Convertiplane Wing Appendage and Rotor Tilt Mechanism
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Solution Overview
Problem
Existing convertiplanes face challenges in optimizing aerodynamic efficiency between 'airplane' and 'helicopter' configurations, particularly due to interference from rotors' downwash and the need for additional sealing elements, which increases bulk and complexity, and affects payload and performance.
Innovation Solution
The design features movable appendages that can be selectively positioned to minimize airflow interruption in 'airplane' mode and allow downwash passage in 'helicopter' mode without additional sealing elements, using a unique hinging mechanism that houses actuating mechanisms within the wing profile, reducing interference with rotor downwash and simplifying the design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If sealing elements are added to close the aperture between wings and movable appendages, then aerodynamic efficiency in airplane configuration is improved, but device complexity and bulk increase
Solution Approach 1:
The patent removes the sealing elements from the system entirely. Instead of adding sealing elements to close the aperture, the design accepts the aperture as part of the structure and optimizes the movable appendage positioning to minimize aerodynamic interference without requiring additional sealing components, thus reducing device complexity while maintaining acceptable aerodynamic efficiency
Solution Approach 2:
The patent employs movable appendages that can dynamically change position between airplane and helicopter configurations. In airplane mode, the appendages are positioned to minimize disruption to airflow over the wings. This dynamic repositioning allows the system to adapt to different flight modes without requiring complex sealing mechanisms, resolving the contradiction between aerodynamic efficiency and device complexity
2Ease of operation
If rotors are tilted for helicopter configuration, then manoeuvrability and ease of use are improved, but maximum operating speed and altitude are limited
Solution Approach 1:
The convertiplane features rotors that can be tilted between vertical (helicopter mode) and horizontal (airplane mode) positions, allowing dynamic adaptation between high manoeuvrability and high speed configurations. This enables the aircraft to achieve both helicopter-like ease of operation and airplane-like cruising performance
Solution Approach 2:
The system changes the operational parameters by tilting the rotor axes. In helicopter configuration, rotors are vertical for maximum manoeuvrability. In airplane configuration, rotors are tilted to horizontal position, transforming the aircraft into a high-speed propeller-driven mode capable of exceeding 150 knots and reaching altitudes above 20,000 feet, thus overcoming the speed and altitude limitations of conventional helicopters
3Loss of energy
If movable appendages are positioned to minimize airflow interruption in airplane mode, then aerodynamic efficiency is improved, but downwash passage is blocked in helicopter mode
Solution Approach 1:
The movable appendages are designed to change position dynamically based on the aircraft configuration. In airplane mode, they are positioned to minimize airflow interruption and maximize aerodynamic efficiency. In helicopter mode, they are repositioned to allow downwash passage. This dynamic adaptability resolves the contradiction between optimizing for one mode and maintaining versatility for both modes
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 approach enhances aerodynamic efficiency in both configurations by minimizing airflow disruption and reducing the need for larger rotors, resulting in improved payload capacity and performance while simplifying the design and reducing bulk.
Implementation Method 1
the downwash generated by the rotor 5 passes through the opening 50
Implementation Method 2
the airflow generated by the rotor 5 passes through the opening 50
Data Source
AI summary
Convertiplane comprising a fuselage; a pair of wings, a pair of nacelles fixed with respect to the wings, and a pair of rotors rotatable about respective second axes and tiltable about a third axis between a first position, reached when the convertiplane is in an aeroplane configuration, and a second position, reached when the convertiplane is in a helicopter configuration. The wing comprises a wing box and a first appendage movable when the convertiplane is in the aeroplane configuration, between a first neutral position, a second raised operating position, and a third lowered operating position; the wing comprises a second appendage movable between a first neutral position assumed when the convertiplane is in the aeroplane configuration and in which it defines an extension of the wing box, and a second position assumed when the convertiplane is in the helicopter configuration and in which it defines, with the wing box, an opening through which the downwash generated by the rotor can flow.