eVTOL Wing Tilt Actuation With Non-Parallel Rotors to Cut Weight
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Solution Overview
Problem
Existing VTOL aircraft face challenges such as high weight due to redundant actuator systems, limited flight range due to energy-intensive electric motors, and restricted landing capabilities on non-hardstand surfaces, which hinder their usability for both commercial and military applications.
Innovation Solution
The design incorporates a VTOL aircraft with a fuselage and wings featuring electric rotors with non-parallel axes of rotation, allowing for efficient wing tilt and reduced weight through a boxed wing structure and strategically mounted motors, enabling operation on various surfaces and improved flight efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional tilt wing actuation systems with redundant actuators and bearings are used, then reliability is improved, but weight increases significantly
Solution Approach 1:
The actuation system is divided into multiple independent electric motors, each controlling a specific rotor or wing section. This segmentation allows for distributed control where failure of one motor does not compromise the entire system, maintaining reliability while using lighter individual motor units compared to traditional single-point actuation with redundancy.
Solution Approach 2:
The invention integrates the actuation function directly into the wing structure itself, combining the wing support function with the tilt actuation function. The wing structure serves dual purposes as both the load-bearing element and the actuation mechanism, eliminating separate bearing assemblies and reducing overall system weight while maintaining reliability through structural integration.
2Power
If encased fan type motors are used for take-off and landing, then vertical lift capability is achieved, but energy consumption increases and flight range is reduced
Solution Approach 1:
The system dynamically adjusts rotor orientation from vertical to horizontal based on flight phase. During take-off and landing, rotors are positioned vertically to generate vertical lift. During forward flight, rotors tilt horizontally to generate forward thrust. This dynamic reconfiguration optimizes energy efficiency across different flight regimes, reducing overall energy consumption while maintaining vertical lift capability when needed.
Solution Approach 2:
The invention changes the operational parameters of the electric motors by varying rotor orientation and pitch angle according to flight conditions. This parameter adjustment allows the same motor system to operate efficiently in both vertical lift mode and forward flight mode, optimizing energy consumption across the entire flight envelope rather than being locked into a single high-energy configuration.
3Speed
If fixed wing configuration is used, then forward flight speed is maintained, but take-off and landing are restricted to hardstand surfaces
Solution Approach 1:
The wing configuration is made dynamic through variable pitch control surfaces and adjustable rotor orientation. The control surfaces can change their angle of attack dynamically during flight, and the rotors can tilt between vertical and horizontal positions. This dynamic adaptability allows the aircraft to operate from various surface types including soft ground, while maintaining forward flight speed performance through optimized aerodynamic configurations.
Solution Approach 2:
The wing structure is designed with multi-functionality, serving as both the primary lift-generating surface and the mounting structure for rotors and control surfaces. The control surfaces on the wings provide both aerodynamic control during forward flight and structural support for rotor mounting during vertical flight modes. This universal design enables operation across diverse surface types while maintaining forward flight capabilities.
4Adaptability or versatility
If actuators and bearings are added to control wing inclination, then tilt capability is achieved, but device complexity increases
Solution Approach 1:
The actuation function is merged with the wing structure itself. The wings are designed with integrated pivot points and mounting structures that allow rotation and tilting without requiring separate bearing assemblies. The wing support structure serves dual purposes as both the load-bearing element and the rotation mechanism, reducing device complexity while maintaining tilt capability.
Solution Approach 2:
Traditional complex bearing assemblies and actuation mechanisms are extracted and replaced with simpler electric motor units directly mounted on the wing structure. The invention removes the need for intermediate mechanical linkages, gears, and complex bearing systems by directly actuating the rotors and control surfaces with electric motors, thereby reducing device complexity while achieving the required tilt capability.
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 reduces the weight of the actuation system, enhances flight range, and allows for take-off and landing on diverse surfaces, improving the aircraft's usability and payload capacity.
Implementation Method 1
a plurality of electric motors and propellers mounted to the aircraft, each motor and propeller being pivotal with the control surface
Implementation Method 2
each motor and propeller being pivotal with the control surface about a leading edge of the wing
Data Source
AI summary
A vertical take-off and landing (VTOL) aircraft (10) comprises a fuselage (24) first and second forward wings (20, 22) and first and second rearward wings (30, 32), each wing having a fixed leading edge (25, 35) and a trailing control surface (50) which is pivotal about a generally horizontal axis. Electric rotors (60) are mounted to the wings (20, 22, 30, 32), the electric rotors (60) being pivotal with the trailing control surface (50) between a first position in which each rotor (60) has a generally vertical axis of rotation, and a second position in which each rotor (60) has a generally horizontal axis of rotation; wherein at least one of the wings (20, 22, 30, 32) has a first and a second electric rotor (60) which are each mounted having non-parallel axes of rotation so that the thrust lines of the first and second electric rotors are different.