基于综合评价的BWB无人机总体方案优化

索欣诗; 王宇; 朱正

doi:10.13700/j.bh.1001-5965.2023.0250

基于综合评价的BWB无人机总体方案优化

doi: 10.13700/j.bh.1001-5965.2023.0250

索欣诗^1, ,,
王宇²,
朱正¹

1.
南京工业职业技术大学航空工程学院，南京 210023
2.
南京航空航天大学航空学院，南京 210016

基金项目: 南京工业职业技术大学引进人才科研启动基金(YK22-03-01)

详细信息

通讯作者:
E-mail：suoxs@niit.edu.cn

中图分类号: V221
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出版历程
- 收稿日期: 2023-05-15
- 录用日期: 2023-08-18
- 网络出版日期: 2023-09-07
- 整期出版日期: 2025-02-28

Overall scheme optimization of BWB UAVs based on comprehensive evaluation

SUO Xinshi^{1
, ,},
WANG Yu²,
ZHU Zheng¹

1.
School of Aeronautical Engineering，Nanjing Vocational University of Industry Technology，Nanjing 210023，China
2.
College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Funds: Start-up Fund for New Talented Researchers of Nanjing Vocational University of Industry Technology (YK22-03-01);

More Information

Corresponding author: E-mail：suoxs@niit.edu.cn

摘要

摘要:
为提高翼身融合(BWB)布局无人机(UAVs)总体方案优化设计效率，根据翼身融合布局无人机外形和性能特点，建立了适用于概念设计阶段无人机总体方案的多学科综合分析模型、综合评价模型和优化模型，并开发了相应工具。采用数值分析和工程方法相结合，完成翼身融合布局无人机总体方案的几何、质量、气动和隐身特性分析。采用改进的逼近理想解排序法(TOPSIS)，从无人机的装载能力、经济性和适应性角度出发，建立综合评价模型。以多个无人机方案为算例，验证了分析模型的合理性。利用可并行的子集模拟优化算法，以巡航升阻比最大和前向雷达散射截面积(RCS)最小为目标完成传统多目标优化，以竞争力最强为目标完成基于综合评价的方案优化。以多目标优化过程产生的全部方案为基础完成参数相关性分析，验证展长、后掠角和扭转角对气动和隐身特性的影响。最终的多目标优化方案RCS降低了41.6%，巡航升阻比提高了3.5%；综合评价优化方案的竞争力得分提高了44.0%。
- 翼身融合 /
- 无人机 /
- 概念设计 /
- 综合评价 /
- 优化
Abstract:
To improve the overall scheme optimization efficiency of blended wing body (BWB) unmanned aerial vehicles (UAVs), a model involving multi-disciplinary analysis, comprehensive evaluation, and optimization suitable for the overall scheme of UAVs in the conceptual design stage was established, in consideration of the geometric and performance characteristics of BWB UAVs. Additionally, corresponding tools were developed. The analysis of geometry, mass, aerodynamics, and stealth characteristics of the BWB UAVs in the overall scheme was performed by combining numerical analysis with engineering methods. An improved TOPSIS method was adopted to establish a comprehensive evaluation model concerning payload capacity, economy, and adaptability of UAVs. The rationality of the analysis model was verified by using several UAV schemes as calculation cases. A parallelizable subset simulation optimization algorithm was utilized to perform a traditional multi-objective optimization with the objectives of maximizing the cruise lift-to-drag ratio and minimizing the forward radar cross section (RCS), and scheme optimization based on the comprehensive evaluation was achieved with the goal of realizing the optimal competitiveness. Based on all schemes generated during the multi-objective optimization process, a parameter correlation analysis was completed, verifying the impact of wingspan, sweep angle, and twist angle on aerodynamic and stealth characteristics. The final multi-objective optimization scheme achieves a 41.6% reduction in RCS and a 3.5% increase in cruise lift-to-drag ratio. The competitiveness score of the optimization scheme based on comprehensive evaluation was improved by 44.0%.
- blended-wing-body /
- UAV /
- conceptual design /
- comprehensive evaluation /
- optimization

HTML全文

图 1 BWB无人机综合评价和优化模型

Figure 1. Comprehensive evaluation and optimization model of BWB UAVs

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图 2 几何建模GUI

Figure 2. GUI for geometric modeling

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图 3 BWB无人机模型

Figure 3. Model of a BWB UAV

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图 4 理想化模型

Figure 4. Idealized model

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图 5 面元法气动分析

Figure 5. Aerodynamic analysis using panel method

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图 6 σ_RCS计算模型

Figure 6. Model for σ_RCS calculation

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图 7 指标归一化

Figure 7. Index normalization

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图 8 群组权重计算流程图

Figure 8. Group weight calculation flowchart

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图 9 优化流程图

Figure 9. Flowchart for optimization

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图 10 极曲线

Figure 10. Polar cuves

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图 11 升阻比特性曲线

Figure 11. Characteristic curves of lift-to-drag ratio

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图 12 不同状态下的σ_RCS分布

Figure 12. σ_RCS distribution under different states

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图 13 方案1模型

Figure 13. Model for scheme 1

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图 14 方案1升阻比特性曲线

Figure 14. Characteristic curves of lift-to-drag ratio for scheme 1

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图 15 方案1σ_RCS分布

Figure 15. σ_RCS distribution for scheme 1

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图 16 参数相关性分析

Figure 16. Analysis of parameters correlation

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图 17 Pareto解集

Figure 17. Pareto solution set

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表 1 理想解

Table 1. Ideal solutions

理想解	载荷质量/kg	总质量/kg	(L/D)_cru	σ_RCS/m²
正	45	150	19	0.003
负	20	200	15	0.010

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表 2 判断矩阵随机一致性指标值

Table 2. Random index values of judging matrix

n	I_RI	n	I_RI
3	0.52	7	1.36
4	0.89	8	1.41
5	1.12	9	1.46
6	1.26	10	1.49

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表 3 几何参数

Table 3. Geometric parameters

部件	半展长/m	后掠角/（°）	梢根比	上反角/（°）
中央翼	0.45	60.0	0.71	0
內翼内段	0.45	60.0	0.55	0
內翼外段	0.23	37.3	0.77	0
外翼	2.10	37.3	0.59	0
小翼	0.27	69.0	0.60	68.5

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表 4 特征参数

Table 4. Characteristic parameters

模型	参考面积/m²	平均气动弦长/m	浸润面积/m²
本文	7.04	1.49	16.67
文献[20]	6.80		16.28
注：参考面积偏差、浸润面积偏差分别为3.5%、2.4%。

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表 5 质量分析结果

Table 5. Results of mass analysis kg

模型	空机结构质量	推进系统质量	系统设备质量	载荷质量	燃油质量	起飞总质量
本文	69.64	14.55	17.99	35.0	31.25	168.43
文献[20]	110.79			35.0	31.25	177.03
注：推进系统质量偏差、载荷质量偏差、燃油质量偏差、起飞总质量偏差分别为110.79%、35.0%、31.25%、177.03%。

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表 6 综合评价参数值

Table 6. Parameters for comprehensive evaluation

参数	载荷质量	总质量	σ_RCS	(L/D)_cru
指标权重	0.459 8	0.131 5	0.121 6	0.287 1
正理想解	0.952 6	0.952 6	0.952 6	0.952 6
负理想解	0.047 4	0.047 4	0.047 4	0.047 4
评价对象	0.645 7	0.687 5	0.457 2	0.599 9

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表 7 方案1几何参数

Table 7. Geometric parameters for scheme 1

部件	半展长/m	后掠角/(°)	梢根比	上反角/(°)	扭转角/(°)
中央翼	0.60	59.70	0.741	0	2.570
內翼内段	0.59	59.70	0.657	0	0.420
內翼外段	0.45	29.96	0.916	0	−0.073
外翼	4.06	29.96	0.173	0	−0.657
小翼	0.60	57.78	0.341	60.02	0

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表 8 方案1分析结果

Table 8. Analysis results for scheme 1

模型	参考面积/m²	起飞质量/kg	(L/D)_cru	σ_RCS/m²
本文	19.4	2 076.38	19.10	0.004 5
文献[23]	20.0	2 000.00	19.88	0.001 4
偏差/%	−3.0	3.8	−3.9	221

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表 9 方案2分析结果

Table 9. Analysis results for scheme 2

模型	参考面积/m²	起飞质量/kg	(L/D)_cru	σ_RCS/m²
本文	19.0	2 070.87	18.13	0.004 2
文献[23]	20.0	2 000.00	18.34	0.002 3
偏差/%	−5.0	3.5	−1.1	82.6

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表 10 方案3分析结果

Table 10. Analysis results for scheme 3

模型	参考面积/m²	起飞质量/kg	(L/D)_cru	σ_RCS/m²
本文	19.48	2 121.5	17.11	0.004 4
文献[23]	20.00	2 000.0	18.38	0.002 4
偏差/%	−2.6	6.1	−6.9	83.3

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表 11 初始方案与Pareto解集对比

Table 11. Comparison between initial scheme and Pareto solution set

方案	σ_RCS/m²	(L/D)_cru
初始	0.006 70	17.27
方案1	0.003 87	17.53
方案2	0.003 91	17.88
方案3	0.004 86	18.12
方案4	0.005 19	18.69

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表 12 初始方案与优化方案对比

Table 12. Comparison between initial scheme and optimization design

指标	初始	优化后
机身半展长/m	0.45	0.36
机身前缘后掠角/（°）	60.0	55.1
外翼半展长/m	2.10	1.81
外翼前缘后掠角/（°）	37.3	36.50
外翼梢根比	0.59	0.54
外翼扭转角/（°）	0	−0.24
载荷质量/kg	35.00	41.31
总质量/kg	168.95	164.74
σ_RCS/m²	0.006 7	0.004 4
(L/D)_cru	17.40	18.32
竞争力	0.624 4	0.899 2

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