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摘要:
针对模块化可重构机翼结构的优化设计问题,以沿展向分布的3个翼段模块为研究对象,研究了不同翼展方案机翼的载荷相关性,通过在优化迭代过程中自动调整设计空间,解决了模块化可重构机翼优化设计时复杂的变量-约束耦合影响问题,建立了适用于模块化可重构机翼结构的分步补偿优化方法。以某无人机模块化可重构机翼结构优化设计问题为例,建立了优化模型,并分别采用所提分步补偿优化方法和传统单方案优化方法进行了优化设计。结果表明:所提方法能够稳定收敛,与单方案优化结果相比较,所提方法以较小的重量代价满足了3种重构方案的所有设计要求,且优化结果具有较好的工程实用性。
Abstract:For optimization of the modular reconfigurable airfoil structures, three wing modules that distributed along the span direction are taken as research object, and the correlations of load among airfoils with different wingspan are investigated. The complex coupling effects between variables and constraints are resolved by adjusting the design space during iteration automatically. A step-compensation optimization method is proposed for design of the modular reconfigurable airfoil structure. Optimization model of airfoil structures from a modular UAV is established and optimization design is conducted using both the step-compensation method and the traditional single scheme optimization method. The results show that using the proposed method can achieve steady convergence, and compared with the results from single scheme optimization method, the final design in this paper can meet all the design requirements of those three reconfiguration schemes with limited cost of weight, and keep better practicability in engineering.
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Key words:
- modular /
- reconfigurable /
- airfoil structures /
- step-compensation /
- structural optimization
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表 1 无人机3种重构方案总体设计参数
Table 1. General design parameters of three UAV reconfiguration schemes
飞机参数 重构方案1 重构方案2 重构方案3 起飞重量/kg 680 625 600 实用升限/m 8 000 6 500 5 000 机翼面积/m2 7.5 6.1 5 机翼翼展/m 11 8 6 最大正过载 3.8 3.5 4.5 最大负过载 -2.5 -2.7 -3.5 安全系数 1.3 1.3 1.3 表 2 符号及定义
Table 2. Definition of symbols
符号 定义 V1 模块1的结构设计变量 V2 模块2的结构设计变量 V3 模块3的结构设计变量 CON1 机翼重构方案1的约束条件 CON2 机翼重构方案2的约束条件 CON3 机翼重构方案3的约束条件 W1 模块1的重量 W2 模块2的重量 W3 模块3的重量 LC1 机翼重构方案1对应的工况 LC2 机翼重构方案2对应的工况 LC3 机翼重构方案3对应的工况 表 3 优化目标结果统计
Table 3. Optimization objective result statistics
模块编号 本文方法模块重量/
kg单方案优化重构方案1 单方案优化重构方案2 单方案优化重构方案3 模块重量/kg 比率/
%模块重量/kg 比率
/%模块重量/kg 比率
/%1 49.03 47.16 3.81 46.65 4.85 46.73 4.69 2 8.94 8.33 6.82 7.90 11.63 — — 3 6.64 6.64 0 — — — — 表 4 模块1上蒙皮厚度设计变量优化结果统计
Table 4. Optimization result statistics of thickness design variables belonging to top skin of Module 1
变量编号 上蒙皮厚度设计变量值/mm 本文方法 单方案优化重构方案1 单方案优化重构方案2 单方案优化重构方案3 TU1 4.22 4.13 4.26 4.05 TU2 4.71 4.66 4.58 4.61 TU3 4.14 3.91 4.11 4.06 TU4 3.75 3.65 3.55 3.71 TU5 3.81 3.77 3.71 3.77 TU6 3.45 3.22 3.42 3.44 TU7 2.84 2.64 2.62 2.71 TU8 3.16 3.04 2.94 2.85 TU9 2.55 2.55 2.45 2.46 TU10 2.54 2.34 2.42 2.34 TU11 2.73 2.62 2.52 2.42 TU12 2.41 2.31 2.38 2.31 TU13 2.31 2.24 2.14 2.05 TU14 2.70 2.56 2.46 2.17 TU15 2.30 2.26 2.23 2.04 -
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