VTOL Propulsion System Biplane Wing Configuration
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Solution Overview
Problem
Current VTOL aircraft face challenges with high thrust/weight ratios, complex construction, poor pilot visibility, and propeller safety issues due to separate propulsion systems for horizontal and vertical flight, as well as complex tilting mechanisms that increase weight and reduce redundancy.
Innovation Solution
A propulsion system with biplane units at the ends of the fuselage, using parallel front and rear wings fixed at angles between 25° and 80°, with electric motors operating tractor or pusher propellers that produce lift through suction or pressure differences, allowing for efficient transition between vertical and horizontal flight without actuators for wings or flaps, and featuring a tilting pilot seat and rotating cabin for improved visibility and safety.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If separate propulsion systems are used for horizontal and vertical flight, then vertical take-off and landing capability is achieved, but the construction becomes complex and weight increases
Solution Approach 1:
The patent employs a single propulsion system that performs both vertical and horizontal flight functions. The propellers can operate in different configurations (vertical for VTOL, horizontal for forward flight) without requiring separate propulsion systems, thereby reducing construction complexity while maintaining versatility
Solution Approach 2:
The propulsion system incorporates movable propellers that can change their orientation and position dynamically. The propellers can tilt and reposition themselves to adapt between vertical and horizontal flight modes, enabling a single system to fulfill multiple functions without complex fixed structures
2Adaptability or versatility
If separate propulsion systems are used for horizontal and vertical flight, then vertical take-off and landing capability is achieved, but the aircraft weight increases
Solution Approach 1:
The patent employs a single propulsion system that performs both vertical and horizontal flight functions. The propellers can operate in different configurations (vertical for VTOL, horizontal for forward flight) without requiring separate propulsion systems, thereby reducing construction complexity while maintaining versatility
Solution Approach 2:
The propulsion system incorporates movable propellers that can change their orientation and position dynamically. The propellers can tilt and reposition themselves to adapt between vertical and horizontal flight modes, enabling a single system to fulfill multiple functions without complex fixed structures
3Power
If propellers are exposed to the environment, then thrust generation is effective, but safety is compromised due to contact with people and environment
Solution Approach 1:
The patent places the propellers inside a protective fuselage structure during horizontal flight. The propellers are nested within the aircraft body, shielded from external contact, while still being able to generate thrust through the fuselage openings or transparent sections designed for this purpose
Solution Approach 2:
The propulsion system incorporates movable propellers that can change their orientation and position dynamically. The propellers can tilt and reposition themselves to adapt between vertical and horizontal flight modes, enabling a single system to fulfill multiple functions without complex fixed structures
4Adaptability or versatility
If tilting mechanisms for wings are used to achieve forward flight, then flight mode transition is enabled, but the mechanisms become complex and heavy
Solution Approach 1:
The patent employs movable propellers that can tilt and reposition themselves to change flight mode. Instead of tilting the entire wing structure, only the propellers are made dynamic, significantly reducing the complexity and weight of the mechanism while maintaining the ability to transition between vertical and horizontal flight
Solution Approach 2:
The patent divides the tilting function into separate modular propeller units rather than requiring a unified wing tilting mechanism. Each propeller can be independently controlled and positioned, simplifying the overall system architecture and reducing mechanical complexity
5Adaptability or versatility
If tilting mechanisms for wings are used to achieve forward flight, then flight mode transition is enabled, but aircraft weight increases
Solution Approach 1:
The patent employs movable propellers that can tilt and reposition themselves to change flight mode. Instead of tilting the entire wing structure, only the propellers are made dynamic, significantly reducing the complexity and weight of the mechanism while maintaining the ability to transition between vertical and horizontal flight
Solution Approach 2:
The patent divides the tilting function into separate modular propeller units rather than requiring a unified wing tilting mechanism. Each propeller can be independently controlled and positioned, simplifying the overall system architecture and reducing mechanical complexity
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 system achieves a lift force greater than thrust force, reduces weight and energy consumption, enhances pilot comfort, and increases aircraft efficiency and speed, while maintaining redundancy and protecting propellers from environmental contact.
Implementation Method 1
uses a propulsion system composed of a fuselage in the form of a frame that merges two propulsion units, one in the front and one in the back... Each biplane propulsion unit uses a front wing and a rear wing... electric motors operating tractor propellers that produce lift through suction or pressure differences
Implementation Method 2
achieves a lift force greater than thrust force... using aerodynamic phenomena of thrust amplification, including at zero aircraft speed
Data Source
AI summary
The present invention relates to the propulsion system and aircraft with vertical take-off and landing—VTOL that uses aerodynamic phenomena of thrust amplification, including at zero speed, to reduce the thrust/weight ratio.According to the invention, an individual aircraft 1, with vertical take-off and landing, uses a fuselage 2 in the form of a frame 3 that merges two propulsion system, 4 and 5 one in the front and the other in the rear, of the bi-planar type, located at the ends of the fuselage 2. The propulsion system 4 uses two wings 6 and 7, which are superimposed, parallel and distanced by a certain distance D. The rear wing 7 is fixed perpendicularly to the frame 3 in its median area, so that an angle α between 25° and 80° is formed with the horizontal plane in static position. The front wing 6 and the rear wing 7 are secured at their ends by two jet limiters 8. Similarly the rear propulsion system 5 uses two wings 8 and 10. On each rear wing 7 and 10 are installed a number of electric motors 11, preferably located at equal distances from each other. Each electric motor 11 actuates a tractor propeller 12.