Adaptive Trailing Edge Assembly for Rotor Blade Hover Performance
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Solution Overview
Problem
Rotor blade designs optimized for forward flight often compromise hover flight performance, and existing active flow control devices require high-frequency actuators that consume more power and are unreliable under rotor blade operating conditions.
Innovation Solution
A rotor blade assembly with a deployable trailing edge assembly, featuring a trailing edge flap and a low-frequency actuator that can be selectively deployed during hover flight to enhance lift while minimizing impact on other aerodynamic aspects, allowing the rotor blade to maintain forward flight performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the rotor blade is designed with a fixed trailing edge optimized for forward flight, then forward flight performance is improved, but hover flight performance deteriorates
Solution Approach 1:
The patent applies the dynamics principle by making the trailing edge flap movable rather than fixed. The flap can be rotated between a first position (conforming to the blade upper surface) for forward flight and a second position (inclined relative to the blade) for hover flight. This dynamic adjustment allows the rotor blade to adapt its aerodynamic characteristics to different flight regimes, resolving the contradiction between optimized forward flight performance and hover flight performance.
2Adaptability or versatility
If high-frequency actuators are used for active flow control, then hover performance can be improved, but power consumption increases and reliability decreases
Solution Approach 1:
The patent applies periodic action by using a low-frequency actuator that operates intermittently rather than continuously. The actuator is activated only when hover performance is needed, rotating the trailing edge flap between positions. This periodic operation significantly reduces power consumption compared to continuous high-frequency actuation, while still achieving the desired hover performance improvement. The low-frequency operation also enhances reliability by reducing mechanical wear and energy demands.
3Adaptability or versatility
If a deployable trailing edge assembly is added to enhance hover performance, then hover performance is improved, but device complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the trailing edge into two functional parts: the fixed trailing edge structure and the movable trailing edge flap. This segmentation allows the flap to be independently controlled and positioned, providing enhanced hover performance without requiring complete redesign of the entire rotor blade structure. The modular approach minimizes added complexity by keeping the fixed portion simple and only adding the necessary movable components where needed.
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 the rotor blade to achieve enhanced hover performance with reduced power consumption and increased reliability, while maintaining forward flight capabilities by using a localized and low-frequency actuated trailing edge assembly.
Implementation Method 1
the upper and lower surfaces of the trailing edge flap are deflected at a predetermined deflection angle relative to the upper and lower surfaces of the rotor blade
Data Source
AI summary
A rotor blade assembly includes a rotor blade having inboard and outboard regions, a blade body, and an internal spar, the blade body defining leading and trailing edges. A trailing edge assembly extends from and is connected to the trailing edge, and has a trailing edge flap and an actuator configured to deploy the trailing edge flap between first and second positions. In one of the first and second positions, an upper surface of the trailing edge flap conforms in profile to an upper surface of the rotor blade, and in the other, the trailing edge flap is inclined relative to the blade. During hovering flight, at least one trailing edge flap segment is deflected to enhance hover performance. During forward flight, at least one trailing edge flap segment is either not deflected for reduced effect on forward flight or is deflected for additional thrust.