民用飞机机身壁板复杂试验载荷优化技术

doi:10.7527/S1000-6893.2022.27989

Abstract

Abstract:

Aiming at the problem of load prediction in the strength test of composite fuselage panel of civil aircraft， we construct an optimization model of the test load based on the strain error matrix， and predict the test load using the multi-dimensional minima optimization algorithm. Firstly， based on the load form of the fuselage panel in the test device， the finite element model of the fuselage panel and the test device was established， and the strain matrix of the fuselage panel under each test reference load calculated. Secondly， the fuselage panel strain error matrix was constructed based on the difference between the strain matrices of the fuselage panel under the full fuselage load state and the test state， and considering the weighting coefficients of each element in the matrix. With the minimum sum of squares of all terms in the strain error matrix as the objective， each reference load coefficient as the optimization variable， and the upper and lower limits of each reference load coefficient as the constraints， the reference load coefficient optimization function was constructed. The optimization function was then processed unconstrained based on the penalty function method， and the reference load coefficients obtained by the steepest gradient method. Finally， based on the optimized load， the strain of the fuselage panel under the composite load of the test was calculated. Compared with the strain of the fuselage panel under the full fuselage load， the distribution trend of the strain was basically the same with the strain error within 10%， proving that this method can provide support for the determination of the test load of the fuselage panel.

Key words: composite material, fuselage plate, test device, strain error matrix, test load factor, multi-dimensional extreme value optimization

CLC Number:

V223

Yuchao GUO, Likai WANG, Xigui SUN, Xiaohua NIE. Optimization technology for complex test load of civil fuselage panel[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 227989-227989.

Figures/Tables 11

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Table 1

Fig.9

Fig.10

References 24

1	WALKER T H， MINGUET P J， FLYNN B W，et al. Advanced technology composite fuselage—structural performance：NASA contractor report 4732［R］. Washington，D.C.：NASA，1997.
2	BISAGNI C， VESCOVINI R， DÁVILA C G. Single-stringer compression specimen for the assessment of damage tolerance of postbuckled structures［J］. Journal of Aircraft， 2011， 48（2）： 495-502.
3	汪厚冰，林国伟，韩雪冰，等. 复合材料帽形加筋壁板剪切屈曲性能［J］. 航空学报， 2019， 40（8）： 222889.
	WANG H B， LIN G W， HAN X B， et al. Shear buckling performance of composite hat-stiffened panels［J］. Acta Aeronautica et Astronautica Sinica， 2019， 40（8）： 222889 （in Chinese）.
4	李真，王俊，邓凡臣，等. 复合材料机身壁板的强度分析与试验验证［J］. 航空学报， 2020， 41（9）： 223688.
	LI Z， WANG J， DENG F C， et al. Strength analysis and test verification of composite fuselage panels［J］. Acta Aeronautica et Astronautica Sinica， 2020， 41（9）： 223688 （in Chinese）.
5	ACCARDO A， RICCI F， LUCARIELLO D， et al. Design of a combined loads machine for tests on fuselage barrels and curved panels［C］∥ 45th AIAA/ASME/ASCE/AHS/ASC Structures， Structural Dynamics & Materials Conference. Reston， Virginia： AIAA， 2004： 1628.
6	ROUSE M. Methodologies for combined loads tests using a multi-actuator test machine［C］∥ Experimental Mechanics of Composite， Hybrid， and Multifunctional Materials， Volume 6. Cham： Springer， 2014： 205-214.
7	ANDREW E L. Configuration and sizing of a test fixture for panels under combined loads： NASA/CR-2006-214520［R］.Washington，D.C.：NASA，2006.
8	BAKUCKAS J G.Full-scale testing and analysis of fuselage structure containing multiple cracks：DOT/FAA/AR-01/46［R］. Washington，D.C.：FAA，2002.
9	The Boeing Company. E-fixture：US7246527B2［P］.2007-07-24.
10	IMA. The number one address for structural and material testing in the aerospace industry［Z/OL］. .
11	王彬文，陈向明，邓凡臣，等. 飞机壁板复杂载荷试验技术［J］. 航空学报， 2022， 43（3）： 024987.
	WANG B W， CHEN X M， DENG F C， et al. Complex load test technology for aircraft panels： review［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（3）： 024987 （in Chinese）.
12	陈安，魏玉龙，廖江海，等. 机身加筋壁板复合加载损伤容限性能试验［J］. 航空学报， 2017， 38（1）： 420093.
	CHEN A， WEI Y L， LIAO J H， et al. Damage tolerance test of stiffened fuselage panel under complex load［J］. Acta Aeronautica et Astronautica Sinica， 2017， 38（1）： 420093 （in Chinese）.
13	臧伟峰，董登科，王俊安.一种大型机身壁板复杂载荷静力/疲劳试验装置：CN103149075A［P］.2015-01-28.
	ZANG W F， DONG D K， WANG J A. A static/fatigue test fixture for complex load of large fuselage panel： CN103149075A［P］.2015-01-28 （in Chinese）.
	臧伟锋，张海英，陈安，等. 一种机身壁板剪切载荷试验装置： CN114705565A［P］. 2022-07-05.
	ZANG W F， ZHANG H Y， CHEN A， et al. Fuselage wallboard shear load test device： CN114705565A［P］. 2022-07-05 （in Chinese）.
14	柴亚南，邓凡臣，李崇，等. 一种机身壁板复合载荷试验装置： CN104807694B［P］. 2018-01-30.
	NAN C Y， DENG F C， LI C， et al. Fuselage panel combined load test device： CN104807694B［P］. 2018-01-30 （in Chinese）.
15	邓凡臣，柴亚南，薛会民，等.大型飞机机身曲板多轴载荷试验技术研究［J］.实验力学，2018，33（3）：484-490.
	DENG F C， CHAI Y N， XUE H M，et al.On the experimental technique for large aircraft fuselage curved panel subjected to multiaxial loading［J］.Journal of Experimental Mechanics， 2018， 33（3）： 484-490 （in Chinese）.
16	中国飞机强度研究所.一种曲板直边约束加载装置：CN202010554450.0［P］. 2020-10-13.
	Aircraft Strength Research Institute of China.A loading device with straight edge constraint for curved panel：CN202010554450.0［P］. 2020-10-13 （in Chinese）.
17	李崇，柴亚南，王彬文，等. 大型机身壁板复杂应力场试验技术［J］. 航空学报， 2022， 43（6）： 526409.
	LI C， CHAI Y N， WANG B W， et al. Test technology for complex stress field of large scale fuselage panel［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（6）： 526409 （in Chinese）.
18	郭瑜超，孙喜桂，王立凯，等. 一种曲板试验载荷计算方法： CN110135044A［P］. 2019-08-16.
	GUO Y C， SUN X G， WANG L K， et al. Curved plate test load calculation method： CN110135044A［P］. 2019-08-16 （in Chinese）.
19	赵鑫，郑晓玲. 复合材料机身大开口壁板静力试验载荷设计［J］. 机械设计与制造工程， 2021， 50（9）： 58-62.
	ZHAO X， ZHENG X L. Load design for static test of the composite fuselage panel［J］. Machine Design and Manufacturing Engineering， 2021， 50（9）： 58-62 （in Chinese）.
20	王彬文，段世慧，聂小华，等. 航空结构分析CAE软件发展现状与未来挑战［J］. 航空学报， 2022， 43（6）： 527272.
	WANG B W， DUAN S H， NIE X H， et al. Development situation and future challenges of CAE software used in aeronautical structural analysis［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（6）： 527272 （in Chinese）.
21	何坚勇. 最优化方法［M］. 北京：清华大学出版社， 2007： 318-323.
	HE J Y. Optimization method［M］. Beijing： Tsinghua University Press， 2007： 318-323 （in Chinese）.
22	陈宝林. 最优化理论与算法［M］. 2版. 北京：清华大学出版社， 2005： 76-81.
	CHEN B L. Optimization theory and algorithm［M］. 2nd ed. Beijing： Tsinghua University Press， 2005： 76-81 （in Chinese）.
23	唐焕文，秦学志. 实用最优化方法［M］. 3版. 大连：大连理工大学出版社， 2004： 89-92.
	TANG H W， QIN X Z. Practical methods of optimization［M］. 3rd ed. Dalian： Dalian University of Technology Press， 2004： 89-92 （Chinese）.
24	郭瑜超，聂小华，张生贵，等. 航空结构仿真与试验应变一致性评估方法［J］. 机械强度， 2020， 42（1）： 246-250.
	GUO Y C， NIE X H， ZHANG S G， et al. Consistency evaluation of the aircraft structural simulation and test［J］. Journal of Mechanical Strength， 2020， 42（1）： 246-250 （in Chinese）.

序号	载荷类型	基准载荷	优化后的载荷系数
1	轴向载荷	1.15×106 N	0.762 5
2	弯曲载荷	1×106 N	0.198 4
3	剪流载荷	250 N/mm	0.071 2
4	垂向剪切载荷	1×105 N	3.484 5
5	气密载荷	0.137 8 MPa	1.000 0
6	V型框架载荷	2×105 N	0.614 0
7	1号地板梁上地板载荷	-14 520 N	0.937 8
8	1号地板梁下地板载荷	10 220 N	0.775 8
9	2号地板梁上地板载荷	-16 817 N	1.403 8
10	2号地板梁下地板载荷	-1 088 N	1.057 6
11	3号地板梁上地板载荷	-4 8501 N	0.527 5
12	3号地板梁下地板载荷	-6 967 N	1.374 9
13	4号地板梁上地板载荷	-23 432 N	-0.012 5
14	4号地板梁下地板载荷	2 348 N	1.077 9
15	5号地板梁上地板载荷	-36 977 N	0.437 2
16	5号地板梁下地板载荷	67 182 N	-0.470 4
17	6号地板梁上地板载荷	-2 392 N	0.530 1
18	6号地板梁下地板载荷	10 634 N	2.272 3
19	7号地板梁上地板载荷	-12 185 N	1.349 4
20	7号地板梁下地板载荷	8 165 N	0.747 6
21	8号地板梁上地板载荷	-15 667 N	1.102 5
22	8号地板梁下地板载荷	-1 050 N	1.032 0
23	9号地板梁上地板载荷	-14 350 N	0.956 8
24	9号地板梁下地板载荷	10 188 N	0.875 5

[1]	Zhiting GAO, Zhuang MA, Yanbo LIU. Effect of CVD-SiC array structure on ablation resistance of ZrB₂/SiC coatings [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(3): 428842-428842.
[2]	Qian YANG, Yanzhe WANG, Di YANG, Zezhong LI, Weiwei QU. Prediction and planning of automatic laying speed for fiber reinforced composite materials based on data⁃driven model [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(10): 429313-429313.
[3]	Jian HAN, Shiyong SUN, Bin NIU, Rui YANG, Dongjiang WU. Progress in manufacturing technologies of resin⁃based composite lattice structures [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(9): 628255-628255.
[4]	Liping LIU, Yuyang QI, Yueguo LIN, Rui BAO, Jianxin XU, Zhenyu FENG, Guanghui QING. Tensile failure of carbon fiber composite material bonded-rivet hybrid repaired structure [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(24): 428676-428676.
[5]	Dong WU, Hong YANG, Wenfeng ZHAO, Yue LUO. High temperature strain measurement of hypersonic aircraft carbon-based composite material structures [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 160-169.
[6]	RAN Qingbo, XIAO Hong, YANG Fuhong, DUAN Yugang. Trajectory planning algorithm for automatic wire laying on perforated surface [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 425602-425602.
[7]	WAN Aoshuang. Probabilistic assessment on damage tolerance of composite helicopter horizontal tail structure [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 525557-525557.
[8]	WANG Yupeng, LYU Shuaishuai, YANG Yu, LI Jiaxin, WANG Yezi. Damage recognition of composite structures based on domain adaptive model [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 526752-526752.
[9]	ZHANG Jiabo, ZHANG Kaihu, FAN Hongtao, LU Mingyu, GAO Ze, ZHANG Xiaohui. Progress in laser processing of fiber composite materials and prospects of its applications in aerospace [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(4): 525735-525735.
[10]	PENG Zhenlong, ZHANG Xiangyu, ZHANG Deyuan. High-speed ultrasonic vibration cutting for difficult-to-machine materials in aerospace field [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(4): 525587-525587.
[11]	LI Dichen, LU Zhongliang, TIAN Xiaoyong, ZHANG Hang, YANG Chuncheng, CAO Yi, MIAO Kai. Additive manufacturing—Revolutionary technology for leading aerospace manufacturing [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(4): 525387-525387.
[12]	GAO Wei, LIU Cun, CHEN Shunqiang. Axial compression test and analysis method of composite stiffened plates with variable thickness [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526764-526764.
[13]	YAN Chuliang. Development and prospect of aircraft structural life reliability assessment technology in China [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(10): 527869-527869.
[14]	TONG Zixiang, LI Mingjia, LI Dong. Multiscale analysis and numerical model for coupled conduction-radiation heat transfer [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(9): 625729-625729.
[15]	ZOU Tianchun, LI Longhui, LIU Zhihao, FU Ji, JU Yuezhang. Effect of overlap length on strain distribution and failure law of CFRP-Al double lap joint [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(6): 224921-224921.

Optimization technology for complex test load of civil fuselage panel

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 11

References 24

Related Articles 15

Recommended Articles

Metrics

Comments