Tiltrotor Double Mobile Wing Segmentation
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Solution Overview
Problem
Existing convertiplanes face challenges with high gyroscopic effects from single large propellers, leading to instability during wing rotation, low maneuverability, and low aerodynamic efficiency, especially in larger aircraft, and have reliability issues due to single propeller configurations.
Innovation Solution
A convertiplane structure with a main wing and auxiliary wing, each equipped with multiple propellers, arranged to form a closed polygon aerodynamic configuration, reducing gyroscopic effects and increasing lift and stability, while distributing payload and structural weight to enhance structural resistance and aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a single large propeller is used for each wing, then the propulsion force is sufficient, but the gyroscopic effect becomes very high making wing rotation difficult and causing fuselage instability
Solution Approach 1:
The patent divides each wing's propulsion system into multiple smaller propellers (at least two main propellers on the main wing and at least two auxiliary propellers on the auxiliary wing) instead of using a single large propeller. This segmentation reduces the gyroscopic effect while maintaining sufficient total propulsion force, enabling stable wing rotation during configuration transitions.
2Device complexity
If a single large propeller is used for each wing, then the propulsion system is simpler, but the maneuverability during wing rotation becomes poor
Solution Approach 1:
The propulsion system is segmented into multiple smaller propellers distributed across the main and auxiliary wings. This configuration reduces the gyroscopic effect that hinders wing rotation, thereby improving maneuverability during configuration transitions while keeping the overall system relatively simple.
Solution Approach 2:
The patent introduces an auxiliary wing positioned at a different vertical height than the main wing, creating a three-dimensional arrangement of propellers. This spatial distribution in multiple dimensions further reduces the cumulative gyroscopic effect and improves wing rotation control.
3Device complexity
If the auxiliary wing is positioned at the same vertical height as the main wing, then the structure is simpler, but the aerodynamic efficiency is low due to high induced drag
Solution Approach 1:
The auxiliary wing is positioned at a different vertical height than the main wing, creating a three-dimensional configuration. This vertical separation reduces induced drag by spacing the wing systems in the vertical dimension, improving aerodynamic efficiency during cruise flight.
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 configuration significantly increases flight range, reduces energy consumption, and enhances maneuverability and reliability by minimizing gyroscopic effects and improving aerodynamic efficiency.
Implementation Method 1
the projections on the plane π of the main wing, of the auxiliary wing and of the vertical wings shape a closed polygon, thus reducing the induced drag and increasing the overall aerodynamic efficiency
Implementation Method 2
Such propellers create a very high gyroscopic effect compared to the mass of the aircraft, making it difficult the rotation of the wings when passing between the take-off configuration and gliding flight configuration
Data Source
Figure 1
Figure 2A
Figure 2B
AI summary
A convertiplane structure (100), having a longitudinal axis x and a plane n orthogonal to it, comprises a main wing (120) arranged to rotate about at least one transversal rotation axis y, an auxiliary wing (130), which is located back with respect to main wing (120), and arranged to rotate about at least one transversal rotation axis y', at least two main propellers (220) located on the main wing (120), and at least two auxiliary propellers (230) located on the auxiliary wing (130). The auxiliary wing (130) is located at a vertical height higher than main wing (120). Two vertical wings (140) are also provided located in such a way that the projections on the plane n of the main wing (120), of the auxiliary wing (130) and of the vertical wings (140) shape a closed polygon, thus reducing the induced drag and increasing the overall aerodynamic efficiency.