Shoulder Wing Vortex Extension for High-Swept Aircraft Wings

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Solution Overview

Problem

Highly-swept wing aircraft face challenges in maintaining control and lift at low speeds, particularly during landing and takeoff, due to the reduced lift generated by their design, which can lead to uncontrollable conditions and the need for higher landing speeds on abbreviated runways.

Innovation Solution

The introduction of a vortex lift enhancer apparatus, including a shoulder wing or air wall coupled to the fuselage, which extends or strengthens the leading-edge vortex along the highly-swept wing, utilizing actuators and processors to adjust its position based on flight conditions, thereby enhancing lift and reducing drag.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Speed

If highly-swept wings are used to achieve higher cruise speeds and high-angle of attack maneuvers, then speed and maneuverability are improved, but control and lift at low speeds deteriorate

Engineering Contradiction:

Improvecruise speedVSAvoidcontrol at low speed

Core Design Contradiction:

SpeedVSEase of operation

Solution Approach 1:

The patent employs a deployable shoulder wing structure that can dynamically change its configuration based on flight conditions. The shoulder wing is stowed during high-speed cruise to minimize drag, and deployed during low-speed operations to enhance lift and control, thus resolving the contradiction between speed performance and low-speed controllability

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The aircraft wing system is divided into the main highly-swept wing and a separate shoulder wing component. This segmentation allows the shoulder wing to be independently deployed or stowed, enabling the aircraft to optimize its aerodynamic characteristics for different flight phases without compromising the main wing design

Inventive Principle:

Principle #1Segmentation

2Loss of energy

If highly-swept wings are used to reduce drag at high speeds, then fuel efficiency is improved, but lift generation at low speeds worsens

Engineering Contradiction:

Improvedrag at high speedVSAvoidlift at low speed

Core Design Contradiction:

Loss of energyVSForce

Solution Approach 1:

The shoulder wing provides dynamic lift enhancement during low-speed phases such as takeoff and landing, while being retracted during high-speed cruise to minimize drag penalties, thus resolving the contradiction between energy efficiency at high speed and lift generation at low speed

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The shoulder wing is deployed in advance during approach and takeoff phases to ensure sufficient lift is available before the aircraft enters the critical low-speed regime, preventing lift deficiency while maintaining high-speed efficiency

Inventive Principle:

Principle #10Preliminary action

3Ease of operation

If the shoulder wing is deployed to enhance lift at low speeds, then control and maneuverability are improved, but device complexity increases

Engineering Contradiction:

Improvemaneuverability at high angle of attackVSAvoidapparatus complexity

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

The shoulder wing employs a flexible, balloon-like structure that can be inflated or deflated to change its aerodynamic profile. This approach provides the necessary lift enhancement with a simpler mechanism compared to rigid deployable surfaces, reducing overall system complexity while maintaining maneuverability

Inventive Principle:

Principle #30Flexible shells and thin films

Solution Approach 2:

The shoulder wing utilizes pneumatic inflation and deflation to control its deployment and retraction, providing a simple and reliable actuation mechanism that enhances maneuverability without requiring complex mechanical linkages or hydraulic systems

Inventive Principle:

Principle #29Pneumatics and hydraulics

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 apparatus increases the lift-to-drag ratio, allowing for slower landing speeds, reduced aircraft loads, and improved maneuverability at high angles of attack, addressing the control issues at low speeds and enabling safer operations on limited runways.

Implementation Method 1

extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft

Methodology Applied

Scientific EffectVortex: Vortex Ring

Implementation Method 2

an actuator operatively coupled to the resilient skin, the actuator to move the resilient skin from a first position to a second position, the second position to affect a leading-edge vortex

Methodology Applied

Scientific Effect:

Implementation Method 3

an air wall operatively coupled to a fuselage of an aircraft proximate a leading-edge of a highly-swept wing of the aircraft and a processor to move the air wall from a first position to a second position, the second position to affect a leading-edge vortex

Methodology Applied

Scientific Effect:

Data Source

PatentUS10967957B2Methods and apparatus to extend a leading-edge vortex of a highly-swept aircraft wing

Publication Date: 2021.04.06 THE BOEING CO

AI summary

Methods, apparatus, and articles of manufacture to extend a leading-edge vortex of a highly-swept wing aircraft wing are disclosed. An example apparatus includes a shoulder wing coupled to a fuselage of an aircraft above a highly-swept wing of the aircraft, the shoulder wing operative in a first position to extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft.