Rotatable Trailing Edge Wing for Rotary Aircraft
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Solution Overview
Problem
Rotary wing aircraft face inefficiencies in both low-speed hovering and high-speed flight due to the download force exerted by fixed wings, which reduces airlift capacity and efficiency when hovering, and the need for lift-sharing during forward flight to optimize speed and range.
Innovation Solution
A lift-sharing wing design with a rotatable trailing edge that is passively biased downward for low-speed flight and upward for high-speed flight, utilizing spring, dashpot, or rack and pinion mechanisms to minimize download force and maximize stability, allowing the main rotor to focus on forward thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a fixed wing is used on a rotary wing aircraft, then lift is provided during forward flight, but download force reduces airlift capacity during hovering and low-speed flight
Solution Approach 1:
The trailing edge of the wing is made rotatable rather than fixed, allowing it to dynamically adjust its position between downward (for hovering) and upward (for forward flight) based on flight conditions. This dynamic adjustment resolves the contradiction by enabling the wing to provide lift during forward flight while minimizing download force during hovering.
Solution Approach 2:
The wing's trailing edge position parameter is changed from fixed to variable, allowing optimization of aerodynamic characteristics for different flight regimes. By adjusting the trailing edge position, the wing can transition between providing maximum lift for forward flight and minimizing download force for hovering, thus resolving the force contradiction.
2Productivity
If a rotatable trailing edge mechanism is added to the wing, then aerodynamic efficiency is optimized for different flight speeds, but device complexity increases
Solution Approach 1:
The mechanism uses passive self-adjustment through aerodynamic forces rather than requiring active control systems. The trailing edge automatically moves to the appropriate position based on airflow and flight conditions, eliminating the need for complex sensors, actuators, and control logic while still achieving optimal aerodynamic efficiency.
Solution Approach 2:
A spring-dashpot mechanism serves as an intermediary between the aerodynamic forces and the trailing edge position. This passive mechanical intermediary translates aerodynamic pressure differences into automatic position adjustments, providing aerodynamic efficiency optimization without requiring complex active control systems.
3Stability of the object's composition
If the trailing edge is biased downward for low-speed flight, then stability is improved during hovering, but lift generation is reduced during high-speed flight
Solution Approach 1:
The trailing edge position is made dynamic rather than fixed, allowing automatic adjustment between downward position (for hovering stability) and upward position (for high-speed lift generation). This resolves the contradiction by enabling the same structure to optimize for different flight regimes at different times.
Solution Approach 2:
The trailing edge periodically transitions between downward and upward positions depending on flight phase. During hovering, it remains downward for stability; during forward flight, it moves upward for lift generation. This periodic adaptation allows the system to maintain optimal performance across varying operational conditions.
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 enhances airlift capacity and efficiency during hovering while enabling higher speeds and stability during forward flight by reducing the download force and optimizing the wing's position in response to aerodynamic conditions.
Implementation Method 1
utilizing spring, dashpot, or rack and pinion mechanisms to minimize download force and maximize stability
Implementation Method 2
utilizing spring, dashpot, or rack and pinion mechanisms to minimize download force and maximize stability
Data Source
AI summary
One embodiment includes a rotary aircraft, including: a rotary propulsion system; a body; and a pair of wings connected on opposite sides of the body, wherein each of the wings includes a flap rotatably connected to a trailing edge thereof and configured to rotate downward relative to the wing during low speed and stationary flight of the aircraft, and to rotate upward relative to the wing during high-speed flight of the aircraft.