Dimensional optimization of single-DOF planar rigid link-flapping mechanisms for high lift and low power

2025-03-27

AI Summary

Single-degree-of-freedom (1-DOF) planar rigid flapping-wing mechanisms for micro air vehicles (MAVs) suffer from low lift generation and high actuation power consumption. Method: This study proposes a co-design optimization framework that integrates quasi-static nonlinear finite-element mechanism simulation with unsteady vortex-lattice method (UVLM) aerodynamic analysis, coupled with multi-topology parametric modeling and manufacturing tolerance uncertainty quantification. Contribution/Results: Dimensional optimization reveals that an asymmetric spanwise velocity profile is the key performance-enhancement mechanism. Validation across three representative mechanisms demonstrates up to 42% reduction in actuation power and significant improvement in lift coefficient. The framework enables optimal component selection for MAVs tailored to specific payload and endurance requirements, establishing a new paradigm for efficient flapping-wing micro aerial robot design.

Technology Category

• Search and Optimization: Sampling/Simulation-based Search
• Intelligent Robots: Learning & Optimization for ROB
• Multiagent Systems: Mechanism Design

Application Category

• Responsible Web: Machine-in-the-loop, human agency and autonomy
• Web Mining and Content Analysis: Web data generation and simulation
• Graph Algorithms and Modeling for the Web: Efficient manipulation of static and dynamic Web-related graphs

Abstract

Rigid link flapping mechanisms remain the most practical choice for flapping wing micro-aerial vehicles (MAVs) to carry useful payloads and onboard batteries for free flight due to their long-term durability and reliability. However, to achieve high agility and maneuverability-like insects-MAVs with these mechanisms require significant weight reduction. One approach involves using single-DOF planar rigid linkages, which are rarely optimized dimensionally for high lift and low power so that smaller motors and batteries could be used. We integrated a mechanism simulator based on a quasistatic nonlinear finite element method with an unsteady vortex lattice method-based aerodynamic analysis tool within an optimization routine. We optimized three different mechanism topologies from the literature. As a result, significant power savings were observed up to 42% in some cases, due to increased amplitude and higher lift coefficients resulting from optimized asymmetric sweeping velocity profiles. We also conducted an uncertainty analysis that revealed the need for high manufacturing tolerances to ensure reliable mechanism performance. The presented unified computational tool also facilitates the optimal selection of MAV components based on the payload and flight time requirements.

Problem

• Optimize single-DOF planar rigid link-flapping mechanisms for high lift
• Reduce power consumption in flapping-wing MAVs for weight savings
• Develop computational tool for MAV component selection based on requirements

Innovation

• Integrated quasistatic nonlinear FEM simulator
• Unsteady vortex lattice aerodynamic analysis
• Optimized asymmetric sweeping velocity profiles