Distributed Suction and Pressure Fan Arrays for Wing Lift Control

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Solution Overview

Problem

Aircraft high-lift devices, such as slats and flaps, increase lift but add complexity and mass, making them undesirable for modern aircraft design.

Innovation Solution

A distributed propulsion system with suction and pressure fan arrays mounted above and below the wing, respectively, allowing independent control of air pressure to optimize lift during different flight phases, potentially reducing the need for traditional high-lift devices.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Force

If traditional high-lift devices (slats, flaps) are used to increase lift, then the lift capability is improved, but the device complexity and mass increase

Engineering Contradiction:

ImproveliftVSAvoidcomplexity

Core Design Contradiction:

ForceVSDevice complexity

Solution Approach 1:

The wing is divided into multiple independent fan arrays distributed across the wing surface, with each fan array capable of independent control. This segmentation allows localized lift generation without requiring complex mechanical high-lift devices spanning the entire wing.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Traditional mechanical high-lift devices (slats, flaps) are replaced with an electrically controlled distributed fan system. The fans use electrical power to generate airflow and pressure differential, substituting mechanical moving parts with an electric propulsion-based system.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

2Force

If traditional high-lift devices (slats, flaps) are used to increase lift, then the lift capability is improved, but the mass of the aircraft increases

Engineering Contradiction:

ImproveliftVSAvoidmass

Core Design Contradiction:

ForceVSWeight of moving object

Solution Approach 1:

The lift-generating function is distributed across multiple small fan arrays rather than concentrated in large mechanical high-lift devices. This segmentation reduces the mass of individual components and allows for more efficient material distribution throughout the wing structure.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Heavy mechanical high-lift devices are replaced with lighter electric fan arrays. The electric propulsion system requires less structural support and eliminates the need for complex hydraulic systems, reducing overall aircraft mass.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Adaptability or versatility

If suction and pressure fan arrays are used to control lift, then the adaptability to different flight phases is improved, but the device complexity increases

Engineering Contradiction:

ImproveadaptabilityVSAvoidcomplexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The fan arrays are designed with variable speed control capabilities, allowing each fan to dynamically adjust its operating parameters based on flight conditions. This dynamic control enables the system to adapt to different flight phases (takeoff, cruise, landing) without requiring physical reconfiguration.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The system controls lift by changing operational parameters (fan speed, airflow rate, pressure differential) rather than physical configuration. By varying these parameters, the system can adapt to different flight conditions while maintaining a fixed physical structure, reducing complexity compared to mechanical reconfiguration systems.

Inventive Principle:

Principle #35Parameter changes

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 system enables efficient control of lift on the wing during various flight segments, reducing the complexity and mass associated with traditional high-lift devices while maintaining optimal performance.

Implementation Method 1

causing, by the one or more controllable devices, at least one of a first operating point for the one or more fans of the suction fan array and a second operating point for the one or more fans of the pressure fan array to adjust so that a pressure ratio of an air pressure below the bottom surface of the wing to an air pressure above the top surface of the wing is changed

Methodology Applied

Scientific EffectPressure differential: Pressure Gradient

Implementation Method 2

Methodology Applied

Scientific EffectFluid flow:

Data Source

PatentUS20240051670A1Aircraft equipped with a distributed propulsion system having suction and pressure fans

Publication Date: 2024.02.15 GENERAL ELECTRIC CO

AI summary

An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.