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Characterization and Thermal Management of a DC Motor-Driven Resonant Actuator for Miniature Mobile Robots with Oscillating Limbs

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arxiv 2002.00798 v1 pith:TWSQMIA2 submitted 2020-01-24 eess.SP cs.ROcs.SYeess.SY

classification eess.SPcs.ROcs.SYeess.SY
keywords actuatorthermaldesignmodelmotor-drivenperformancecharacterizationdeveloped
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In this paper, we characterize the performance of and develop thermal management solutions for a DC motor-driven resonant actuator developed for flapping wing micro air vehicles. The actuator, a DC micro-gearmotor connected in parallel with a torsional spring, drives reciprocal wing motion. Compared to the gearmotor alone, this design increased torque and power density by 161.1% and 666.8%, respectively, while decreasing the drawn current by 25.8%. Characterization of the actuator, isolated from nonlinear aerodynamic loading, results in standard metrics directly comparable to other actuators. The micro-motor, selected for low weight considerations, operates at high power for limited duration due to thermal effects. To predict system performance, a lumped parameter thermal circuit model was developed. Critical model parameters for this micro-motor, two orders of magnitude smaller than those previously characterized, were identified experimentally. This included the effects of variable winding resistance, bushing friction, speed-dependent forced convection, and the addition of a heatsink. The model was then used to determine a safe operation envelope for the vehicle and to design a weight-optimal heatsink. This actuator design and thermal modeling approach could be applied more generally to improve the performance of any miniature mobile robot or device with motor-driven oscillating limbs or loads.

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  1. System Identification of Thrust and Torque Characteristics for a Bipedal Robot with Integrated Propulsion

    cs.RO 2025-04 conditional novelty 3.0 of 10

    The paper fits a thrust equation with two empirical constants and measures the KV380 motor torque constant as 0.0311 Nm/A, but the thrust validation depends on fitted parameters and a coarse 200-node CFD.

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