考虑进排气系统的UCAV气动隐身一体化设计

doi:10.3969/j.issn.1009-086x.2026.03.011

摘要/Abstract

摘要：

气动和隐身性能是现代无人战斗机（unmanned combat air vehicle, UCAV）设计的两大关键目标。利用几何建模软件的二次开发技术，建立了UCAV机体、进气道和喷管的参数化几何模型，利用一维发动机模型开展UCAV内外流一体化的气动数值模拟。采用设计实验（design of experiments，DoE）和代理模型对UCAV机身和进排气系统进行了气动隐身一体化优化设计。结果显示优化方案在UCAV气动和隐身性能上均有显著提升，能较好地应用于机体和进排气高度融合的飞行器气动隐身多目标优化，有望缩短设计周期减低开发成本。

关键词: 进排气系统设计, 内外流一体化设计, 参数化建模, 一维发动机模型, 气动隐身一体化设计, 无人战斗机

Abstract:

Aerodynamic performance and stealth capability are two critical objectives in the design of modern unmanned combat air vehicles （UCAVs）. This study develops parametric geometric models of the UCAV airframe， inlet， and nozzle through secondary development of CAD software， and conducts aerodynamic numerical simulations of integrated internal and external flow coupling using a 1D engine model. An aerodynamic-stealth integrated optimization framework is implemented through design of experiments （DoE） and surrogate modeling techniques for the UCAV airframe， inlet and exhaust system. The results demonstrate that the proposed optimization framework achieves significant improvements in both aerodynamic and stealth performance， validating its effectiveness in multi-objective aerodynamic-stealth optimization for aircraft with highly-integrated airframe-propulsion configurations. Furthermore， this methodology shows promising potential for accelerating design iterations and reducing developmental expenditures.

Key words: inlet and exhaust system design, integrated interior and outflow design, parametric modeling, one-dimensional engine model, aerodynamic stealth integrated design, unmanned combat air vehicle（UCAV）

中图分类号:

郑力, 虞涵普, 张祺忻, 邓双厚, 冯国旭, 杨延年. 考虑进排气系统的UCAV气动隐身一体化设计[J]. 现代防御技术, 2026, 54(3): 115-130.

Li ZHENG, Hanpu YU, Qixin ZHANG, Shuanghou DENG, Guoxu FENG, Yannian YANG. Integrated Design of Aerodynamic Stealth for UCAV Considering Inlet and Exhaust System[J]. Modern Defense Technology, 2026, 54(3): 115-130.

图/表 41

图1 机身平面几何形状参数定义

Fig. 1 Definition of plane geometric shape parameters for airframe

图2 干净构型与带动力构型对比

Fig. 2 Comparison between clean configuration and inlet configuration

图3 进气道进口外形主要参数

Fig. 3 Main parameters of the inlet shape of the intake duct

图4 鼓包外形控制样条线分布

Fig. 4 Spline distribution of bulge shape control

图5 进气道进口截面形状及曲率分布

Fig. 5 Cross-sectional shape and curvature distribution of the inlet duct

图6 喷口平面外形及参数

Fig. 6 Plane shape and parameters of nozzle

图7 喷管进出口截面积示意

Fig. 7 Schematic diagram of cross-sectional area of nozzle inlet and outlet

图8 进气道参数化生成模型

Fig. 8 Parameterized generation model for intake duct

图9 分开排气式涡扇发动机结构示意图

Fig. 9 Schematic diagram of separated exhaust turbofan engine structure

图10 RCS随ka变化规律

Fig. 10 RCS variation law with ka

表1 机体各优化变量及范围

Table 1 Optimization variables and ranges of the airframe

参数	下限	初始构型	上限
b/C₁	1.3	1.5	1.7
$χ 1$ /（°）	45	50	60
T₃/（°）	-8	-5	0

表1 机体各优化变量及范围

Table 1 Optimization variables and ranges of the airframe

参数	下限	初始构型	上限
b/C₁	1.3	1.5	1.7
$χ 1$ /（°）	45	50	60
T₃/（°）	-8	-5	0

图11 不同网格疏密程度的机身网格

Fig. 11 Aircraft body grids with different degrees of grid density

表2 不同数量网格下计算所得升阻比

Table 2 Calculate the lift to drag ratio under different numbers of grids

网格数	L/D计算值
200万	16.44
320万	17.09
437万	17.08

图12 机身电磁计算网格及入射波分布

Fig. 12 Electromagnetic calculation grid and incident wave distribution of the aircraft body

表3 进气道进口及鼓包优化变量初始值及优化值范围

Table 3 Initial values and optimization range of variables for inlet and bulge optimization of intake duct

参数	下限	初始构型	上限
L_in/mm	500	800	1 200
H_in	0	0.4	0.8
H_gb	0	0.4	0.8
Z_y	0.2	0.5	1.0
$χ i n$	30	32	36

表3 进气道进口及鼓包优化变量初始值及优化值范围

Table 3 Initial values and optimization range of variables for inlet and bulge optimization of intake duct

参数	下限	初始构型	上限
L_in/mm	500	800	1 200
H_in	0	0.4	0.8
H_gb	0	0.4	0.8
Z_y	0.2	0.5	1.0
$χ i n$	30	32	36

表4 进气道内通道优化变量初始值及优化取值范围

Table 4 Initial value and optimization range of variables for optimizing the internal passage of intake duct

参数	下限	初始构型	上限
A	-5	-4	5
A′	-5	-4	5
b₂	-16	0	4
c₂	-16	-15	4

图13 不同控制参数Al，6下的机身截面尾缘

Fig. 13 Tail edge of fuselage section under different control parameters Al，6

图14 机体升阻比随截面尾缘控制系数Al，6的变化

Fig. 14 Variation of lift to drag ratio of the Body with the control coefficient Al，6 of the section trailing edge

表5 喷管内通道优化变量初始值及优化取值范围

Table 5 Initial value and optimization range of variables for optimizing the internal passage of the nozzle

参数	下限	Baseline	上限
A	-10	0	10
A′	-10	0	10
b₂	50	60	70
c₂	50	60	70

图15 代理模型建立及优化流程

Fig. 15 Establishment and optimization process of proxy model

图16 基于ISGHT建立的优化设计框架

Fig. 16 Optimization design framework based on ISGHT

图17 机体优化样本分布及可行域

Fig. 17 Sample distribution and feasible region for optimizing the organism

表6 初始与优化后各样本参数组合

Table 6 Initial and optimized parameter combinations for each sample

参数	b/C₁	$χ 1$ /（ $°$ ）	T₃/（ $°$ ）
初始构型	1.50	50.00	-5.00
1#	1.56	54.40	-3.64
2#	1.54	53.91	-4.14
3#	1.54	53.45	-3.60

表6 初始与优化后各样本参数组合

Table 6 Initial and optimized parameter combinations for each sample

参数	b/C₁	$χ 1$ /（ $°$ ）	T₃/（ $°$ ）
初始构型	1.50	50.00	-5.00
1#	1.56	54.40	-3.64
2#	1.54	53.91	-4.14
3#	1.54	53.45	-3.60

表7 初始与各样本组合RCS计算结果

Table 7 Initial RCS calculation results for each sample combination

编号	L/D	RCS/dBsm
编号	L/D	400 MHz	2 GHz	10 GHz
Baseline	17.11	-5.27	-22.23	-29.41
1#	19.57	-4.39	-20.37	-30.06
2#	19.13	-5.69	-20.40	-29.40
3#	18.94	-5.32	-20.80	-30.00

图18 各波段下的机体前向90°方位角RCS分布

Fig. 18 RCS distribution of the aircraft at a forward 90 ° azimuth angle in each frequency band

图19 优化构型与初始构型压力分布对比

Fig. 19 Comparison of pressure distribution between optimized configuration and initial configuration

图20 优化构型机体与初始构型机体RCS分布对比

Fig. 20 Comparison of RCS distribution between optimized configuration aircraft and initial configuration aircraft

图21 进气道进口及鼓包参数寻优样本及可行域

Fig. 21 Optimization samples and feasible regions for inlet and bulge parameters of intake duct

表8 进气道进口及鼓包初始与优化后各样本参数组合

Table 8 Initial and optimized sample parameter combinations for intake duct inlet and bulge

参数	L_in	H_in	H_gb	$χ i n$	Z_x	Z_y
初始构型	800	0.40	0.40	30	0.50	0.50
1#	653	0.42	0.21	35.78	1.00	1.00
2#	667	0.40	0.29	30	1.00	0.98
3#	634	0.50	0.14	30.46	1.00	0.95

表8 进气道进口及鼓包初始与优化后各样本参数组合

Table 8 Initial and optimized sample parameter combinations for intake duct inlet and bulge

参数	L_in	H_in	H_gb	$χ i n$	Z_x	Z_y
初始构型	800	0.40	0.40	30	0.50	0.50
1#	653	0.42	0.21	35.78	1.00	1.00
2#	667	0.40	0.29	30	1.00	0.98
3#	634	0.50	0.14	30.46	1.00	0.95

表9 进气道进口及鼓包初始与优化后各样本组合计算结果

Table 9 Calculation results of initial and optimized sample combinations for inlet and bulge of intake duct

编号	L/D′	$σ$	DC₆₀
初始构型	15.10	0.957	0.29
1#	16.12	0.965	0.19
2#	15.99	0.961	0.13
3#	16.23	0.964	0.18

表9 进气道进口及鼓包初始与优化后各样本组合计算结果

Table 9 Calculation results of initial and optimized sample combinations for inlet and bulge of intake duct

编号	L/D′	$σ$	DC₆₀
初始构型	15.10	0.957	0.29
1#	16.12	0.965	0.19
2#	15.99	0.961	0.13
3#	16.23	0.964	0.18

图22 优化构型进口与初始构型进口压力分布及流线对比

Fig. 22 Comparison of pressure distribution and streamline between optimized configuration inlet and initial configuration inlet

图23 进口及鼓包优化构型与初始构型进气道出口截面总压恢复系数分布对比

Fig. 23 Comparison of total pressure recovery coefficient distribution at the outlet section of the inlet duct between the imported and bulge-optimized Configurations and the initial Configuration

图24 进气道内通道优化各参数样本分布

Fig. 24 Sample distribution of various parameters for optimizing the internal channel of the intake duct

表10 进气道内通道初始与优化后构型计算结果对比

Table 10 Comparison of initial and optimized configuration calculation results for the internal channel of the intake duct

组合	$σ$	DC₆₀
初始构型	0.945	0.34
优化构型	0.956	0.19

表10 进气道内通道初始与优化后构型计算结果对比

Table 10 Comparison of initial and optimized configuration calculation results for the internal channel of the intake duct

组合	$σ$	DC₆₀
初始构型	0.945	0.34
优化构型	0.956	0.19

图25 内通道优化构型与初始构型对称截面马赫数及流线对比

Fig. 25 Comparison of Mach number and streamline between optimized internal channel configuration and initial configuration with symmetric cross-section

图26 优化构型与初始构型进气道出口总压恢复系数分布对比

Fig. 26 Comparison of total pressure recovery coefficient distribution at the outlet of optimized and initial intake configurations

图27 优化构型与初始构型进气道内通道各截面马赫数及流线分布

Fig. 27 Optimization configuration and initial configuration of Mach number and streamline distribution in each section of the inlet channel

图28 优化前后截面的面积、曲率及构型中心线对比

Fig. 28 Comparison of cross-sectional area， curvature， and configuration centerline before and after optimization

表11 喷管初始构型与优化构型计算Cfx 结果对比

Table 11 Comparison of Cfx results between initial and optimized nozzle configurations

组合	Cf_x
初始构型	0.683
优化构型	0.712

图29 优化前后喷管截面模型及马赫数分布对比

Fig. 29 Comparison of nozzle cross-sectional models and Mach number distribution before and after optimization

图30 优化前后喷管表面马赫数分布对比

Fig. 30 Comparison of Mach number distribution on nozzle surface before and after optimization

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