Cooperative Flow Actuators for Low-Energy Separation Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing active flow control systems for aircraft and vehicles are inefficient in terms of energy consumption, weight, size, and noise, and require significant resources to operate effectively, while also being limited in design flexibility and performance.
Innovation Solution
A cooperative actuator system comprising multiple groups of actuators and a control unit that form and interact with flow structures to optimize flow control, reducing energy and resource requirements, and enabling lighter, smaller, and quieter systems with enhanced performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional fluidic actuators with valves are used for active flow control, then flow separation can be prevented and lift can be increased, but energy consumption and resource requirements increase significantly
Solution Approach 1:
The actuator system is divided into multiple independent actuator units distributed along the surface, each capable of being controlled independently. This segmentation allows for more efficient energy distribution and reduces the overall energy requirement compared to a single centralized system with valves.
Solution Approach 2:
The actuators operate by generating periodic pulsed ejecta flows rather than continuous flow. This periodic action reduces average energy consumption while maintaining effectiveness in preventing flow separation, as the pulsed nature allows for energy recovery periods and reduces continuous resource requirements.
2Productivity
If conventional active flow control systems are implemented, then aerodynamic performance can be improved, but the system weight and size increase
Solution Approach 1:
By segmenting the actuator system into multiple small distributed units rather than one large centralized system, the overall weight is reduced while maintaining aerodynamic effectiveness. Each small actuator unit requires minimal structural support and can be integrated more efficiently into the aircraft structure.
Solution Approach 2:
The system transitions from a traditional valve-based mechanical control approach to a distributed array of actuators operating in spatial distribution along the surface. This dimensional change from centralized to distributed architecture reduces the need for heavy mechanical components and allows for more efficient weight distribution.
3Productivity
If traditional fluidic actuators are used, then flow control can be achieved, but noise and structural loads increase
Solution Approach 1:
Distributing the flow control function across multiple small actuator units reduces the noise and structural load generated by each individual actuator compared to a single large actuator system. The segmented approach allows for better noise dispersion and reduces concentrated structural loading.
Solution Approach 2:
The periodic pulsed operation of the actuators reduces continuous noise generation and allows for quieter operation between pulses. This periodic action also reduces continuous structural loading, allowing the structure to relax between actuation cycles and reducing fatigue loads.
4Adaptability or versatility
If conventional actuator systems are used for flow control, then basic flow influence is possible, but design flexibility and performance optimization are limited
Solution Approach 1:
The distributed array of independent actuator units provides greater design flexibility compared to conventional valve-based systems. Each actuator can be independently controlled and optimized for specific local flow conditions, allowing for tailored flow control strategies across different regions of the aircraft surface.
Solution Approach 2:
The system employs dynamic control of multiple actuators with adjustable pulsation frequencies, duty cycles, and momentum injection parameters. This dynamic capability allows the system to adapt to varying flight conditions and optimize performance in real-time, providing versatility that static conventional systems cannot achieve.
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 cooperative actuator system achieves a significant reduction in energy and mass flow, allowing for more efficient flow control with reduced structural loads and noise, while increasing design space and performance, and enabling the use of various actuation devices for flow control tasks.
Implementation Method 1
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 2
Flow bodies as parts of an aircraft, a vehicle or of another apparatus subjected to a surrounding flow are often required to show aerodynamic characteristics that result in a substantially fully attached flow
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
The invention relates to a cooperative actuator system (20) for active flow control, an aircraft, vehicle, boat or automobile comprising such cooperative actuator system, and a method for operating an actuator system for active flow control. The cooperative actuator system (20) comprises a plurality of actuators (10), a control unit (21), and a data unit (22). The plurality of actuators (10) is configured to be distributed along the surface (6) in at least a first group and a second group downstream of the first group. The control unit (21) is configured to control the actuators of the first group so that they form a first flow structure along the surface (6). The data unit (22) is configured to provide data of the first flow structure. The control unit (21) is further configured to control the actuators of the second group based on the data of the first flow structure, so that the actuators of the second group cooperatively interact with the first flow structure to form a second flow structure along the surface (6).