Simulation Study on Optimization Method of Design Parameters for Transwave Stealth Wing Skin

doi:10.3969/j.issn.1009-086x.2022.02.007

Abstract

Abstract:

In order to obtain good aerodynamic and stealth performance at the same time， based on the principle of combining shape stealth technology with material stealth technology， a design scheme of wing skin based on wave transmission is proposed. In order to balance the relationship between the lift force and the electromagnetic stealth performance of the wave transmitting wing， a surrogate model based strategy is adopted to optimize the geometric parameters of the wave transmitting wing. The results show that after optimization， the transonic wing can maintain good RCS （radar cross section） reduction characteristics in frequency domain and spatial domain and have enough lift conditions. The proposed proxy model has high accuracy， and can be used as an effective means to balance interdisciplinary problems in engineering.

Key words: wave transparent wing, stealth, radar cross section （RCS）, lift force, surrogate model, optimization

摘要：

为同时获得良好的气动和隐身性能，基于外形隐身技术与材料隐身技术相结合的原理，提出了一种以透波为主的机翼蒙皮设计方案；为平衡透波机翼升力与机翼电磁隐身性能之间的关系，采用一种基于代理模型的策略，对透波机翼外形几何特征参数进行了优化设计。研究结果表明，经过优化后，透波机翼在频域、空域范围内保持良好的雷达散射截面（RCS）减缩特性的同时可具备足够的升力条件。所提出的代理模型精准度高，在工程上平衡跨学科领域问题时，可作为一种有效手段。

关键词: 透波机翼, 隐身, 雷达散射截面（RCS）, 升力, 代理模型, 优化

CLC Number:

V218

Tian-li YU, Wen-feng DONG, Wen-jian LIU, Ya FAN. Simulation Study on Optimization Method of Design Parameters for Transwave Stealth Wing Skin[J]. Modern Defense Technology, 2022, 50(2): 45-52.

于天立, 董文锋, 刘文俭, 范亚. 透波隐身机翼蒙皮设计参数优化方法仿真研究[J]. 现代防御技术, 2022, 50(2): 45-52.

Figures/Tables 14

Fig.1 Wing diagram

Fig.2 Schematic diagram of incidence angle

Fig.3 Flow chart of geometric parameter optimization method for wave transparent wing based on surrogate model

Fig.4 Linear regression relationship between the predicted value of surrogate model and the measured value of sample scheme

Table1 Root mean square error analysis after normalization

目标变量	y₁	y₂	y₃	y₄	y₅	y₆	y₇
L	0.086 3	0.144 6	0.053 8	0.104 7	0.073 2	0.085 6	0.047 8

Table2 Values of variables after optimization

设计变量	x₁/m	x₂/m	x₃/m	x₄/m	x₅/m	x₆/（°）
优化后取值	0.834 4	0.819 8	0.291 9	1.249 4	0.438 2	57.421 8

Table3 Comparison of optimization results and verification results

目标变量	y₁/dBsm	y₂/dBsm	y₃/dBsm	y₄/dBsm	y₅/dBsm	y₆/dBsm	y₇/N
优化结果	-66.69	-71.92	-62.89	-63.30	-59.65	-60.11	5 114.74
验证结果	-66.19	-68.88	-60.97	-63.37	-58.01	-60.12	5 023.84
差值	0.50	3.04	1.92	0.07	1.64	0.01	90.90

Table4 Comparison between optimization results and RCS simulation data of metal wing

目标变量	y₁/dBsm	y₂/dBsm	y₃/dBsm	y₄/dBsm	y₅/dBsm	y₆/dBsm
优化结果	-66.69	-71.92	-62.89	-63.30	-59.65	-60.11
金属机翼	-13.52	-7.95	-19.05	-18.91	-24.10	-24.53
差值	53.17	63.97	43.84	44.39	35.55	35.58

Fig.5 Relationship between design variables and RCS at 0.5GHz

Fig.6 Relationship between lift and design variables

Fig.7 Relationship between RCS and sweep angle in azimuth incidence range at 0.5 GHz

Fig.8 Relationship between RCS and wing chord length in azimuth incidence range at 0.5 GHz

Fig.9 Relationship between RCS and sweep angle at 0.5 GHz

Fig.10 Relationship between wing lift and design variables

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