Perpendicular Motor Propulsion Assembly for Aircraft Wings
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Solution Overview
Problem
Existing electric propulsion systems for aircraft, such as e-Propeller systems, face integration challenges due to large motor diameters and lengths, which increase space requirements and penalize aerodynamic performance, especially when multiple motors are needed to meet power requirements.
Innovation Solution
A propulsion assembly with electric motors positioned perpendicular to the propeller axis, allowing for orientation along the wing direction, reducing drag, and enabling efficient power transmission using bevel gears and mechanical reduction gears, while maintaining a compact footprint.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If electric motors are arranged with axes parallel to the propeller axis, then power transmission is simplified, but the wing thickness must be increased locally along the entire engine length, increasing drag
Solution Approach 1:
The patent changes the spatial arrangement by positioning motor axes perpendicular to the propeller axis rather than parallel, allowing motors to be embedded in the wing's planform area rather than requiring increased thickness along the engine length, thus reducing drag while maintaining power transmission capability through bevel gears
2Power
If multiple electric motors are used to meet power requirements, then power output increases, but the number of motors with significant diameters and lengths increases, making integration complex
Solution Approach 1:
The patent merges multiple motor assemblies into a unified propulsion system where multiple motors share common structural elements and mounting arrangements within the wing, reducing overall integration complexity despite increasing power output through multiple units
Solution Approach 2:
By orienting motor axes perpendicular to the propeller axis, the patent enables motors to be arranged in a planar configuration within the wing's surface area rather than requiring significant thickness, facilitating the integration of multiple motors without proportionally increasing complexity
3Force
If motors with reducers are used, then torque is increased, but the size of the propulsion system increases considerably, penalizing aerodynamic performance
Solution Approach 1:
The patent replaces traditional mechanical reducer systems with direct-drive electric motors that generate sufficient torque electronically, eliminating the need for bulky mechanical gear reductions while maintaining the required torque output for propeller drive
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 optimizes the integration of electric motors within the aircraft wing, improving aerodynamic performance and allowing for multiple motors to be used without increasing the overall size, thus enhancing the propulsion system's efficiency and power output.
Implementation Method 1
The drive shaft of each of the electric motors carries a motor bevel gear, and the propeller shaft carries at least one propeller bevel gear meshing with the motor bevel gear carried by the drive shaft of each of the electric motors
Data Source
Figure 1~2
Figure 3~4B
Figure 5~6B
AI summary
Propulsion assembly (1, 1', 1'') for an aircraft, comprising at least two electric motors (20, 30) configured to be arranged in a wing (110) of the aircraft and each comprising a rotor having a motor shaft (22 , 32) which is movable around an engine axis (X), at least one propeller (10) supported by a propeller shaft (12) which is movable around a propeller axis (A) and mechanically coupled to the motor shaft (22, 32) of the at least two electric motors (20, 30), the propeller axis (A) being perpendicular to the motor axis (X) of the at least two electric motors (20, 30).