Fixed Circular Wing VTOL Aircraft With Hinged Cockpit
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Solution Overview
Problem
Current aircraft designs for vertical take-off and horizontal flight either require complex mechanical systems, high energy costs, or compromise on range and accessibility due to the need for rotating wings or tilt-rotors, while also failing to maintain pilot and passenger comfort and safety during transition phases.
Innovation Solution
An aircraft with fixed, non-rotating closed wings integrating propulsion devices, allowing vertical take-off and horizontal flight transition by pitch axis rotation, and piloting via differential thrust control, with a hinged cockpit for constant passenger position and easy access.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If rotating wing devices (helicopters) are used for vertical take-off, then vertical take-off capability is achieved, but range of action is reduced and mechanical complexity increases
Solution Approach 1:
The aircraft is divided into two independent functional modules: a fixed circular wing structure providing lift and a separately controllable propulsion system with multiple independent thrusters. This segmentation allows the wing to remain simple and fixed while the propulsion system handles all rotational and thrust control functions through differential thrust of individual thrusters, eliminating the need for complex rotating mechanical linkages.
Solution Approach 2:
The patent replaces traditional mechanical control systems (rotating wings, tilt-rotor mechanisms, moving control surfaces) with a thrust-vectoring propulsion system. Independent electronic control of multiple thrusters provides rotational control and attitude adjustment without any mechanical rotation of the wing structure itself, substituting mechanical complexity with electronic control of fixed propulsion elements.
2Adaptability or versatility
If tilt-rotor systems are used for transition from vertical to horizontal flight, then range of action is improved, but mechanical complexity and cost increase
Solution Approach 1:
The aircraft achieves dynamic transition between vertical and horizontal flight modes through real-time adjustment of thruster thrust vectors and differential thrust distribution. The fixed circular wing provides continuous lift while the propulsion system dynamically adapts its thrust configuration, allowing smooth transition without mechanical tilting or rotation of the wing-rotor assembly.
Solution Approach 2:
The fixed circular wing structure serves multiple functions simultaneously: it provides lift during vertical take-off, generates aerodynamic drag for deceleration, and contributes to horizontal flight stability. The propulsion system with multiple independent thrusters performs multiple functions including thrust generation, rotational control, attitude adjustment, and transition management, eliminating the need for specialized tilt-rotor mechanisms.
3Device complexity
If flat wings are used for horizontal flight, then simplicity is maintained, but induced drag increases due to marginal vortices
Solution Approach 1:
The patent employs a circular wing geometry instead of traditional flat or rectangular wings. The circular shape eliminates the strong tip vortices characteristic of flat wings by distributing the vortex generation uniformly around the entire perimeter. This curved geometry reduces induced drag while maintaining structural simplicity and symmetry, improving aerodynamic efficiency without adding 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
This design simplifies propulsion, reduces mechanical complexity, maintains passenger comfort, and enhances safety and performance by eliminating tilt-rotors and maintaining a stable passenger position during all flight phases, while offering reduced drag and easy boarding.
Implementation Method 1
vertical take-off and horizontal flight, devoid of a plane wing and comprising 3 non-contiguous closed wings each integrating at least one propulsion device
Implementation Method 2
Piloting on two or three of the axes of rotation can be obtained without the use of moving planes. This piloting can be obtained by differential control of the thrust of at least three of the propulsion motors.
Implementation Method 3
This aircraft can pass from the vertical take-off (or hovering) phase to the horizontal flight phase, and vice versa, by rotation on the pitch axis without requiring the presence of tilt-rotors.
Implementation Method 4
These closed wings are all fixed, without the possibility of rotation, to the same structure of the aircraft. The position of the pilots and passengers in this type of machine must be managed during the transition phase in order to maintain visibility in flight and a comfortable position for the pilots and passengers.
Implementation Method 5
The cockpit carrying the pilot(s) and any passenger(s) is hinged with respect to the rest of the aircraft in order to allow the pilots and passengers to be maintained in a substantially constant position with respect to the axis of gravity during all phases of flight.
Data Source
Figure 1
Figure 2
AI summary
The present invention relates to a vertical takeoff and horizontal flight aircraft comprising at least three circular wings (2), each incorporating a propulsion device (3). This tilt-rotor-free aircraft includes a differential propeller speed control system. It can transition from the vertical takeoff (or hovering) phase to the horizontal flight phase by tilting on its pitch axis. The cockpit (1), which carries at least the pilots and passengers, is hinged relative to the rest of the aircraft and is thus maintained in a substantially horizontal position throughout all phases of flight to ensure that the pilots and passengers remain in a substantially constant position relative to the center of gravity. It also allows for easy boarding and disembarking.