Convertiplane Appendage Closing System for Aeroelastic Stability
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Solution Overview
Problem
Existing convertiplanes face challenges in maintaining aeroelastic stability during transitions between airplane and helicopter configurations, particularly in the event of drive mechanism failures.
Innovation Solution
A convertiplane design with movable appendages that include a passive closing system using Belleville washers and lever mechanisms to preload appendages into neutral positions, ensuring stability and minimizing airflow interference, combined with drive mechanisms for controlled movement between operating positions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If drive mechanisms are used to move appendages between operating positions, then the convertiplane can switch between airplane and helicopter configurations, but the system becomes vulnerable to drive mechanism failures that compromise aeroelastic stability
Solution Approach 1:
The closing system is pre-configured with elastic means (springs) that automatically engage when the appendage moves toward the neutral position, ensuring the appendage returns to and remains in the neutral position without requiring active drive mechanism intervention. This preliminary mechanical arrangement ensures stability is maintained even if drive mechanisms fail.
Solution Approach 2:
The closing system uses self-acting mechanical elements including elastic means and lever mechanisms that automatically maintain the appendage in the neutral position without requiring external control or power. The system serves itself by using the movement of the appendage to engage the closing mechanism, which then maintains stability passively.
2Ease of operation
If appendages are moved to define compartments for rotor airflow in helicopter configuration, then hover capability is improved, but airflow interference and turbulence increase
Solution Approach 1:
The appendages are designed to be dynamically reconfigurable, moving between extended neutral positions for airplane flight and lowered compartment-defining positions for helicopter hover. This dynamic adjustment allows the aircraft to optimize its aerodynamic characteristics for different flight regimes, reducing harmful airflow interference when in airplane configuration while enabling hover capability when in helicopter configuration.
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
Ensures aeroelastic stability and optimal airflow conditions in both configurations, enhancing safety and performance by maintaining appendages in neutral positions even in the event of drive mechanism failures.
Implementation Method 1
a closing system (60) configured to elastically preload a respective appendage (21) towards a respective first neutral operating position
Data Source
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AI summary
A convertiplane (1) is described, which comprises a fuselage (2) extending along a first axis (A), a pair of half-wings (3) projecting cantilevered from respective sides of the fuselage (2), a pair of nacelles (4) housing respective engines and operatively connected to the half-wings (3); and a pair of rotors (5) associated with the half-wings (3), rotatable around respective second axes (B) and tiltable so as to arrange the convertiplane (1) in an airplane configuration or in a helicopter configuration. Each half-wing (3) further comprises a wingbox (20) and an appendage (21) articulated on the wingbox (20) and selectively movable between a relative first neutral operating position taken when the convertiplane (1) is in the airplane configuration and in which it defines an extension of the wingbox (20) and a relative second position taken when the convertiplane (1) is in the helicopter configuration and in which it defines with the wingbox (20) a compartment (50) through which the air flow generated by the respective rotor (5) can pass. The convertiplane (1) comprises a closing system (60) configured to elastically preload each appendage (21) towards the respective first neutral operating position.