Fixed-Motor Electric Tiltrotor Drive for Mode Conversion
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Solution Overview
Problem
Existing electric vertical takeoff and landing (eVTOL) aircraft, particularly electric tiltrotor aircraft, face challenges in efficiently converting between helicopter and airplane modes due to the need for flexible motor positioning, which complicates the propulsion system and can interfere with passenger safety and heat management.
Innovation Solution
A drive system for electric tiltrotor aircraft featuring fixed electric motors relative to the wing, coupled with a tiltable gearbox and rotor assembly, allowing for seamless conversion between helicopter and airplane modes while maintaining motor stability and reducing interference.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If flexible motor positioning is used to enable conversion between helicopter and airplane modes, then adaptability is improved, but device complexity increases and heat management becomes more difficult
Solution Approach 1:
The propulsion system is divided into separate functional components: fixed motors mounted to the wing structure and movable rotor assemblies that can be tilted independently. This segmentation allows the motors to remain stationary while the rotor mast and blades are tilted between vertical (helicopter mode) and horizontal (airplane mode) positions, enabling mode conversion without requiring the entire propulsion system to move.
Solution Approach 2:
The patent combines the motor mounting structure with the wing structure, creating an integrated assembly where motors are fixed to the wing. This merging eliminates the need for separate motor positioning mechanisms and simplifies the overall structure while maintaining the ability to convert between flight modes through rotor mast tilting only.
2Adaptability or versatility
If flexible motor positioning is used to enable mode conversion, then adaptability is improved, but passenger safety is compromised due to interference
Solution Approach 1:
By separating the motor mounting function from the rotor tilting function, the patent ensures that motors remain in fixed, safe positions away from moving rotor components. This segmentation eliminates potential safety hazards associated with motors moving into positions that could interfere with passengers or other critical systems during mode conversion.
3Adaptability or versatility
If flexible motor positioning is used, then adaptability is improved, but heat management becomes more difficult due to increased interference
Solution Approach 1:
The fixed motor positioning created by segmentation allows for dedicated heat management pathways and clearance zones. Motors remain in consistent locations where heat dissipation can be optimized through fixed mounting structures and consistent airflow paths, avoiding the heat management issues that would arise from motors moving through different positions during mode conversion.
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
Enables efficient conversion between helicopter and airplane modes with improved motor stability and reduced heat interference, enhancing safety and operational flexibility.
Implementation Method 1
at least one electric motor for providing rotational energy to a motor shaft
Implementation Method 2
a gearbox connected to the motor shaft for receiving rotational energy from the at least one electric motor via the motor shaft and providing rotational energy to the rotor mast via a rotor shaft
Data Source
AI summary
A rotor system for an aircraft includes a rotor assembly comprising a plurality of rotor blades connected to a rotor mast, wherein the rotor assembly is tiltable relative to a wing of the aircraft between a first position corresponding to an airplane mode of the aircraft and a second position corresponding to a helicopter mode of the aircraft; and a drive system for providing rotational energy to the rotor assembly via the rotor mast. The drive system includes at least one electric motor for generating rotational energy to a motor shaft; and a gearbox connected to receive rotational energy from the at least one electric motor via the motor shaft and to provide rotational energy to the rotor mast via a rotor shaft, wherein the at least one electric motor is fixed relative to the wing of the aircraft.