Active Flow Control for Transonic Shock Wave Management
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Solution Overview
Problem
Existing air vehicles require complex infrastructure for flight control surfaces, increasing weight, manufacturing cost, and reducing performance, particularly during transonic flight.
Innovation Solution
An air vehicle with an airfoil designed for transonic flight featuring upstream and downstream orifices and an active flow control system that alters the strength and location of shock waves by controlling air flow through these orifices to create an aerodynamic imbalance, thereby controlling motion during transonic flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional flight control surfaces (flaps, spoilers, ailerons, rudders, elevators, fins) with hinge structures, hydraulic or pneumatic actuators, and fluid delivery systems are used, then vehicle control during transonic flight is achieved, but vehicle complexity, manufacturing cost, and weight increase, and vehicle performance is reduced
Solution Approach 1:
The patent extracts and eliminates the complex mechanical infrastructure (hinge structures, actuators, fluid delivery systems) by using only small orifices in the airfoil surface. The control function is achieved through pure aerodynamic manipulation via controlled air injection through these minimal openings, removing unnecessary mechanical components while maintaining control capability
Solution Approach 2:
Instead of using large-scale mechanical control surfaces that affect the entire vehicle, the invention applies localized air injection through small orifices at specific positions on the airfoil. This local quality approach allows precise control with minimal infrastructure, targeting specific flow regions to achieve desired vehicle response
2Reliability
If traditional flight control surfaces with substantial infrastructure are used, then vehicle control is achieved, but weight increases
Solution Approach 1:
The patent removes the heavy mechanical infrastructure (actuators, hinge structures, fluid delivery systems) and replaces it with a minimal orifice system. The control function is achieved through aerodynamic forces generated by controlled air injection, eliminating the need for heavy mechanical components while maintaining control effectiveness
Solution Approach 2:
The invention replaces the mechanical control system (actuators moving physical surfaces) with an aerodynamic control system that uses controlled air injection through orifices. This substitution eliminates mechanical weight by using fluid dynamics principles to achieve control through pressure and flow manipulation rather than mechanical movement
3Productivity
If controlled air flow through orifices is used to alter shock wave strength and location, then response time increases and performance is enhanced, but system complexity increases
Solution Approach 1:
The patent extracts the essential control function from complex mechanical systems and implements it through a simplified orifice-based aerodynamic system. The active flow control achieves rapid response by directly manipulating air flow through orifices to alter shock wave characteristics, eliminating the response delays inherent in mechanical actuation systems
Solution Approach 2:
The invention controls vehicle response by changing aerodynamic parameters (air flow rate, pressure, and distribution) through the orifices rather than changing mechanical configurations. By modulating these flow parameters, the system achieves rapid response times as aerodynamic changes occur instantaneously compared to mechanical movement
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 solution reduces the complexity and weight of flight control systems, enhances performance by allowing faster response times and reduced aeroacoustic noise, and maintains vehicle control with less infrastructure compared to traditional systems.
Implementation Method 1
The airfoil has a region of supersonic flow during transonic flight. A surface of the airfoil has upstream and downstream orifices at or within the region. The active flow control system controls flow through the orifices to alter strength and location of a shock wave in the region.
Implementation Method 2
The system creates an aerodynamic imbalance to move the shock wave.
Data Source
AI summary
An air vehicle includes an airfoil designed for transonic flight. The airfoil has a region of supersonic flow during transonic flight. A surface of the airfoil has upstream and downstream orifices at or within the region. The air vehicle further includes an active flow control system for controlling air vehicle motion during transonic flight by controlling flow through the orifices to alter strength and location of a shock wave in the region. The system creates an aerodynamic imbalance to move the shock wave.