露, 刘钒, 孙俊峰, 崔兴达. 类X-37B航天器气动力天地相关性数值模拟[J]. 航空学报, 2021, 42(2): 624010-624010.

MA Shuai, ZHANG Lu, LIU Fan, SUN Junfeng, CUI Xingda. Numerical simulation of correlation analysis of X-37B-like spacecraft's aerodynamic datum between flight and ground prediction[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(2): 624010-624010.

参考文献

[1] 陈坚强, 张益荣, 张毅锋,等. 高超声速气动力数据天地相关性研究综述[J].空气动力学学报, 2014, 32(5):587-599. CHEN J Q, ZHANG Y R, ZHANG Y F, et al. Review of correlation analysis of aerodynamic data between flight and ground prediction for hypersonic vehicle[J]. Acta Aerodynamica Sinica, 2014, 32(5):587-599(in Chinese).
[2] WIKIPEDIA. Boeing X-37[EB/OL]. (2015-10-25)[2020-03-24]. http://en.wikipedia.org/wiki/X-37.
[3] 孙宗祥, 唐志共, 陈喜兰, 等. X-37B的发展现状及空气动力技术综述[J].实验流体力学, 2015, 29(1):1-14. SUN Z X, TANG Z G, CHEN X L, et al. Review of the state-of-art and aerodynamic technology of X-37B[J]. Journal of Experiments in Fluid Mechanics, 2015, 29(1):1-14(in Chinese).
[4] X-37B orbital test vehicle[EB/OL].[2020-03-24]. http://www.boeing.com/boeing/defensespace/ic/sis/x37b_otv/x37b_otv.page.
[5] 冯毅, 肖光明, 唐伟, 等. 类X-37运载器气动布局概念设计[J].空气动力学学报, 2012, 31(1):94-98. FENG Y, XIAO G M, TANG W, et al. Aerodynamics configuration conceptual design for X-37 analog transporter[J]. Acta Aerodynamica Sinica, 2012, 31(1):94-98(in Chinese).
[6] 蒋崇文, 杨加寿, 李克难, 等. 类X-37B飞行器气动特性的数值研究[J]. 中国空间科学技术, 2014, 4(2):94-98. JIANG C W, YANG J S, LI K N, et al. Numerical study on aerodynamic characteristics of an X-37B-like vehicle[J]. Chinese Space Science and Technology, 2014, 4(2):94-98(in Chinese).
[7] 牟斌. 流动控制数值模拟研究[D]. 绵阳:中国空气动力研究与发展中心, 2006. MOU B. Numerical simulation and investigation of flow control[D]. Mianyang:China Aerodynamics Research and Development Center, 2006(in Chinese).
[8] 肖中云. 旋翼流场数值模拟方法研究[D]. 绵阳:中国空气动力研究与发展中心, 2007. XIAO Z Y. Investigation of computational modeling techniques for rotor flowfields[D]. Mianyang:China Aerodynamics Research and Development Center, 2007(in Chinese).
[9] 肖中云, 江雄, 牟斌, 等. 并行环境下外挂物动态分离过程的数值模拟[J]. 航空学报, 2010, 31(8):1509-1516. XIAO Z Y, JIANG X, MOU B, et al. Numerical simulation of dynamic process of store separation in parallel environment[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(8):1509-1516(in Chinese).
[10] 王建涛, 易贤, 肖中云, 等. ARJ21-700飞机冰脱落数值模拟[J]. 空气动力学学报, 2013, 31(4):430-436. WANG J T, YI X, XIAO Z Y, et al. Numerical simulation of ice shedding from ARJ21-700[J]. Acta Aerodynamica Sinica, 2013, 31(4):430-436(in Chinese).
[11] 余永刚, 周铸, 黄江涛, 等. 单通道客机气动标模CHN-T1设计[J]. 空气动力学学报, 2018, 36(3):505-513. YU Y G, ZHOU Z, HUANG J T, et al. Aerodynamic design of a standard model CHN-T1for single-aisle passenger aircraft[J]. Acta Aerodynamica Sinica, 2018, 36(3):505-513(in Chinese).
[12] 马率, 邱名, 王建涛, 等. CFD在螺旋桨飞机滑流影响研究中的应用[J]. 航空学报, 2019, 40(4):622365. MA S, QIU M, WANG J T, et al. Application of CFD in slipstream effect on propeller aircraft research[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(4):622365(in Chinese).
[13] STEFAN K, DIMITRI M. Summary of data from the sixth AIAA CFD drag prediction workshop:Case 5(coupled aero-structural simulation):AIAA-2017-1207[R]. Reston:AIAA, 2017.
[14] EDWARD N T, OLAF P B, STEFAN K, et al. Summary of data from the sixth AIAA CFD drag prediction work-shop:CRM cases 2 to 5:AIAA-2017-1208[R]. Reston:AIAA, 2017.
[15] 贾区耀, 杨益农, 陈农. 天空飞行与地面风洞实验动态气动相关中的雷诺数影响[J]. 实验流体力学, 2007, 21(4):91-96. JIA Q Y, YANG Y N, CHEN N. The influence of Reynolds number on dynamic aerodynamics correlation between real flight and wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2007, 21(4):91-96(in Chinese).
[16] 陈谟. 细长物体亚、跨、超声速α_∞=0°~90°消除支杆干扰的气动力实验方法研究[J]. 宇航学报, 2009, 30(1):109-113. CHEN M. A study of averodynamic experiment method eliminated sting interference in the sub-tran-supersonic wind tunnel for slender body at α_∞=0°-90°[J]. Journal of Astronautics, 2009, 30(1):109-113(in Chinese).
[17] 章荣平, 王勋年, 李真旭, 等. 低速风洞尾撑支杆干扰研究[J]. 实验流体力学, 2006, 20(3):33-38. ZHANG R P, WANG X N, LI Z X, et al. Investigation of sting support interference in low speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2006, 20(3):33-38(in Chinese).
[18] 王勋年. 低速风洞试验[M]. 北京:国防工业出版社, 2002. WANG X N. Low speed wind tunnel test[M]. Beijing:National Defense Industry Press, 2002(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

类X-37B航天器气动力天地相关性数值模拟

Numerical simulation of correlation analysis of X-37B-like spacecraft's aerodynamic datum between flight and ground prediction

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	惠俊鹏, 汪韧, 俞启东. 基于强化学习的再入飞行器“新质”走廊在线生成技术[J]. 航空学报, 2022, 43(9): 325960-325960.
[2]	罗佳奇, 傅文豪, 曾先, 夏志恒. 雷诺数对高负荷低压涡轮叶栅流动损失的不确定性影响[J]. 航空学报, 2022, 43(7): 125427-125427.
[3]	郭秋亭, 孙岩, 郭正, 刘光远. 风洞试验雷诺数/静气动弹性效应分离方法[J]. 航空学报, 2022, 43(11): 526312-526312.
[4]	杨钊, 李杰, 牛笑天. 层流机翼飞行验证平台雷诺数效应分析及修正[J]. 航空学报, 2022, 43(11): 527287-527287.
[5]	姜鹏, 郭栋, 韩亮, 李清东, 任章. 多飞行器再入段时间协同弹道规划方法[J]. 航空学报, 2020, 41(S1): 723776-723776.
[6]	王继明, 高云海, 焦仁山. 大型客机低速构型高雷诺数风洞腹撑支架干扰数值模拟[J]. 航空学报, 2020, 41(4): 123526-123526.
[7]	张永杰, 吴莹莹, 朱胜利, 王斌团, 谭兆光, 袁昌盛. 翼身融合民机典型PRSEUS受压壁板屈曲及渐进损伤分析[J]. 航空学报, 2019, 40(9): 623185-623185.
[8]	朱志斌, 尚庆, 白鹏, 刘强. 翼型低雷诺数层流分离现象随雷诺数的演化特征[J]. 航空学报, 2019, 40(5): 122528-122528.
[9]	张彦军, 段卓毅, 雷武涛, 白俊强, 徐家宽. 超临界自然层流机翼设计及基于TSP技术的边界层转捩风洞试验[J]. 航空学报, 2019, 40(4): 122429-122429.
[10]	洪俊武, 王运涛, 李伟, 杨小川. HiLiftPW-3高升力构型数值模拟[J]. 航空学报, 2019, 40(3): 122391-122391.
[11]	钟敏, 华俊, 郑遂, 白俊强, 孙卫平, 黄领才. 大型水陆两栖飞机侧风起降的滑流影响分析[J]. 航空学报, 2019, 40(1): 522372-522372.
[12]	王科雷, 周洲, 祝小平, 许晓平. 低雷诺数多螺旋桨/机翼耦合气动设计[J]. 航空学报, 2018, 39(8): 121918-121918.
[13]	李冠雄, 马东立, 杨穆清, 郭阳. 低雷诺数翼型局部振动非定常气动特性[J]. 航空学报, 2018, 39(1): 121427-121427.
[14]	孙俊磊, 王和平, 周洲, 雷珊. 螺旋桨滑流对菱形翼布局无人机气动的影响[J]. 航空学报, 2018, 39(1): 121431-121431.
[15]	张保雷, 上官燕琴, 王娴, 陈刚, 李跃明. 低雷诺数下横流-射流中剪切涡的试验研究[J]. 航空学报, 2017, 38(7): 120831-120831.