面向总体性能的高速飞行器布局优化

邓帆; 焦子涵; 付秋军; 陈林; 田书玲; 张栋

doi:10.13700/j.bh.1001-5965.2015.0847

面向总体性能的高速飞行器布局优化

doi: 10.13700/j.bh.1001-5965.2015.0847

邓帆^{1, 2, ,},
焦子涵^1,,
付秋军^1,,
陈林^1,,
田书玲^3,,
张栋^4,

1.
中国运载火箭技术研究院空间物理重点实验室, 北京 100076
2.
谢菲尔德大学机械工程学院, 谢菲尔德 S1
3.
南京航空航天大学航空宇航学院, 南京 210016
4.
西北工业大学航天飞行动力学技术重点实验室, 西安 710072

详细信息

作者简介:
焦子涵, 男, 硕士, 工程师。主要研究方向:飞行器气动布局设计。Tel.:010-88531845, E-mail:zihan325@126.com

付秋军, 男, 博士, 研究员。主要研究方向:飞行器总体设计。Tel.:010-68381167, E-mail:fuqiujun@163.com

陈林, 男, 博士, 高级工程师。主要研究方向:空气动力学、飞行器设计。Tel.:010-88531845, E-mail:chenlincfd@gmail.com

田书玲, 男, 博士, 副教授。主要研究方向:计算流体力学、飞行器优化设计。Tel.:025-84892735, E-mail:shulingtian@nuaa.edu.cn

张栋, 男, 博士, 讲师。主要研究方向:飞行器动力学建模与控制。Tel.:029-88492788, E-mail:zhangdong@nwpu.edu.cn

通讯作者:
邓帆, 男, 博士, 高级工程师。主要研究方向:飞行器总体设计。Tel.:010-68199538, E-mail:dengfan8245@sina.cn

中图分类号: V221⁺.3;V211.3;V211.7
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出版历程
- 收稿日期: 2015-12-25
- 录用日期: 2016-01-22
- 网络出版日期: 2017-12-20

Hypersonic vehicle shape optimal design based on overall performance

DENG Fan^{1, 2
, ,},
JIAO Zihan^1
,,
FU Qiujun^1
,,
CHEN Lin^1
,,
TIAN Shuling^3
,,
ZHANG Dong^4
,

1.
Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China
2.
Department of Mechanical Engineering, University of Sheffield, Sheffield S1
3.
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
4.
National Key Laboratory of Aerospace Flight Dynamics, Northwestern Polytechnical University, Xi'an 710072, China

More Information

Corresponding author: DENG Fan, Tel.:010-68199538, E-mail:dengfan8245@sina.cn

摘要

摘要:
飞行器气动布局的选型和优化技术在总体设计中处于关键地位，在临近空间飞行的飞行器对升阻比和操控性能都提出了更高的要求。翼身组合的升力体外形由于兼顾内部装填以及升阻特性成为了目前高速飞行器主要的设计方向。以一类具有普适性的面对称升力体外形为基础，采用相关性分析手段提取出飞行器的关键几何参数，挖掘出几何参数对所关心的总体性能指标的影响度大小，并建立起基于CFD方法的气动布局优化平台，以总体性能指标为约束，优化出高升阻比外形，通过风洞试验验证了优化设计方法的有效性，为高速飞行器的气动布局工程化设计提供了有效的技术手段。
- 高速飞行器 /
- 优化设计 /
- 总体性能 /
- 风洞试验 /
- 数值计算
Abstract:
Aerodynamic configuration design and optimization are vital to overall design of aircraft. Higher requirements of lift-drag ratio and control performance are put forward for near space vehicles. The lifting-body shape of the wing-body combination has become the main design direction of the hypersonic vehicle due to its internal loading and lift-drag characteristics. According to a class of universal symmetry lifting-body configuration, the key geometry parameters of vehicle were extracted using interrelation analysis method. The effect of geometry parameters on concerned overall performance was dug out. Aerodynamic shape optimization platform was established based on CFD method. With several key overall performance constraints, high lift-drag ratio shape was designed and optimized. The effectiveness of optimal design has been verified by wind tunnel test, which will provide an effective technical means for rapid engineering aerodynamic shape design of hypersonic vehicle.
- hypersonic vehicle /
- optimal design /
- overall performance /
- wind tunnel test /
- numerical calculation

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图 1 初始参数化外形示意图

Figure 1. Schematic diagram of initial parameterized shape

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图 2 快速工程算法有效性验证(Ma=10.5, α=-4°, β=2°)

Figure 2. Effectiveness verification of engineering algorithm (Ma=10.5, α=-4°, β=2°)

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图 3 快速优化设计方法流程图

Figure 3. Flowchart of fast optimization design method

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图 4 样本点计算网格拓扑和压力分布云图

Figure 4. Computational grid topology and pressure distribution contours of sample points

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图 5 初始外形与优化外形对比

Figure 5. Comparison between initial and optimum shapes

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图 6 飞行器优化前后流场结构对比

Figure 6. Flow structure comparison of initial and optimum vehicle

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图 7 优化前后外形纹影图(Ma=8)

Figure 7. Schlieren pictures of initial and optimum shapes (Ma=8)

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图 8 优化前后外形升阻性能曲线比较

Figure 8. Lift and drag curves of initial and optimum shapes

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表 1 参数化建模的主要几何参数

Table 1. Main geometrical parameters of parametric modelling

参数	物理意义	取值范围
α_1up/(°)	一锥上锥角	(8, 15)
α_2up/(°)	二锥上锥角	(0, 5)
β_WB/(°)	水平翼后端面处翼安装角	(-2, +2)
R_head/mm	端头半径	(10, 50)
R_fyrd/mm	俯仰舵前缘半径	(10, 20)
C_L₁	一锥长度占总长的百分比	(0, 0.5)
ρ_wing	水平翼二次曲线形状系数	(0.3, 0.9)
C_WS	水平翼起始位置长度系数	(0, 1)
α_wing/(°)	水平翼后缘后掠角	(-50, 50)
α_fyrd/(°)	俯仰舵前缘后掠角	(0, 50)
d_Blw/mm	BB下截面宽度	(358, 558)
η_fyrd/mm	俯仰舵外露展长	(600, 700)
L/mm	飞行器总长	(2 000, 3 000)
f_{xrd_turn}	俯仰舵舵轴位置系数	(0.1, 0.9)
C_zita	俯仰舵在体身z向位置系数	(0.2, 0.8)
C_{L_W}	水平翼截止位置长度系数	(0, 1)

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表 2 一阶灵敏度函数

Table 2. First-order sensitivity function

类型	表达式	正则表达式	维数
一阶基准	∂f/∂x	Δf/Δx	f/x
一阶百分比	(∂f/∂x)∂x	Δf	f
一阶对数	(∂f/∂x)(x/f)	(Δf/Δx)(x/f)

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表 3 参数敏感性排序

Table 3. Rank of sensitive parameters on each factor

尺寸定义	k(按影响度从大到小排序)
长度	L	R_fyrd	η_fyrd	d_Blw	R_head
角度	α_1up	β_WB	α_2up	α_wing	α_fyrd
系数	C_{L_W}	C_L₁	C_WS	ρ_wing	C_zita

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表 4 典型马赫数状态

Table 4. Parameters of typical Mach number

H/km	Ma	T₀/K	P₀/(10⁵Pa)	/10^-3	Re_∞L/(10⁷m^-1)
33.02	5.16	290	6.70	2.43	1.97
38.21	8.17	435	33.28	4.16	1.64
41.72	10.60	596	95.90	5.69	1.43

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表 5 优化前后气动特性(Ma=8，α=8°)

Table 5. Aerodynamic characteristics before and after optimization (Ma=8, α=8°)

外形	C_A	C_N	κ
初始外形	0.286 2	1.599 6	3.051 5
优化外形	0.192 9	1.434 0	3.566 8

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