设计可变形无人机MetaMorpher，兼顾垂直起降与高效巡航
Design and Aerodynamic Modeling of MetaMorpher: A Hybrid Rotary andFixed-Wing Morphing UAV
- 采用分段翼结构和非线性动力学模型，支持灵活构型测试
- 在Simulink中验证多种飞行模式，模型表现稳定可靠
- 适合快速原型设计与多构型评估，适用于新型无人机研发
本文提出一种通用、全面的非线性数学模型与概念设计，用于MetaMorpher——一种可变形无人飞行器（UAV），旨在弥合垂直起降灵活性与固定翼巡航效率之间的差距。基于成功设计的spincopter平台，本工作采用轻质材料与新型机翼折叠策略，构建简化机械架构。不同于传统刚体近似，我们推导出非线性飞行动力学模型，支持对分段机翼结构进行任意力分布建模。该模块化设计使同一环境中可测试不同翼型、质量分布与弦长配置。作为本研究的一部分，多种飞行模式在Simulink环境中被具体测试与分析。结果表明，该模型在不同结构配置下表现出可预测行为，证明其作为快速设计评估工具的可靠性。
原文摘要 · Abstract (English)
In this paper, we present a generalized, comprehensive nonlinear mathematical model and conceptual design for the MetaMorpher, a metamorphic Unmanned Aerial Vehicle (UAV) designed to bridge the gap between vertical takeoff and landing agility and fixed-wing cruising efficiency. Building on the successful design of the spincopter platform, this work introduces a simplified mechanical architecture using lightweight materials and a novel wing-folding strategy. Unlike traditional rigid-body approximations, we derive a nonlinear flight dynamics model that enables arbitrary force distributions across a segmented wing structure. This modularity allows for testing different airfoils, mass distributions, and chord lengths in a single environment. As part of this work, various flight modes were specifically tested and analyzed in the Simulink environment. The results show that the model behaves predictably under different structural configurations, demonstrating its reliability as a tool for rapid design evaluation.
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