Propulsor Cyclic Control for Electric Aircraft
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Solution Overview
Problem
Edgewise flight causes non-axial strain on rotors and drive systems of aircraft, leading to expediated aging and wear, and existing solutions are insufficient.
Innovation Solution
A system and method for propulsor cyclic control on an electric aircraft, which includes a motor, a propulsor with solid blades, and a cyclic that varies the angle of attack of the propulsor as a function of its rotational position.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If edgewise flight is performed, then the aircraft can achieve certain flight maneuvers, but non-axial strain occurs on rotors and drive systems causing expediated aging and wear
Solution Approach 1:
The patent applies cyclic control to dynamically adjust the pitch angle of propeller blades during rotation. The pitch angle varies continuously throughout the rotation cycle, being higher when the blade is in the advancing position and lower when in the retreating position. This dynamic adjustment mitigates non-axial strain forces during edgewise flight while maintaining maneuverability, thereby resolving the contradiction between flight versatility and drive system reliability.
2Reliability
If cyclic control is implemented to mitigate edgewise flight forces, then stress and wear on rotors and drive systems are reduced, but device complexity increases
Solution Approach 1:
The cyclic control system is integrated into the existing propulsor structure, utilizing the rotational motion of the propeller itself to drive the pitch adjustment mechanism. The system leverages the inherent dynamics of the propulsor operation rather than requiring separate complex actuation mechanisms, thereby reducing overall system complexity while achieving the desired stress mitigation.
Data Source
AI summary
Disclosed herein are systems and methods for propulsor cyclic control. Propulsor cyclic control may be used to reduce asymmetric loads in aircraft flight. A system for propulsor cyclic control may include an electric aircraft comprising a motor, a propulsor, and a cyclic. Cyclic may be controlled passively or actively.