Flight Performance and Dynamics Analysis Methods of Highly Flexible Unmanned Aerial Vehicles

WANG Jiachen; ZHOU Zhou; WANG Rui

doi:10.12382/bgxb.2026.0032

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Flight Performance and Dynamics Analysis Methods of Highly Flexible Unmanned Aerial Vehicles

更新时间：2026-08-12

- Flight Performance and Dynamics Analysis Methods of Highly Flexible Unmanned Aerial Vehicles
- Acta Armamentarii (2026)
- 作者机构：
  
  西北工业大学航空学院, 陕西西安 710072
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2026.0032
  CLC： TJ301
- Received：09 January 2026，
  
  Revised：2026-08-10，
  
  Accepted：10 August 2026，
- 稿件说明：
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WANG Jiachen, ZHOU Zhou, WANG Rui. Flight Performance and Dynamics Analysis Methods of Highly Flexible Unmanned Aerial Vehicles[J/OL]. Acta Armamentarii, 2026.
DOI：

WANG Jiachen, ZHOU Zhou, WANG Rui. Flight Performance and Dynamics Analysis Methods of Highly Flexible Unmanned Aerial Vehicles[J/OL]. Acta Armamentarii, 2026. DOI： 10.12382/bgxb.2026.0032.

摘要

在执行军事侦察、通信中继等任务时，大柔性无人机因其长续航、低成本等特点受到广泛关注，但显著的几何非线性变形增加了全包线飞行性能评估和动力学特性分析的难度。在已有本征梁建模与模型降阶研究的基础上，本文建立结构–飞行动力学耦合模型，并采用全局搜索与序列二次规划相结合的混合优化算法，在给定安全约束条件下计算飞行包线内的多项性能指标，通过与刚性基准模型对比，分析柔性变形对飞行性能的影响。针对高维动力学模型计算与模态辨识困难的问题，采用奇异摄动法进行模型降阶，并将应变能相对变化率作为表征结构变形相似程度的指标，用于比较不同配平构型下的动力学特性。数值结果表明，结构变形相似程度与系统特征根和特征向量的变化具有明显关联；在本文所考察的工况和变形约束范围内，相关动力学特性随基准飞行状态呈现较为连续的演化趋势。所建立的分析流程可为大柔性无人机飞行性能与动力学特性的评估提供参考。

Abstract

Highly flexible unmanned aerial vehicles (UAVs) have attracted considerable attention because of their long endurance and low operating cost. However

significant geometrically nonlinear deformation increases the difficulty of evaluating full-envelope flight performance and analyzing dynamic characteristics. Based on existing studies of intrinsic-beam modeling and model order reduction

a coupled structural–flight-dynamics model is established. A hybrid optimization method combining global search and sequential quadratic programming is employed to calculate multiple performance metrics over the flight envelope under prescribed safety constraints. By comparison with a rigid reference model

the effects of flexible deformation on flight performance are analyzed. To reduce the computational burden and facilitate modal identification for the high-dimensional dynamic model

the singular perturbation method is adopted for model order reduction. Relative strain-energy variation is introduced as an indicator of similarity between trim configurations and is used to compare the local dynamic characteristics of different trim states. Numerical results show an evident association between structural-deformation similarity and variations in eigenvalues and eigenvectors. Within the investigated operating conditions and deformation-constraint range

the relevant dynamic characteristics exhibit relatively continuous variation with the baseline flight condition. The proposed analysis procedure can provide a reference for evaluating the flight performance and dynamic characteristics of highly flexible UAVs.

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references

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