A high-confidence helicopter rotor fluid-structure-sound coupling calculation method, system and device
CN121525573BActive Publication Date: 2026-08-28NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Patent Information
- Application Number
- CN202511699624.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-18
- Publication Date
- 2026-08-28
- Estimated Expiration
- 2045-11-18
AI Technical Summary
Technical Problem
[0004]目前，现有技术体系在旋翼流-固-声耦合建模中难以实现计算效率与分析精度的兼顾，亟需建立新型流-固-声多场耦合分析模型，以实现旋翼动力学特性与声辐射特性的精细化协同分析，破解当前效率与精度失衡的技术瓶颈
Benefits of technology
[0009]根据本申请提供的具体实施例，本申请公开了以下技术效果：本申请将桨叶气动力作为动载荷传递至桨叶动力学模型，推进一个时间步并计算桨叶弹性响应；同时引进配平模型，依据桨叶气动力分布，推进一个时间步，并更新旋翼操纵量；通过上述配平模型的引入，根据实时载荷与桨叶变形状态动态更新操纵量，突破了传统方法中控制参数固定或滞后调整的局限，确保旋翼始终处于贴近真实运行的动态平衡工况。当动载荷与桨叶弹性响应收敛时，根据预设周期内的动载荷分布及桨叶弹性响应计算旋翼总噪声，使预测结果能充分反映各系统耦合作用下的噪声生成机制，更贴合旋翼实际运行中的噪声辐射特性。当动载荷与桨叶弹性响应未收敛时，依据桨叶弹性响应更新桨叶模型的桨叶外形及表面面元状态，然后推进一个时间步，并根据更新后的旋翼操纵量调整桨叶模型的运动状态，通过旋翼尾迹模型生成新涡粒子，进而更新桨叶气动力分布，然后返回将桨叶气动力作为动载荷传递至所述桨叶动力学模型的步骤，进入下一次迭代；通过这样的处理，构建出“气动-结构-配平”三者在同一时间步的同步推进机制。相较于传统耦合中需等待动力学收敛后再传递参数的模式，该流程彻底避免了中间传参的时间损耗，使噪声计算模块能实时获取高保真的流-固耦合数据，在提升整体计算效率的同时，保障了噪声预测与动态流场的时间同步性。
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Figure CN121525573B_ABST
Abstract
The application discloses a high-confidence helicopter rotor fluid-structure-sound coupling calculation method, system and device, relates to the technical field of helicopter design, and comprises the following steps: transferring the blade aerodynamic force to the blade dynamics model as a dynamic load, advancing a time step and calculating the blade elastic response; meanwhile, a trim model is introduced, a time step is advanced according to the blade aerodynamic force distribution and the rotor control quantity is updated; when the dynamic load and the blade elastic response converge, the total noise of the rotor is calculated according to the dynamic load distribution and the blade elastic response in a preset period; when the convergence is not achieved, the blade shape and the surface element state of the blade model are updated according to the blade elastic response, a time step is advanced, the motion state of the blade model is adjusted according to the updated rotor control quantity, new vortex particles are generated through a rotor wake model, the blade aerodynamic force distribution is updated, and the next iteration is entered. The application can balance the accuracy and efficiency in the rotor fluid-structure-sound coupling analysis.
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Citation Information
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