电动复合四旋翼无人机总体多学科优化设计方法

张航; 黄盈卓

doi:10.7652/xjtuxb202308015

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电动复合四旋翼无人机总体多学科优化设计方法

智能制造 | 更新时间：2025-05-08

- 电动复合四旋翼无人机总体多学科优化设计方法
- Multidisciplinary Design Optimization for an Electric Quadrotor Fixed-Wing Hybrid Unmanned Air Vehicle
- 西安交通大学学报 2023年57卷第8期页码：148-160
- 作者机构：
  
  1. 长安大学工程机械学院,西安,710064
  2. 重庆凯瑞机器人技术有限公司,重庆,400799
- 作者简介：
  
  : 2022-12-22。作者简介: 张航(1991—),男,讲师。基金项目: 国家自然科学青年基金资助项目(52202435)
- 基金信息：
  
  : 2022-12-22。作者简介: 张航(1991—),男,讲师。基金项目: 国家自然科学青年基金资助项目(52202435);中央高校基本科研业务费资助项目(300102252102)。
- DOI：10.7652/xjtuxb202308015
  中图分类号： TP221
- 网络首发：2023-08-10，
  
  纸质出版：2023
- 稿件说明：
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张航, 黄盈卓. 电动复合四旋翼无人机总体多学科优化设计方法[J]. 西安交通大学学报, 2023,57(8):148-160.

ZHANG Hang, HUANG Yingzhuo. Multidisciplinary Design Optimization for an Electric Quadrotor Fixed-Wing Hybrid Unmanned Air Vehicle[J]. 2023, 57(8): 148-160.
张航, 黄盈卓. 电动复合四旋翼无人机总体多学科优化设计方法[J]. 西安交通大学学报, 2023,57(8):148-160. DOI： 10.7652/xjtuxb202308015.

ZHANG Hang, HUANG Yingzhuo. Multidisciplinary Design Optimization for an Electric Quadrotor Fixed-Wing Hybrid Unmanned Air Vehicle[J]. 2023, 57(8): 148-160. DOI： 10.7652/xjtuxb202308015.

摘要

为解决当前电动复合四旋翼无人机设计中存在的布局选择缺乏理论依据、缺少旋翼模式下的抗风性能的分析和评估方法、两套动力系统独立进行设计和总体设计过程多数采用传统序列设计方法而未充分考虑几何外形、气动、配平和稳定性、动力系统、质量、旋翼模式下的抗风性能和续航性能等学科之间参数相互传递带来的复杂耦合关系等问题

根据所提基于代理模型的改进并行子空间优化算法

通过建立几何外形参数化模型和气动网格划分模型、各个飞行模式下的气动性能和飞行性能分析模型、旋翼模式下抗风性能的评估和分析模型以及已经提出的电动力系统模型

形成了电动复合四旋翼无人机的多学科优化设计(MDO)方法

并将该方法应用于一架小型电动复合四旋翼无人机的总体设计当中

基于优化设计结果制作了原理样机。原理样机的飞行实验结果显示飞行性能均满足设计要求

并且在起飞总质量降低约为2.8%的情况下

航时提升了约14.1%

最大可抗风速提升了约3.5%

表明了所提MDO方法的可行性和正确性

可为电动复合四旋翼无人机产品的研发和应用提供一定的理论指导。

Abstract

This paper addresses issues in the current design of electric quadrotor fixed-wing hybrid unmanned air vehicles(EH-UAVs)

including a lack of theoretical basis for the layout configuration selection

a lack of analysis and evaluation methods for the wind disturbance rejection capability in the quadrotor mode

the issue that design methods for the electric propulsion systems of most EH-UAVs are to design the quadrotor system and fixed-wing system independently

and the issue that design methods for the conceptual design are mainly the traditional sequence design methods without fully considering the complex coupling relationships caused by the mutual transfer of parameters between various disciplines such as geometric shape

aerodynamics

trimming and stability

propulsion system

weight

wind disturbance rejection capability in the quadrotor mode

and endurance performance. Based on the proposed improved surrogate model based concurrent subspace optimization(CSSO)architecture

this paper establishes a multidisciplinary optimization(MDO)method for the conceptual design of EH-UAVs. This is accomplished by building geometric shape parameterization models and aerodynamic grid division models

aerodynamic and flight performance analysis models for different flight modes

evaluation and analysis models for wind disturbance rejection capability in the quadrotor mode

and the proposed electric propulsion system models. The proposed MDO method and the discipline analysis models are applied to the conceptual design process of a small EH-UAV. A prototype of the EH-UAV is fabricated based on the MDO results. The flight test results of the prototype show that the flight performance meets the design requirements

and with a 2.8% reduction in takeoff weight

the endurance time is improved by approximately 14.1%

and the maximum wind speed that the EH-UAV can resist is increased by approximately 3.5%. This verifies the feasibility and correctness of the MDO method proposed in this article

which can provide guidance for the research and application of EH-UAVs.

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references

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