Shock Wave Manager for Transonic Aircraft Drag Reduction
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft traveling at transonic speeds face challenges in managing shock waves, which increase drag and affect aerodynamic properties, as existing methods fail to effectively monitor and control these shock waves in real-time.
Innovation Solution
The implementation of a shock wave manager apparatus using multiple cameras and position calculators to capture and analyze images of shock waves, employing background-oriented schlieren techniques and deformation compensation methods to determine shock wave positions and strengths, and generating commands to control actuators or control surfaces based on these calculations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If multiple cameras and image processing systems are used to monitor shock waves in real-time, then measurement precision and reliability improve, but device complexity increases
Solution Approach 1:
The patent introduces a shock wave manager apparatus as an intermediary system that coordinates multiple cameras, position calculators, and command generators. This centralizing intermediary manages the complex interactions between multiple sensors and actuators, making the overall system more manageable while maintaining high measurement precision through multi-camera imaging
Solution Approach 2:
The monitoring system is segmented into distinct functional modules: multiple cameras for image capture, position calculators for shock wave position determination, and command generators for actuator control. This segmentation allows each component to be optimized independently while working together to achieve precise shock wave monitoring
2Productivity
If real-time shock wave monitoring and control is implemented, then aerodynamic performance improves, but use of energy increases
Solution Approach 1:
The system implements continuous real-time monitoring of shock waves using multiple cameras and continuous image processing to track shock wave position and strength. This continuous useful action enables dynamic adjustment of control surfaces and actuators to maintain optimal aerodynamic performance throughout flight conditions
Solution Approach 2:
The shock wave manager apparatus establishes a feedback loop where shock wave positions and strengths are continuously measured by cameras, processed to determine deviations from optimal conditions, and used to generate commands that adjust control surfaces. This closed-loop feedback system optimizes aerodynamic performance while managing energy consumption through intelligent control
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 enables real-time monitoring and control of shock waves, reducing drag and enhancing aerodynamic performance by accurately determining shock wave positions and strengths, allowing for optimal adjustment of aircraft surfaces and engines.
Implementation Method 1
a first camera at a first location on an aircraft to capture a first image of a surface of the aircraft
Implementation Method 2
employing background-oriented schlieren techniques to determine shock wave positions and strengths
Implementation Method 3
employing background-oriented schlieren techniques and deformation compensation methods to determine shock wave positions and strengths
Data Source
AI summary
Methods, apparatus, and articles of manufacture to monitor a shock wave proximate a surface of an aircraft are disclosed. An example apparatus includes a first camera at a first location on an aircraft to capture a first image of a surface of the aircraft during a first time period, and capture a second image of the surface during a second time period, a second camera at a second location to capture a third image of the surface during the first time period, and capture a fourth image of the surface during the second time period. The example apparatus further includes a position calculator to identify a first position of a shock wave based on the first and third images, and a second position based on the second and fourth images, and calculate a difference between the first and the second positions, and a command generator to generate a command to control at least one of an actuator and a control surface based on the difference.