Compliant Wing System for Drag Reduction

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Solution Overview

Problem

Existing aircraft control surfaces, such as ailerons and flaps, create drag and noise due to their rigid structures and fixed configurations, which are not optimal for varying flight conditions, and there is a need for adjustable surface contours to enhance performance and efficiency.

Innovation Solution

A fixed compliant wing system with compliant rib structures and actuators that deform to change the camber of the wing without discrete control surfaces, allowing for adjustable surface contours and reduced drag and noise.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Strength

If rigid control surfaces (ailerons, flaps, slats) are used, then structural strength and control authority are improved, but drag and noise increase

Engineering Contradiction:

Improvestructural strengthVSAvoiddrag and noise

Core Design Contradiction:

StrengthVSObject-generated harmful factors

Solution Approach 1:

The patent employs flexible membrane structures instead of rigid control surfaces. The membrane can deform continuously to change camber and twist along the span, eliminating the need for traditional rigid flaps and ailerons. This flexible membrane approach reduces drag by eliminating gaps and sharp edges, while also reducing noise from turbulent flow separation.

Inventive Principle:

Principle #30Flexible shells and thin films

Solution Approach 2:

The patent implements dynamic shape adjustment through distributed actuators that can change the camber and twist of the wing in real-time. The membrane structure allows continuous deformation along the span, enabling the wing to adapt its geometry dynamically rather than using discrete, static control surfaces.

Inventive Principle:

Principle #15Dynamics

2Device complexity

If fixed wing configuration is used, then structural simplicity is improved, but adaptability to different flight conditions deteriorates

Engineering Contradiction:

Improvestructural simplicityVSAvoidadaptability to flight conditions

Core Design Contradiction:

Device complexityVSAdaptability or versatility

Solution Approach 1:

The patent transforms the fixed wing into a dynamically adjustable structure using distributed actuators embedded within the membrane. These actuators can change the camber and twist distribution along the span, allowing the same simple membrane structure to adapt to different flight conditions (cruise, takeoff, landing) without requiring complex mechanical control surfaces.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The patent changes geometric parameters (camber, twist, airfoil shape) of the wing by deforming the membrane structure. By adjusting the position and shape of the membrane through actuation, the wing can optimize its aerodynamic parameters for different flight regimes while maintaining the same basic structural configuration.

Inventive Principle:

Principle #35Parameter changes

3Force

If discrete control surfaces with gaps are used, then control authority is improved, but noise production increases

Engineering Contradiction:

Improvecontrol authorityVSAvoidnoise production

Core Design Contradiction:

ForceVSObject-generated harmful factors

Solution Approach 1:

The flexible membrane creates a continuous surface without gaps between control surfaces and the wing body. This eliminates gap turbulence and the associated noise while maintaining control authority through distributed actuation that can create effective camber changes across the entire wing span.

Inventive Principle:

Principle #30Flexible shells and thin films

Solution Approach 2:

The patent merges the function of multiple discrete control surfaces (flaps, ailerons, slats) into a single integrated membrane structure. This unified approach eliminates the gaps and joints between separate surfaces, reducing noise from turbulent flow while maintaining the ability to generate control forces through distributed actuation.

Inventive Principle:

Principle #5Merging (Combining)

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 system achieves efficient deformation with minimal energy consumption and reduced maintenance, enabling optimized wing configurations for different flight conditions and applications, such as in aircraft, watercraft, and high-speed land vehicles.

Implementation Method 1

The outer compliant contoured structure is configured to deform when force is applied to the drive members of the compliant rib structures

Methodology Applied

Scientific EffectElastic deformation: Elasticity

Data Source

PatentUS9233749B1Variable camber adaptive compliant wing system

Publication Date: 2016.01.12 THE GOVERNMENT OF THE UNITED STATES AS REPRESENTED BY THE SECRETARY OF THE AIR FORCE

AI summary

A fixed compliant wing system is provided that is coupled to a rigid spar and a rigid stopper. The fixed compliant wing system includes an actuator and at least two compliant rib structures coupled to the rigid spar. The compliant rib structures include an outer compliant contoured structure, a drive member coupled to the outer compliant contoured structure where the drive member is in a sliding arrangement with the rigid stopper. The drive member is further connected to the actuator. The outer compliant contoured structure of the compliant rib structures is configured to deform when force is applied from the actuator to the drive member. The fixed complaint wing system further includes a skin encompassing the compliant rib structures.