VTOL Aircraft Wing-Rotor Layout for Low-Complexity Lift
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current VTOL aircraft designs face challenges such as increased complexity and cost due to dead weight from vertical lift motors that are not used during most flight time, risk of rotor contact with objects or people, complex stability control mechanisms, and high thrust/weight ratios, which affect efficiency, safety, and redundancy.
Innovation Solution
Aircraft with a propulsion system using four thrust-producing elements, two at the front and two at the rear, with rotors driven by electric motors, where the rotation planes are horizontal or slightly inclined, and wings positioned to enhance lift even in static conditions, allowing for efficient vertical and horizontal flight without actuators for wings or propellers, and varying rotor speeds for flight mode transitions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If different rotors are used for vertical and forward flight, then vertical lift capability is achieved, but device complexity increases due to dead weight from vertical lift motors not used during forward flight
Solution Approach 1:
The patent applies multi-functionality by designing a single rotor system that performs both vertical lift and forward thrust functions. The rotor can operate in different modes: vertically oriented for takeoff/landing and horizontally oriented for forward flight, eliminating the need for separate propulsion systems and reducing overall device complexity.
Solution Approach 2:
The patent employs dynamic reconfiguration of the rotor orientation through tilting mechanisms. The rotor can change its angle of inclination from vertical to horizontal position, allowing the same physical component to adapt to different flight phases. This dynamic adjustment eliminates dead weight issues while maintaining versatility.
2Device complexity
If unprotected rotors are used, then device complexity is reduced, but safety deteriorates due to risk of rotor contact with surrounding objects or people
Solution Approach 1:
The patent introduces protective structures such as protective cages or shields that act as intermediaries between the rotor and surrounding objects/people. These protective elements prevent direct contact while allowing the rotor to maintain its operational simplicity and aerodynamic efficiency.
3Adaptability or versatility
If tilting wings or tilting rotors are used, then vertical and horizontal flight capability is achieved, but device complexity increases due to sophisticated control mechanisms for stability
Solution Approach 1:
The patent employs self-service principles by designing the aircraft so that the center of gravity and center of pressure are positioned to automatically provide stability during transition. The geometric arrangement of the rotor and wing components creates inherent aerodynamic stability that reduces or eliminates the need for complex active control mechanisms.
4Power
If distributed electric propulsion is used, then propulsion capability is achieved, but thrust/weight ratio remains high (1.2-1.4) without additional aerodynamic phenomena
Solution Approach 1:
The patent applies aerodynamic phenomena to create lift forces that counteract the weight of the aircraft. By optimizing the interaction between the rotor-generated airflow and the wing surfaces, additional lift is produced beyond what would be achieved by propulsion alone, effectively reducing the thrust/weight ratio and improving overall efficiency.
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 design simplifies construction, reduces weight, enhances propulsion efficiency, increases speed, and improves safety by eliminating rotor contact risks and single points of failure, while maintaining a compact size and high redundancy.
Implementation Method 1
The front rotors are operated to produce a depression on the front wing and this contributes to increase the vertical thrust force. At the same time the rear rotors are operated to produce an increased pressure on the rear wing lower surface and this contributes to increase of the vertical thrust force
Implementation Method 2
uses certain aerodynamic phenomena to increase the lifting force
Data Source
AI summary
The invention refers to a VTOL aircraft of the type that uses certain aerodynamic phenomena to increase the lifting force and to reduce the thrust/weight ratio. An aircraft 1 uses a propulsion system 2 consisting of four thrust producing elements, two in front 3 and two in rear 4. Each front thrust producing element 3 contains at least one front rotor 5 operated by at least one front electric motor, fixed on a fuselage 10. Each rear thrust producing element 4 contains at least one rear rotor 7 driven by at least a rear electric motor 8, fixed on the fuselage 10. On the fuselage 10 is attached symmetrically a front wing 12. On the fuselage 10 is attached symmetrically a rear wing 13. The wing 12 and 13 are used also in static conditions respectively in take-off and landing.