Hybrid VTOL Rotor Layout for Higher Payload and Endurance
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Solution Overview
Problem
Conventional hybrid aircrafts do not maximize payload capacity, which is crucial for commercial and resource-saving perspectives, as they rely heavily on electric rotors with limited endurance and high power consumption.
Innovation Solution
A VTOL aircraft design featuring front and rear rotors powered by internal combustion engines for primary lift and thrust, with electric rotors providing stability, allowing for a significant reduction in battery size and weight, enabling higher payload capacity and longer endurance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If electric rotors are used to provide primary lift and thrust in hybrid aircraft, then vertical take-off and landing capability is achieved, but battery size and weight increase significantly, reducing payload capacity
Solution Approach 1:
The aircraft's rotor system is segmented into two distinct groups: electric rotors mounted on the wings and an internal combustion engine rotor mounted on the fuselage. This segmentation allows each rotor type to be optimized for specific functions, with the ICE rotor providing primary lift during vertical flight and electric rotors providing supplemental lift and stability, thereby reducing the power requirements and weight of the battery system.
Solution Approach 2:
The internal combustion engine rotor serves multiple functions: it provides primary vertical lift during take-off and hover, transitions to horizontal thrust during forward flight, and can be vectored to provide both lift and thrust components during transition phases. This multi-functionality eliminates the need for separate dedicated lift and propulsion systems, reducing overall system weight and complexity.
2Weight of moving object
If internal combustion engines are used for primary lift, then payload capacity increases due to reduced battery weight, but mechanical complexity and failure risk increase
Solution Approach 1:
The aircraft merges conventional fixed-wing aerodynamics with rotorcraft vertical flight capability by integrating a traditional wing structure with vectored rotors. The wing provides efficient forward flight and cruise performance, while the vectored rotors enable vertical take-off and landing. This combination allows the use of lighter batteries and smaller ICE components compared to a pure rotorcraft design, as the wing shares the burden of providing lift during forward flight.
Solution Approach 2:
The rotor system incorporates dynamic vectoring capability, allowing the rotors to change their orientation and thrust direction in real-time. During vertical flight, rotors are oriented vertically to provide lift; during forward flight, they transition to horizontal orientation for thrust; and during transition phases, they provide a combination of both. This dynamic adaptability enables a single rotor system to perform multiple functions, reducing the need for additional mechanical components.
3Duration of action of moving object
If electric rotors provide all vertical lift during hover, then high power consumption occurs, but if internal combustion engine provides lift, then endurance increases
Solution Approach 1:
The internal combustion engine is designed to be air-cooled and self-sufficient, requiring no external power source or complex cooling systems. It directly drives the rotor through a simple reduction gear mechanism, converting chemical energy from fuel directly into mechanical work for rotor rotation. This self-service capability eliminates the need for heavy battery systems and complex power management electronics, significantly reducing overall system weight and power consumption while extending endurance.
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 aircraft achieves a higher payload capacity and longer endurance by utilizing internal combustion engines for primary lift and thrust, while electric motors provide stability, minimizing dead weight and power consumption during hover and forward flight.
Implementation Method 1
a front rotor pivotably mounted to a leading end of the fuselage... one or both of the front and rear rotor/s are driven by one or more suitable internal combustion engine/s
Implementation Method 2
an array of electric rotors mounted to the airframe operatively to provide vertical stability and/or lift to the aircraft, wherein the electric rotors are fixedly mounted to the airframe and are driven by one or more suitable electric motor/s
Implementation Method 3
a front rotor displaceable about an axis parallel to the transverse axis between a lift position in which the front rotor is oriented to provide vertical lift to the aircraft
Data Source
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AI summary
This invention relates to a vertical take-off and landing (VTOL) aircraft, a method of controlling a VTOL aircraft, and a control system for controlling the VTOL aircraft. The aircraft comprises an airframe having a wing extending along a transverse axis and attached to a fuselage extending between a longitudinal axis of the aircraft, and an empennage or canard. An array of electric rotors is fixedly mounted to the airframe. Front and rear internal combustion engines are pivotably mounted to the fuselage and are displaceable between lift positions in which the front and rear rotors are oriented to provide vertical lift to the aircraft for vertical flight and propulsion positions in which the front and rear rotors are oriented to provide forward thrust to the aircraft for horizontal flight. The front and rear rotors provide a majority, or all, of the vertical lift to the aircraft during vertical flight.