Aircraft Wing Rotor Pivot Mechanism for Transition Stability
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Solution Overview
Problem
Existing aircraft designs, such as tilt rotor and tilt wing types, face inefficiencies in flight efficiency and stability due to main wing interactions with propeller wakes and negative angles of attack during transitions from hovering to level-flight, leading to potential descent risks and instability under wind resistance.
Innovation Solution
An aircraft with a displaceable connecting part that maintains a positive angle of attack for the lift generating part relative to the flying direction, utilizing a combination of lift and thrust generating parts, including a wing and rotary wing, to ensure efficient and safe transitions between hovering and level-flight states.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the main wing enters a wide range of the propeller wake at the time of ascending, then the aircraft can achieve thrust generation, but the flight efficiency of the main wing is deteriorated
Solution Approach 1:
The connecting part is configured to be displaceable, allowing the main wing to dynamically adjust its position and angle of attack in response to different flight phases. During ascending, the main wing can be positioned to avoid propeller wake, while during hovering-to-level-flight transition, it can maintain optimal angle of attack, thus resolving the contradiction between thrust generation and flight efficiency
2Power
If the main wing has a negative angle of attack at the time of transition from hovering to level-flight, then the aircraft can achieve horizontal direction thrust, but the airframe will descend
Solution Approach 1:
The displaceable connecting part enables the main wing to maintain a positive angle of attack during transition from hovering to level-flight, ensuring continuous lift generation. This dynamic adjustment prevents the airframe from descending while achieving the required horizontal thrust, thus resolving the contradiction between thrust generation and flight stability
3Adaptability or versatility
If the entire main wing is displaced, then the aircraft can achieve transition flexibility, but it is unstable when receiving resistance of wind
Solution Approach 1:
The aircraft system is segmented into the thrust generation part (rotor) and the lift generation part (main wing), connected by a displaceable connecting part. This segmentation allows the main wing to remain relatively stable while the rotor provides transition flexibility, resolving the contradiction between adaptability and stability under wind resistance
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 solution enables efficient and safe transitions from hovering to level-flight by maintaining a positive angle of attack, reducing the impact of propeller wakes and enhancing stability, thereby improving flight efficiency and safety.
Implementation Method 1
a lift generating part
Implementation Method 2
a thrust generating part capable of flying and hovering
Data Source
AI summary
An aircraft that enables an efficient and safe transition from hovering to level-flight. The aircraft according to the present invention includes a lift generating part, a thrust generating part capable of flying and hovering, a connecting part that displaceably connects the lift generating part and the thrust generating part so that the lift generating part can maintain a positive angle of attack with respect to the flying direction at least at the time of ascending. The lift generating part is a wing part having a main surface, and at least at the time of hovering, a propulsion direction by the thrust generating part is along a direction obliquely intersecting the vertical direction. At least at the time of hovering, the propulsion direction and the main surface form an obtuse angle. At least at the time of hovering, the propulsion direction is along the vertical direction.