Modular Fluidic Actuator Plenums for Aircraft Flow Control

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Existing active flow control systems for aircraft are cumbersome and inefficient due to complex geometry of fluidic actuators, which complicates integration and increases weight, reducing fuel efficiency and performance.

Innovation Solution

A modular fluid flow control system with plenums and fluidic actuators that allow for flexible configuration and integration, reducing pressure drop and flow loss by simplifying fluid connections and enabling customization without significant redesign, and can be retrofitted onto existing aircraft structures.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If complex geometry fluidic actuators are used to control airflow, then aerodynamic performance is improved, but system weight increases and fuel efficiency decreases

Engineering Contradiction:

Improveairflow control effectivenessVSAvoidsystem weight

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The system divides the aircraft surface into multiple zones with discrete fluidic actuators distributed across plenums, allowing localized airflow control rather than requiring complex geometry throughout the entire actuator system. This segmentation enables effective airflow control while minimizing overall system weight.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent applies fluidic actuators with specific local properties at critical locations on the aircraft surface (such as leading edges and control surfaces) where airflow control is most needed. This localized approach provides effective aerodynamic control without the weight penalty of complex geometry system-wide.

Inventive Principle:

Principle #3Local quality

2Reliability

If complex geometry fluidic actuators are used, then airflow control capability is enhanced, but integration complexity increases

Engineering Contradiction:

Improveairflow control capabilityVSAvoidintegration complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The system segments the fluidic actuator array into modular units distributed across multiple plenums that can be independently integrated onto the aircraft surface. This modular segmentation simplifies the integration process compared to installing a single complex geometry actuator system, while maintaining effective airflow control capability through coordinated operation of multiple simpler units.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent employs universal plenum structures and standardized fluidic actuator components that can be integrated across different aircraft surfaces and configurations. This universality reduces integration complexity by allowing the same basic components to serve multiple functions and locations, eliminating the need for custom complex geometry designs for each application.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Force

If traditional fluidic actuator systems are used, then aerodynamic forces can be affected, but pressure drop and flow loss increase

Engineering Contradiction:

Improveaerodynamic force modulationVSAvoidpressure drop and flow loss

Core Design Contradiction:

ForceVSLoss of energy

Solution Approach 1:

The patent replaces traditional mechanical valve and piping systems with a pneumatic-hydraulic plenum distribution system that uses the aircraft's existing pneumatic resources. This substitution eliminates complex mechanical flow control components that cause pressure drops, while still enabling effective modulation of aerodynamic forces through controlled fluid delivery to distributed actuators.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The system uses pneumatic principles to distribute fluid through plenums to multiple fluidic actuators, leveraging the compressibility and flow characteristics of gases to minimize pressure losses. This pneumatic approach reduces flow loss compared to traditional mechanical systems while maintaining the ability to affect aerodynamic forces through controlled actuation.

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 system improves aircraft performance by enhancing airflow control, reducing drag, increasing lift, and improving fuel efficiency while being lightweight and adaptable.

Implementation Method 1

The fluidic actuators are configured to provide pressurized fluid to the aerodynamic surface to modify an aerodynamic characteristic of the aerodynamic surface

Methodology Applied

Scientific EffectPressurized fluid flow: Jet

Data Source

PatentUS11332235B2Active flow control systems for aircraft and related methods

Publication Date: 2022.05.17 THE BOEING CO

AI summary

Active fluid control systems and related methods are disclosed. A disclosed example active fluid control system includes a plurality of plenums coupled together to define a fluid flow passageway, and a plurality of fluidic actuators coupled to outer surfaces of respective ones of the plenums. The fluidic actuators define actuator inlets and actuator outlets. The fluid flow passageway defined by the plenums to fluidly couple the fluidic actuators and a pressurized fluid supply source. The plenums are configured to couple to an aircraft structure supporting an aerodynamic surface to enable the actuator outlets to be mounted to the aerodynamic surface. The fluidic actuators are configured to provide the pressurized fluid to the aerodynamic surface to modify an aerodynamic characteristic of the aerodynamic surface.