Sonic Boom Control via Wing Morphing and Fuel Redistribution
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Solution Overview
Problem
Supersonic aircraft experience shape changes during flight due to variations in weight and speed, leading to deviations in lift distribution and increased sonic boom magnitude, which existing technologies fail to effectively mitigate.
Innovation Solution
A system and method that utilize sensors, processors, and control surfaces to detect deviations in lift distribution and redistribute fuel or adjust wing geometry to counteract wing twist and maintain desired lift distribution, thereby reducing sonic boom magnitude.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the supersonic aircraft operates at off-design conditions (varying weight and speed), then the aircraft can adapt to different flight requirements, but the shape changes cause lift distribution deviations and increased sonic boom magnitude
Solution Approach 1:
The patent applies dynamics by making the wing geometry changeable through morphing capabilities. The wing can dynamically adjust its shape (camber, twist, sweep) in response to varying flight conditions such as weight and speed changes. This dynamic adaptation allows the aircraft to maintain optimal lift distribution across different operating points, thereby reducing sonic boom magnitude while preserving flight condition adaptability.
Solution Approach 2:
The patent utilizes parameter changes by modifying physical parameters of the wing such as camber, twist, and sweep angles. These geometric parameters are actively adjusted based on detected flight conditions (weight, speed) to optimize lift distribution. By changing these parameters, the system maintains consistent sonic boom characteristics despite operating away from design conditions.
2Force
If the wing deflects up or down to accommodate weight and speed variations, then the aircraft can maintain lift, but the wing twist increases and causes lift distribution to vary from desired distribution
Solution Approach 1:
The patent applies local quality by implementing distributed actuators along the wing span that can independently adjust local wing section properties. Rather than uniform wing deflection, different sections of the wing can be locally adjusted to compensate for twist effects. This localized control allows the wing to maintain proper twist distribution and lift characteristics even when overall wing deflection is required for weight and speed variations.
Solution Approach 2:
The patent utilizes feedback by employing sensors to detect actual wing deflection and twist conditions, then using this information to drive actuators that counteract unwanted twist. The system continuously monitors flight conditions and wing geometry, comparing actual state with desired state, and applies corrective actions through actuator control to maintain optimal lift distribution and minimize sonic boom.
Data Source
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AI summary
A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system still further includes a processor communicatively coupled to the sensor and operatively coupled with the control surface. The processor is configured to (1) receive information from the sensor indicative of the condition of the supersonic aircraft, (2) determine that there is a deviation between a lift distribution and a design-condition lift distribution based on the information, and (3) control the control surface to move in a manner that reduces the deviation. The magnitude of the sonic boom is reduced when the deviation is reduced.