跨域变体飞行器气动力热非层次多模型融合降阶方法

doi:10.7527/S1000-6893.2023.28259

Abstract

Abstract:

Cross-domain morphing aircraft can change their configurations to adapt to different flight conditions and improve flight capability in large airspace within wide speed range， consequently becoming a topic of interest. This paper constructs a high-fidelity aerodynamic and aerothermodynamic model of a quasi-waverider cross-domain morphing aircraft based on RANS equations and low-fidelity models based on engineering estimation methods. The Non-hierarchical Multi-model Fusion Method using Multi-level Kriging and Quadratic Programming （NMF-MKQP） is proposed considering the existence of non-hierarchical multi-fidelity models for hypersonic aerodynamic and aerothermodynamic analysis. The uncoupled expression of the mean squared error is derived to convert the global optimization problem of scaling factor maximum likelihood estimation into a quadratic programming problem， and the scaling factors are analytically determined accordingly. In this way， the efficiency of the proposed model reduction method is significantly improved while reducing the computation cost. The NMF-MKQP outperforms the state-of-the-art multi-fidelity surrogate modeling methods in terms of approximation accuracy. The aerodynamic and aerothermodynamic characteristics of cross-domain morphing aircraft with varying sweep angles and spans are assessed based on the constructed reduced-order model， further establishing a morphing strategy during cross-domain gliding. The flight performance increases with the lift-to-drag ratio， while ensuring a decreasing maximum heat flux.

Key words: cross-domain morphing aircraft, aerodynamics and aerothermodynamics, non-hierarchical multi-model fusion, model order reduction, wing sweep angle morphing, wing span morphing

CLC Number:

V221

Yufei WU, Teng LONG, Renhe SHI, Yao ZHANG. Non⁃hierarchical multi⁃model fusion order reduction based on aerodynamic and aerothermodynamic characteristics for cross⁃domain morphing aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(21): 528259-528259.

Figures/Tables 26

Fig.1

Fig.2

Table 1

Initial scheme geometry parameters

参数	$W'$	$T'$	$H u'$	$H l'$	$N u'$	$N l'$
取值	1.40	1.00	0.30	0.30	1.25	1.25
参数	$M u'$	$M l'$	$ρ L'$	$ρ 12'$	$W 1'$	$W 2'$
取值	0.75	0.75	0.30	0.70	0.75	0.60

Table 1

Fig.3

Fig.4

Fig.5

Table 2

Results of grids independency check

代号	规模/万	$C L$	$C D$	$C L / D$	$q m a x$ / （10⁶ W·m^-2）	最大变化率/ %
G1	1 024	0.288	0.124	2.322	6.784	N/A
G2	1 167	0.288	0.124	2.322	7.013	3.37
G3	1 296	0.288	0.124	2.321	7.306	4.18
G4	1 530	0.288	0.124	2.322	7.304	0.28
G5	1 814	0.287	0.124	2.322	7.303	0.20

Table 2

Fig.6

Table 3

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Table 4

Comparison of simulation results of ball⁃head blunt cone case

模型	$q m a x$ /（10⁶ W·m^-2）	耗时/s
高精度	3.196	8.446×10³
低精度Ⅰ	3.285	5.367
低精度Ⅱ	3.364	4.548

Table 4

Table 5

Constructing cost of numerical benchmarks

序号	$N c$	$n e$	$r e c$
1	2	5	4
2	2	20	4
3	3	40	6
4	3	60	6
5	2	150	4
6	3	200	6

Table 5

Table 6

Table 7

Correlation check results for multi⁃fidelity models

模型	$C L$	$C D$	$q m a x$
高精度/低精度Ⅰ	0.979	0.964	0.861
高精度/低精度Ⅱ	0.979	0.964	0.840

Table 7

Table 8

Approximation accuracy and computation cost of initial scheme with aerodynamic and aerothermodynamic characteristics

类别	指标	NMF-MKQP	MLK	CK⁃Ⅰ	CK-Ⅱ
$C L$	MAE/10^-3	1.877	1.871	2.929	2.921
	RMSE	4.788×10^-6	4.788×10^-6	7.333×10^-4	7.387×10^-4
	耗时/s	3.452	11.436	2.736	2.795

$C D$	MAE	1.101×10^-4	1.096×10^-4	1.273×10^-3	1.189×10^-3
	RMSE	4.967×10^-8	4.971×10^-8	2.588×10^-4	2.626×10^-4
	耗时/s	3.312	9.918	2.946	2.790

q_max	MAE/10⁵	2.299	2.960	4.529	3.929
	RMSE/10⁵	1.276	1.667	1.764	1.582
	耗时/s	3.651	11.294	2.863	2.844

Table 8

Table 9

Cross⁃domain flight characteristic conditions

工况点	$M a ∞$	$α$ /（°）	$H$ /km
起点	18.0	20.0	50.0
中点	15.0	15.0	45.0
末点	12.0	10.0	40.0

Table 9

Fig.13

Fig.14

Fig.15

Fig.16

Table 10

Comparison of aerodynamic and aerothermodynamic performance of morphing schemes

工况点	$C L / D$		$q m a x$ /（W·m^-2）
工况点	初始方案	变体方案	初始方案	变体方案
起点	1.835	2.170	1.621×10⁷	1.578×10⁷
中点	2.352	2.554	1.026×10⁷	9.961×10⁶
末点	2.937	3.216	5.072×10⁶	4.928×10⁶

Table 10

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问题	指标	NMF-MKQP	VWS-MFS	VWS-HK	LR-MFS	MLMF-CK
1	MAE	1.862×10^-6	0.214	1.017	2.865	1.825
1	RMSE	1.951×10^-7	0.051	0.349	0.855	1.269

2	MAE	0.210	0.499	0.547	1.092	6.353
2	RMSE	0.026	0.079	0.088	0.209	1.311

3	MAE	2.113×10³	1.618×10⁴	3.770×10⁴	1.229×10⁵	9.596×10⁴
3	RMSE	2.229×10²	2.804×10³	4.734×10³	2.898×10⁴	2.127×10⁴

4	MAE	0.607	1.017	2.722	7.566	10.310
4	RMSE	0.064	0.207	0.390	1.684	2.148

5	MAE	595.65	626.430	716.89	850.15	5.388×10³
5	RMSE	55.850	59.830	72.502	88.230	201.104

6	MAE	6.912×10⁷	8.511×10⁷	3.299×10⁸	6.728×10⁹	5.728×10¹¹
6	RMSE	6.546×10⁶	7.932×10⁶	2.758×10⁷	9.310×10⁷	7.272×10¹⁰

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Non⁃hierarchical multi⁃model fusion order reduction based on aerodynamic and aerothermodynamic characteristics for cross⁃domain morphing aircraft

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