Rotor Blade Trim Tab Actuation via Core Integration

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Existing rotary wing aircraft lack adjustable trim tabs that can dynamically change their angle relative to the rotor blade to optimize aerodynamic properties based on flight conditions, limiting control over global blade characteristics such as high-speed efficiency and flutter stability.

Innovation Solution

A rotor blade with an integrated actuation system within the core, allowing the trim tab assembly to adjust its angle relative to the rotor blade, featuring a support member and actuators that apply force to the trim portion, enabling independent movement of multiple trim tab assemblies along the rotor blade span.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If trim tabs are formed as discrete sections connected to the blade after manufacture, then manufacturing flexibility is improved, but the ability to adjust trim tab angle relative to the rotor blade is lost

Engineering Contradiction:

Improvemanufacturing flexibilityVSAvoidtrim tab angle adjustability

Core Design Contradiction:

Ease of manufactureVSAdaptability or versatility

Solution Approach 1:

The patent merges the trim tab assembly with the rotor blade by integrating the actuation system within the blade core and connecting the trim tab to the blade through support members and hinges, creating a unified structure that maintains both manufacturing flexibility and angle adjustability

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The patent introduces dynamic adjustability by enabling the trim tab angle relative to the rotor blade to be changed during operation through the actuation system, transforming a static connection into a dynamic, controllable relationship

Inventive Principle:

Principle #15Dynamics

2Stability of the object's composition

If trim tabs are mounted to the rotor blade surface, then structural integration is improved, but the ability to independently adjust each trim tab assembly is limited

Engineering Contradiction:

Improvestructural integrationVSAvoidindependent trim tab adjustment

Core Design Contradiction:

Stability of the object's compositionVSAdaptability or versatility

Solution Approach 1:

The patent segments the trim tab assembly into independent components including the trim tab portion, support members, hinges, and actuators, allowing each assembly to be independently adjusted while maintaining structural integration through the blade core

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent nests the actuation system within the rotor blade core, placing the motor and transmission mechanisms inside the blade structure, while the trim tab assembly is nested within the blade cross-section, enabling independent adjustment without compromising structural integrity

Inventive Principle:

Principle #7Nested doll (Nesting)

3Adaptability or versatility

If an actuation system is integrated within the rotor blade core, then aerodynamic control capability is improved, but device complexity increases

Engineering Contradiction:

Improveaerodynamic control capabilityVSAvoidactuation system complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The patent nests the actuation system within the rotor blade core, placing the motor, transmission mechanisms, and control components inside the blade structure, which consolidates complexity into a contained volume rather than adding external complexity

Inventive Principle:

Principle #7Nested doll (Nesting)

Solution Approach 2:

The patent designs the actuation system to serve multiple functions: adjusting trim tab angle, controlling aerodynamic properties, and adapting to different flight conditions, thereby reducing the need for separate specialized components

Inventive Principle:

Principle #6Universality (Multi-functionality)

Data Source

PatentUS11325695B2Rotor blade internal structure for trailing edge actuation

Publication Date: 2022.05.10 LOCKHEED MARTIN CORP

AI summary

A rotor blade of a rotary wing aircraft includes a core defining a trailing edge of the rotor blade and a skin extending from the trailing edge defining an opening including the core. The skin defines an aerodynamic surface of the rotor blade. The rotor blade additionally includes at least one trim tab assembly including a trim portion extending from the core beyond the trailing edge of the rotor blade and an actuation system including at least one actuator disposed within the core. The actuation system is operable to adjust an angle of the trim portion relative to the rotor blade.