[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

Journal of Projectiles, Rockets, Missiles and Guidance >

2022 , Vol. 42 >Issue 6: 79 - 84

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2022.06.012

Research on Lightweight Design of Aircraft Plate Components Based on Response Surface

  • YANG Hui ,
  • WANG Qi ,
  • HE Guoyi ,
  • ZHANG Xiaoxin ,
  • CHEN Longsheng
Expand
  • School of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China

Received date: 2022-05-25

  Online published: 2025-02-25

Fold

Abstract

In order to reduce the weight of a solid missile tail, simulate the beam rib structure in the wing of plane to optimize it. Remove the internal area on the basis of maintaining the appearance, reinforce the hollow area by adding stiffeners. Determine the number of stiffeners through preliminary design, and then use the method of standard quadratic polynomial to fit response surface function of stiffener position and width to maximum stress, maximum deformation and mass, further optimize the parameters according to the response surface. The optimization results show that on the premise that the maximum deformation and maximum stress remain basically unchanged, the mass is reduced by 25.67%, and have a good lightweight effect, it can be used as a reference for the lightweight design of solid missile tail.

Key words： lightweight; finite element calculation; response surface optimization; missile tail; stiffener

Cite this article

YANG Hui , WANG Qi , HE Guoyi , ZHANG Xiaoxin , CHEN Longsheng . Research on Lightweight Design of Aircraft Plate Components Based on Response Surface[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2022 , 42(6) : 79 -84 . DOI: 10.15892/j.cnki.djzdxb.2022.06.012

[an error occurred while processing this directive]

References

Publishing order | Descend order by publishing year | Descend order by cited within
[1]
李士静. 某型导弹铸造弹翼的优化设计[J]. 洪都科技, 1992(4):1-6.

[2]
张刚, 李洪波, 文世珍, 等. 某型号弹翼结构拓扑优化设计[J]. 科学技术创新, 2019(6):39-40.

[3]
温晶晶, 吴斌, 刘承骛. 导弹整体式翼面骨架结构的拓扑优化设计[J]. 兵工学报, 2017, 38(1):81-88.

DOI

[4]
吴元琦. 飞行器舵翼结构的仿生轻量化设计及其力学性能研究[D]. 南京: 南京航空航天大学, 2017.

[5]
周子童. 高刚度薄壁结构的多级加筋拓扑优化研究[D]. 大连: 大连理工大学, 2020.

[6]
LI Q H, QU Y X, LUO Y F, et al. Concurrent topology optimization design of stiffener layout and cross-section for thin-walled structures[J]. Acta Mechanica Sinica, 2021, 37(3): 472-481.

[7]
林纯景. 机翼筋板结构拓扑、尺寸和形状综合优化设计[EB/OL]. (2017-07-13)[2022-04-15]. https://kns.cnki.net/KCMS/detail/detail.aspx?dbcode=CPFD&filename=ATER201707001026.

[8]
MARTINEZ D W, ESPINO M T, CASCOLAN H M, et al. A comprehensive review on the application of 3D printing in the aerospace industry[J]. Key Engineering Materials, 2022, 16(8): 244-272.

[9]
周长省, 鞠玉涛, 朱福亚. 火箭弹设计理论[M]. 北京: 北京理工大学出版社, 2014.

[10]
杨小兰, 刘极峰, 陈旋. 基于ANSYS的有限元法网格划分浅析[J]. 煤矿机械, 2005, 26(1):38-39.

[11]
王宇, 卢玲, 李文韬. 基于Ansys的有限元网格划分方法应用研究[J]. 起重运输机械, 2014, 469(3):53-56.

[12]
张涛. 基于植物叶脉形态的板壳结构加强筋设计[D]. 赣州: 江西理工大学, 2016.

[13]
FLORENT S, FRANÇOIS X I, CÉDRIC J, et al. A component-based method for the optimization of stiffener layout on large cylindrical rib-stiffened shell structures[J]. Structural and Multidisciplinary Optimization, 2021, 64(4): 1843-1861.

[14]
柴山, 尚晓江, 刚宪约, 等. 工程结构优化设计方法与应用[M]. 北京: 中国铁道出版社, 2015.

[15]
张运真, 徐康, 赵亚东, 等. 基于ANSYS Workbench自动换料车床电主轴多目标优化设计[J]. 机械设计与制造, 2021, 369(11):197-201.

[16]
肖粤翔. 非参数响应曲面方法研究及应用[D]. 天津: 天津大学, 2004.

Options
Outlines

/

〈 〉

[an error occurred while processing this directive]