融入低声爆设计的超声速民机概念方案多学科优化

doi:10.7527/S1000-6893.2025.31457

Abstract

Abstract:

To meet the demand for rapid analysis and optimization in conceptual design of supersonic civil aircraft， we present a multidisciplinary analysis optimization method integrated with low-boom design. The method consists of three main steps. Determining the target reversed equivalent area， which aims to provide a low-boom reversed equivalent area distribution target for multidisciplinary optimization. Optimizing the aircraft configuration within the multidisciplinary optimization framework， the overall parameters of the wing and tail are used as design variables to obtain a multi-objective optimal solution set for minimizing maximum takeoff weight and matching equivalent reversed area. Fine-tuning fuselage shape and tailplane parameters based on the results of multidisciplinary optimization， making minor adjustments to further match the target reversed equivalent area distribution. In this multidisciplinary approach， sonic boom characteristics are analyzed exclusively through the calculation of reversed equivalent area， which significantly reduces the computational expense. This enables the application of high-fidelity sonic boom prediction methods during the conceptual design. The method is compatible with existing multidisciplinary optimization frameworks for civil aircraft design， facilitating seamless implementation. The method is applied to the optimization of the medium-sized supersonic civil aircraft conceptual design.Results show that an optimal solution set for the multiple objectives is obtained with less computational expense. An optimal design that has less maximum takeoff weight and highly matches the reversed equivalent area， is selected from the optimal solution set. Compared to the baseline design， the maximum takeoff weight is reduced by 3.6% and sonic boom is reduced by 6.62 PLdB.

Key words: supersonic civil aircraft, conceptual design, multidisciplinary optimization, low-boom design, reversed equivalent area

CLC Number:

V221

Chao YANG, Yuting TAN, Wei WANG, Yan ZHAO, Xiongqing YU. Multidisciplinary optimization with low-boom design for supersonic civil aircraft conceptual design[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(20): 531457.

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部件参数	数值
机身长度/m	66
机翼展长/m	22.4
机翼前缘后掠角/（°）	76.6，71.5，66.0
机翼面积/m²	280
垂尾面积/m²	31.8
平尾面积/m²	32
短舱长度/m	6.7

部件	设计变量
机翼	内段上反角、中段上反角、外段上反角
	内段后掠角、中段后掠角、外段后掠角
	中段半展长、外段半展长
平尾	后掠角
平尾	梢根比
垂尾	展长
机身	上轮廓线控制点z坐标
	下轮廓线控制点z坐标
	右轮廓线控制点y坐标

约束变量	下限	上限
航程/km	6 000
起飞场长/m		1 800
着陆场长/m		1 800
单发失效第二爬升段爬升率/%	2.4
纵向力矩系数导数		0
滚转力矩系数导数		0
偏航力矩系数导数	0
客舱长度/m	14.0	15.4
客舱高度/m	2.65	2.90
客舱宽度/m	2.8	3.1

截面位置x_i （i=1，2，…，5）/m	下限/m²	上限/m²
1.80	0.016 7	0.020 4
30.00	6.280 0	6.940 0
37.00	9.960 0	10.650 0
44.00	14.380 0	15.890 0
85.56	27.650 0	27.650 0

类别	参数	初始值	下限	上限	优化结果
目标	min W_TO/t	80.16			77.29
目标	min F₁	0.644			0.401
变量	机翼内段上反角/（°）	18.3	12.0	20.0	17.3
	机翼中段上反角/（°）	4.0	0	7.0	5.1
	机翼外段上反角/（°）	11.0	7.0	15.0	12.2
	机翼内段后掠角/（°）	76.6	74.0	78.0	77.5
	机翼中段后掠角/（°）	71.5	69.0	73.0	70.6
	机翼外段后掠角/（°）	66.0	62.0	68.0	67.7
	机翼中段展长/m	6.96	6.60	7.30	7.13
	机翼外段展长/m	8.29	7.80	8.60	8.11
	平尾后掠角/（°）	66.0	62.0	70.0	68.1
	平尾梢根比	0.12	0.08	0.20	0.145
	垂尾展长/m	4.7	4.0	5.5	4.48
约束	航程/km	6 000	6 000		6 000
	起飞场长/m	1 723		1 800	1 702
	着陆场长/m	1 690		1 800	1 660
	单发失效第二爬升段爬升率/%	4.11	2.40		4.19
	纵向力矩系数导数	-0.018 7		0	-0.017 1
	滚转力矩系数导数	-0.002 8		0	-0.002 2
	偏航力矩系数导数	0.018 3	0		0.016 9
	客舱长度/m	14.2	14.0	15.4	14.0
	客舱高度/m	2.50	2.45	2.70	2.47
	客舱宽度/m	2.83	2.80	3.10	2.81

Multidisciplinary optimization with low-boom design for supersonic civil aircraft conceptual design

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部件参数	基准方案	优化方案
燃油质量/kg	39 518	37 769
机翼质量/kg	10 982	10 145
机身质量/kg	6 092	5 969
尾翼质量/kg	2 164	2 122
起落架质量/kg	3 046	2 937
系统和其他质量/kg	6 573	6 573
推进系统质量/kg	6 012	6 012
使用项目质量/kg	960	960
有效载荷质量/kg	4 800	4 800
总质量/kg	80 147	77 287

项目	基准方案	优化结果
起飞失速速度/（m·s^-1）	75.8	74.6
起飞场长/m	1 722.9	1 701.6
进场速度/（m·s^-1）	68.61	67.1
着陆场长/m	1 689.6	1 659.8
航程/km	6 000	6 000

项目	基准方案	优化结果	稳定性
C_mα/（（°）^-1）	-0.018 7	-0.017 1	纵向静稳定
C_nβ/（（°）^-1）	0.018 3	0.016 9	航向静稳定
C_lβ/（（°）^-1）	-0.002 8	-0.002 2	横向静稳定

航段名称	NO _x 排放量/kg
航段名称	基准方案	优化结果
滑跑、起飞	18.310	17.873
爬升	87.429	84.671
巡航	417.193	399.117
下降	0.675	0.641
进近着陆	0.104	0.101
全航线	523.711	502.403

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