基于PRSEUS结构的翼身融合民机中央机体球亏面框优化设计方法

doi:10.7527/S1000-6893.2023.29331

Abstract

Abstract:

The Blended Wing Body （BWB） layout is an unconventional subsonic transport aircraft configuration. To address the design challenges of the aft pressure frame in this layout， this paper conducts optimization design work on the central fuselage circumferential frame using NASA’s proposed Pultruded Rod Stitched Efficient Unitized Structure （PRSEUS） concept. Finite element models are separately established for a certain type of BWB aircraft's aluminum flat frame and the PRSEUS pherical deficient surfaces frame. Numerical simulations and comparisons reveal that the PRSEUS pherical deficient surfaces frame exhibits superior load-bearing performance and lower structural weight. Building upon this， the paper performs further sensitivity analysis on the PRSEUS pherical deficient surfaces frame， identifying influential parameters related to its static strength and stability， and summarizing the impact patterns. By analyzing the effects of key parameters in the collaborative optimization process， a synergy optimization strategy based on surrogate models is developed， known for its strong applicability and high efficiency. Employing this collaborative optimization approach， the paper optimizes the dimensions of the PRSEUS pherical deficient surfaces frame. Through a thorough optimality analysis of the results， an optimized solution that balances static strength and stability is achieved， reducing the weight of the PRSEUS pherical deficient surfaces frame by 10.6%. The designed PRSEUS pherical deficient surfaces frame excels in load-carrying efficiency and stability， whichoffers valuable insights to designers and researchers in related fields.

Key words: BWB civil aircraft, aft pressure frame, PRSEUS structure, surrogate model, collaborative optimization

CLC Number:

V223

Yongjie ZHANG, Jingpiao ZHOU, Lei SHI, Dong LI, Binqian ZHANG. Optimization design method of central fuselage spherical deficient surface frames in blended⁃wing⁃body civil aircraft based on PRSEUS structure[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(12): 229331-229331.

Figures/Tables 47

Fig.1

Fig.2

Table 1

Table 2

Fig.3

Table 3

7075 aluminum alloy parameter

参数	取值
弹性模量 $E$ /MPa	71 000
泊松比 $μ$	0.33
密度 $ρ$ /（kg·m^-3）	2 700
抗拉强度 $σ s$ /MPa	524
屈服强度 $σ b$ /MPa	455

Table 3

Fig.4

Fig.5

Fig.6

Table 4

Composite material properties［16］

参数	取值
纵向弹性模量 $E 1$ /MPa	67 154.93
横向弹性模量 $E 2$ /MPa	33 542.99
厚度方向弹性模量 $E 3$ /MPa	34 956.42
$纵向横向剪切模量 G 12$ /MPa	16 340.57
纵向厚度方向剪切模量 $G 13$ /MPa	16 340.57
横向厚度方向剪切模量 $G 23$ /MPa	5 515.81
纵向横向泊松比 $μ 12$	0.4
纵向厚度方向泊松比 $μ 13$	0.4
横向厚度方向泊松比 $μ 23$	0.095
密度 $ρ$ /（kg·m^-3）	1 600

Table 4

Table 5

Material properties of pultruded rod and foam core［16］

参数	取值
拉挤杆弹性模量 $E a$ /MPa	126 932.48
泡沫芯弹性模量 $E b$ /MPa	144.79
拉挤杆泊松比 $μ a$	0.30
泡沫芯泊松比 $μ b$	0.45
拉挤杆密度 $ρ a$ /（kg·m^-3）	1 600.0
泡沫芯密度 $ρ b$ /（kg·m^-3）	99.9

Table 5

Fig.7

Fig.8

Fig.9

Table 6

Table 7

Strength value of composite materials［16］

参数	取值
$X t$ /MPa	724.64
$X c$ /MPa	546.06
$Y t$ /MPa	320.61
$Y c$ /MPa	261.31
$S 12$ /MPa	206.15

Table 7

Fig.10

Fig.11

Fig.12

Fig.13

Table 8

Fig.14

Table 9

Fig.15

Fig.16

Fig.17

Fig.18

Fig.19

Fig.20

Fig.21

Fig.22

Table 10

Accuracy of surrogate models for static strength of spherical deficient surfaces frame

模型	$R M S E$	$R 2$	$M A E$
Kriging	0.155 73	0.687 84	0.325 46
RBF	0.018 53	0.995 98	0.039 98
PRS	0.106 48	0.873 28	0.268 86

Table 10

Fig.23

Table 11

Accuracy of surrogate model for stability of spherical deficient surfaces frame

模型	$R M S E$	$R 2$	$M A E$
Kriging	0.041 76	0.980 09	0.102 62
RBF	0.046 70	0.974 16	0.102 88
PRS	0.136 46	0.714 97	0.463 67

Table 11

Fig.24

Fig.25

Fig.26

Table 12

Physical meaning of each design variable

物理意义	稳定性学科级变量	静强度学科级变量	系统级变量
球皮	$x 1$	$y 1$	$z 1$
长桁腹板	$x 2$	$y 2$	$z 2$
拉挤杆	$x 3$	$y 3$	$z 3$
止裂带	$x 4$	$y 4$	$z 4$
端盖	$x 5$
包裹层	$x 6$
环框		$y 5$

Table 12

Fig.27

Table 13

Fig.28

Fig.29

Table 14

Table 15

Fig.30

Table 16

Table 17

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参数	取值
乘客数量/座	300
燃油质量/kg	76 000
最大起飞质量/kg	210 000
航程/km	13 000
巡航马赫数	0.84
翼展/m	63.12
纵横比	0.65

部段	质量/kg	占比/%
前机身	3 000	1.4
中机身	30 000	14.3
后机身	3 000	1.4
机翼	8 000	3.8
连接件	6 000	2.9
全机	50 000	23.8
最大起飞重量	210 000	100.0

部件	层数	单层厚度/mm	总厚度/mm
球皮	10	1.320 8	13.208
长桁腹板	9	1.320 8	11.887
止裂带	9	1.320 8	11.887
端盖	6	1.320 8	7.924 8
包裹层	1	1.320 8	1.320 8
环框	16	1.320 8	21.133

序号	质量/t	蔡-吴失效因子	一阶屈曲特征值
1	1.183	0.911 4	1.775
2	1.177	0.925 7	1.693
3	1.192	0.894 7	1.646
4	1.180	0.988 5	1.702
5	1.195	0.940 8	1.882
6	1.190	0.936 7	1.762
7	1.187	0.971 1	1.768
8	1.186	0.920 7	1.832
9	1.193	0.892 9	1.703

部件	层数	总厚度/mm	单层厚度/mm
球皮	10	13.828	1.382 8
长桁腹板	9	5.944	0.660 4
止裂带	9	5.944	0.660 4
端盖	6	6.050	1.008 3
包裹层	1	0.721	0.721 0
环框	16	23.187	1.449 2

Optimization design method of central fuselage spherical deficient surface frames in blended⁃wing⁃body civil aircraft based on PRSEUS structure

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球亏面框部件	层合板数目
球皮	10
长桁腹板	9
长桁止裂带	9
隔框包裹层	1
隔框止裂带	9
环框	16
端盖	6

变量	球皮/mm	长桁腹板/mm	止裂带/mm	端盖/mm	包裹层/mm	环框/mm	拉挤杆/mm
改变量/%	4.69	-50	-50	-23.66	-45.41	9.72	-23.55
优化前	1.320 8	1.320 8	1.320 8	1.320 8	1.320 8	1.320 8	10.000 0
优化后	1.382 8	0.660 4	0.660 4	1.008 3	0.721 0	1.449 2	7.645 0

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