Propeller Blade Retention Using Magnetic Arrays
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Solution Overview
Problem
Conventional aircraft components, particularly in electric propulsion systems, face challenges such as frequent wear, heat generation, vibration, noise, and the need for efficient noise and vibration management, especially in densely populated areas, along with the requirement for safe and reliable operation in various environments, including vertiports and restricted spaces.
Innovation Solution
The development of a distributed electric propulsion system with tiltable forward engines and fixed aft engines, combined with a propeller blade retention system that includes a hub, retention sleeve, bearings, and a cap to manage centrifugal and bending loads, ensuring the propellers can withstand operational stresses while minimizing weight and drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional aircraft components are used in electric propulsion systems, then the system can achieve basic propulsion function, but the components experience frequent wear and generate excessive heat and vibration
Solution Approach 1:
The patent replaces conventional mechanical fastening systems with a magnetic retention system using magnet arrays and magnetic couples. This substitution eliminates mechanical wear between moving parts while maintaining secure blade attachment, thereby improving reliability without increasing heat generation from friction
Solution Approach 2:
The patent changes the operational parameters of the retention system by using magnetic field strength instead of mechanical clamp force. The magnetic couples can be engaged and disengaged without physical contact, reducing wear and heat generation while maintaining the necessary retention force for propeller blade attachment
2Strength
If conventional propeller retention systems are used, then the structure is simple, but the system cannot withstand frequent centrifugal and bending loads from tilting operations
Solution Approach 1:
The retention system is segmented into multiple independent magnetic arrays distributed around the propeller hub, with each array containing multiple magnets. This segmentation allows the load to be distributed across multiple retention points, enabling the system to withstand centrifugal and bending loads from tilting operations while maintaining a relatively simple overall structure
Solution Approach 2:
The magnetic retention system provides counteracting forces through magnetic attraction to balance the centrifugal and bending loads experienced during tilting operations. The magnetic couples create holding forces that counterweight the dynamic loads, enabling the propeller to withstand frequent tilting operations without requiring complex mechanical reinforcement
3Reliability
If distributed electric propulsion system is implemented, then safety is improved through redundancy, but the system generates more noise and vibration requiring management mechanisms
Solution Approach 1:
The magnetic retention system replaces mechanical fastening mechanisms that generate noise and vibration during operation. By using magnetic fields instead of mechanical contact and friction, the system reduces noise and vibration generation while maintaining the safety benefits of distributed propulsion redundancy
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This configuration enables efficient, quiet, and reliable operation of electric aircraft, capable of vertical takeoff and landing, with reduced noise and vibration, and improved safety through distributed propulsion and effective load management, allowing for frequent use in dense urban environments.
Implementation Method 1
a first bearing disposed between the second portion of the retention sleeve and the inner surface of the hub, the first bearing having a first race contacting the inner surface of the hub. Some disclosed embodiments include a second bearing disposed between the first portion of the retention sleeve and the inner surface of the hub, the second bearing having a second race contacting the inner surface of the hub
Implementation Method 2
a propeller for an aircraft... configured to retain the propeller blade... capable of withstanding operational stresses including centrifugal and bending loads
Implementation Method 3
configured to retain the propeller blade... capable of withstanding operational stresses including centrifugal and bending loads
Data Source
AI summary
Apparatus, systems, and methods for a propeller blade retention system. The retention system may include a hub including a socket formed by an inner surface of the hub, a blade extending into the socket and a retention sleeve having a first portion and a second portion. The retention system may include a filler sleeve disposed between the blade and the second portion of the retention sleeve, a first bearing disposed between the second portion of the retention sleeve and the inner surface of the hub, the first bearing having a first race, and a second bearing disposed between the first portion of the retention sleeve and the inner surface of the hub, the second bearing having a second race. The retention system may include a cap comprising a body portion and a flange portion. The retention system may include a shim carrier.