面向在线变形的跨域变构型飞行器气动设计方法

doi:10.7527/S1000-6893.2025.32490

Abstract

Abstract:

Morphing aircraft， which adapt their aerodynamic shape online to meet mission demands， are a prominent research topic for maintaining high performance across wide flight envelopes. To address the challenges of integrated coordination between online/offline design variables and multi-profile heterogeneous constraints in the aerodynamic design of morphing aircraft， we develop a multi-mission aerodynamic design method for cross-domain aircraft. The proposed method parameterizes the aerodynamic shape with both online and offline variables and constructs an inner-outer dual-layer coupled optimization framework aimed at achieving a globally optimal offline shape while meeting the optimal online configurations for each flight profile. The method was applied to a variable-sweep cross-domain aircraft， and shape optimization is carried out for take-off/landing （max lift coefficient） and high-speed flight （max lift-to-drag ratio with center of pressure constraints）. Depending on the objective weights， the optimized lift coefficient at Ma=0.4 increased by 55.03% and 56.85%， while lift-to-drag ratios at Ma=6.0 and Ma=10.0 increased by 1.16%， 1.69% and 0.94%， 1.68%， respectively. Crucially， the high-speed center of pressure variation was successfully controlled within the 2% design constraint in all cases. These results verify the effectiveness of the proposed optimization framework.

Key words: cross-domain morphing, multi-point design, dual-layer optimization method, shape optimization, planar shape optimization

CLC Number:

V211.3

Haipeng CHEN, Haichuan YU, Xiangyu GU, Xinwei WANG, Xiaojiu ZHANG, Jun CHEN. Aerodynamic design methods for cross-domain morphing aircraft oriented to online deformation[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(5): 132490.

Figures/Tables 27

Fig.1

Fig.2

Table 1

Fig.3

Fig.4

Fig.5

Fig.6

Table 2

Table 3

Design conditions and online variable bounds

设计点	设计状态	$θ$ /（°）		$Λ$ /（°）
设计点	设计状态	下界	上界	下界	上界
1	Ma=0.4， H=0 km，α=4°	-50	-20	-0	30
2	Ma=6.0， H=30 km，α=4°	0	20	50	70
3	Ma=10.0， H=40 km，α=4°	10	25	60	75

Table 3

Table 4

Fig.7

Table 5

Fig.8

Fig.9

Table 6

Fig.10

Table 7

Table 8

Fig.11

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参数	数值
机身长度/m	7.837
翼面半展长/m	1.320
俯视投影面积/m²	14.740
前缘钝化半径/mm	5
外翼后掠角/（°）	50

展向截面	y方向位移/m
展向截面	下界	上界
1	-0.20	0.05
2	-0.20	0.05
3	-0.12	0.02
4	-0.08	0.02
5	-0.06	0.02

马赫数	气动力系数	R²	均方根误差/10^-4	平均绝对误差/10^-4
0.4	C_x	0.998 9	0.66	0.50
	C_y	0.999 8	5.26	4.11
	C_mz	0.999 7	4.20	3.23
6.0	C_x	0.996 6	1.25	0.95
	C_y	0.995 7	4.87	3.83
	C_mz	0.998 8	2.14	1.68
10.0	C_x	0.994 0	1.07	0.83
	C_y	0.997 0	2.67	1.90
	C_mz	0.997 3	2.18	1.58

工况	Λ/（°）
工况	Ma=0.4	Ma=6.0	Ma=10.0
Ori	50	50	50
工况1	0	62.18	61.27
工况2	0	61.56	59.94

工况	构型	Ma=0.4			Ma=6.0			Ma=10.0
工况	构型	C_L	C_D	K	C_L	K	X_CP	C_L	K	X_CP
Ori		0.378 0	0.078 2	4.832 3	0.124 1	3.942 0	0.703 4	0.098 9	3.905 8	0.703 3
工况1	Opt_sweep	0.553 9	0.103 5	5.353 0	0.111 6	4.000 5	0.675 0	0.089 7	3.966 5	0.683 0
工况1	Opt_hybrid	0.586 0	0.106 7	5.495 8	0.111 9	4.008 4	0.684 1	0.090 1	3.971 3	0.691 2
工况2	Opt_sweep	0.553 9	0.103 5	5.353 3	0.112 3	4.030 1	0.680 1	0.090 9	3.993 0	0.681 2
工况2	Opt_hybrid	0.592 9	0.106 9	5.544 8	0.112 2	3.987 9	0.700 1	0.090 5	3.942 4	0.703 4

Aerodynamic design methods for cross-domain morphing aircraft oriented to online deformation

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Figures/Tables 27

References 42

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工况	马赫数	优化阶段	ΔC_L /%	ΔK/%	ΔX_CP/%
工况1	0.4	后掠角优化	46.53	10.78
		型面优化	8.49	2.96
		双层优化	55.03	13.73
	6.0	后掠角优化	-10.07	1.48	-2.84
		型面优化	0.24	0.2	0.91
		双层优化	-9.83	1.69	-1.93
	10.0	后掠角优化	-9.30	1.55	-2.03
		型面优化	0.40	0.12	0.82
		双层优化	-8.90	1.68	-1.21
工况 2	0.4	后掠角优化	46.53	10.78
		型面优化	10.32	3.96
		双层优化	56.85	14.74
	6.0	后掠角优化	-9.51	2.23	-2.33
		型面优化	-0.08	-1.07	2.00
		双层优化	-9.59	1.16	-0.33
	10.0	后掠角优化	-8.09	2.23	-2.21
		型面优化	-0.40	-1.30	2.22
		双层优化	-8.49	0.94	0.01

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