Direct Drive Rotor Motor for Rotary-Wing Aircraft
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Solution Overview
Problem
Conventional rotary-wing aircraft rely on mechanical drive trains and hydraulic systems, which increase weight, maintenance requirements, and complexity, necessitating a more efficient power transmission and propulsion system.
Innovation Solution
An electric propulsion system featuring a static mast, a stationary rotor hub assembly, an electric motor with a stator and rotor assembly, and a power generation system using electromagnetic coils and permanent magnets, eliminating the need for traditional gearboxes and hydraulic systems by integrating an over-running clutch and elastomeric gimbal for reduced weight and maintenance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a mechanical drive train with gearboxes and hydraulic systems is used, then power transmission is achieved, but aircraft weight increases and maintenance requirements increase
Solution Approach 1:
The patent extracts and eliminates the mechanical gearbox and hydraulic systems from the helicopter drive train, replacing them with an electric motor system. The electric motor is directly coupled to the rotor, removing the need for complex mechanical transmission components and thereby reducing aircraft weight while maintaining power transmission capability
Solution Approach 2:
The patent substitutes the mechanical drive train system with an electric propulsion system. The electric motor replaces the engine-gearbox-mechanical transmission system, and electrical power transmission replaces hydraulic power transmission, thereby eliminating heavy mechanical components and reducing overall aircraft weight
2Power
If a mechanical drive train with gearboxes and hydraulic systems is used, then power transmission is achieved, but device complexity increases
Solution Approach 1:
The patent removes the complex mechanical gearbox and hydraulic systems from the drive train, extracting only the essential power transmission function and implementing it through a simpler electric motor system with direct rotor coupling, thereby reducing device complexity
Solution Approach 2:
The patent merges the functions of the engine, gearbox, and hydraulic systems into a single integrated electric motor system. The electric motor directly couples to the rotor, combining multiple separate mechanical and hydraulic systems into one unified electrical propulsion system, thereby reducing overall complexity
3Power
If a mechanical drive train with gearboxes and hydraulic systems is used, then power transmission is achieved, but maintenance requirements increase
Solution Approach 1:
The patent extracts and eliminates the maintenance-intensive mechanical gearbox and hydraulic systems, replacing them with an electric motor system that has fewer moving parts and no hydraulic fluid, thereby reducing maintenance requirements while maintaining power transmission
Solution Approach 2:
The patent substitutes the mechanical and hydraulic systems with an electric propulsion system that eliminates gears, belts, hydraulic pumps, and fluid lines, thereby removing the components that require the most maintenance and improving ease of repair
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
The electric propulsion system reduces aircraft weight, maintenance costs, and complexity by eliminating mechanical gearboxes and hydraulic systems, providing a more efficient and reliable power transmission system for rotary-wing aircraft.
Implementation Method 1
The rotor assembly includes at least one permanent magnet arranged circumferentially about the static mast and supported by the rotating system, the at least one permanent magnet being generally aligned with the at least one electromagnetic coil
Implementation Method 2
The rotating system includes a rotor head associated with an over-running clutch
Data Source
AI summary
An electric propulsion system includes a static mast defining an axis of rotation and a stationary rotor hub assembly coupled to the static mast. A rotating system is rotatably mounted to the stationary rotor hub assembly. The electric propulsion system additionally includes an electric motor including a stator assembly associated with the rotor hub assembly and a rotor assembly associated with the rotating system.