Fluidic Actuator Flow Control for Aircraft Wing Separation
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Solution Overview
Problem
Conventional active flow control systems for preventing flow separation on aircraft surfaces are complex, costly, and inefficient, especially at high lift conditions, and often require mechanical components that increase weight and maintenance costs.
Innovation Solution
A flow body with an active flow control system featuring a plurality of openings and fluidic actuators connected to an air source, utilizing control pressure ports to generate a pulsating flow without mechanical valves, which influences the surrounding flow by deflecting air primarily into one outlet, thereby reducing flow separation and increasing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional active flow control systems with mechanical valves are used, then flow separation can be controlled, but device complexity and manufacturing costs increase
Solution Approach 1:
The patent replaces mechanical valves with a fluidic actuator system that uses compressed air pulses to control flow separation. The fluidic actuator employs Coanda effect and vortex generation through strategically positioned openings and deflectors, eliminating moving mechanical parts while maintaining effective flow control capability.
Solution Approach 2:
The invention uses pneumatic principles by introducing compressed air through the fluidic actuator to generate control pressures that manipulate the boundary layer flow. The system utilizes pressure differentials and pneumatic pulses to create vortical structures that prevent flow separation, replacing mechanical actuation with pneumatic control.
2Reliability
If mechanical leading edge high lift devices are used, then flow attachment is improved, but weight and manufacturing costs increase
Solution Approach 1:
The patent replaces heavy mechanical leading edge devices with a lightweight fluidic actuator system. The actuator uses compressed air storage and controlled release to generate flow control effects, eliminating the need for complex mechanical high lift devices while achieving similar or superior flow attachment performance with significantly reduced weight.
Solution Approach 2:
The system employs periodic pulsing of compressed air through the fluidic actuator to maintain flow attachment. By delivering controlled pulses of air at optimal frequencies, the system creates sustained vortical structures that prevent separation, replacing continuous mechanical device deployment with intermittent pneumatic actuation.
3Reliability
If passive vortex generators are used, then some flow attachment is achieved, but parasitic drag increases in normal flight conditions
Solution Approach 1:
The patent implements a dynamic flow control system where the fluidic actuator can be activated or deactivated based on flight conditions. During normal flight, the system remains inactive avoiding parasitic drag, while during high lift conditions it activates to provide flow attachment, creating an adaptive system that optimizes performance across different operating regimes.
Solution Approach 2:
The system changes the operational state of flow control by introducing compressed air pulses only when needed. By controlling the activation parameters of the fluidic actuator based on flight conditions, the system achieves flow attachment when required while minimizing energy loss during normal operation, unlike fixed passive vortex generators that continuously create drag.
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 effectively suppresses flow separation with minimal mechanical components, reducing manufacturing and maintenance costs while maintaining high lift capabilities, and can be adapted for various flow bodies like aircraft wings and wind turbines, enhancing aerodynamic performance.
Implementation Method 1
the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets
Implementation Method 2
utilizing control pressure ports to generate a pulsating flow without mechanical valves
Implementation Method 3
This ejection is able to delay separations to higher flow incident angles by introducing vortical structures, which convect downstream of the flow element thus energizing the otherwise separated flow area
Implementation Method 4
a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an inlet connectable to an air source, at least two outlets
Data Source
AI summary
A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings.