Aircraft Pressure Field Control via Movable Compression Surfaces
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Solution Overview
Problem
Supersonic aircraft face challenges in maintaining a pressure field without steep pressure gradients to comply with governmental sonic boom restrictions, as deviations in speed, atmospheric conditions, or propulsion system operation can lead to undesirable pressure gradients.
Innovation Solution
A system comprising pressure sensors and a controller that measure and adjust the pressure field by moving movable components such as extendable compression surfaces or flight control surfaces to reduce or eliminate steep pressure gradients, ensuring compliance with sonic boom limits.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If the aircraft operates at predetermined design conditions (speed, atmospheric conditions, throttle settings), then the pressure field remains free from steep pressure gradients and sonic boom magnitude complies with governmental limits, but any deviation from these conditions causes steep pressure gradients to form, increasing sonic boom magnitude beyond acceptable limits
Solution Approach 1:
The patent applies the dynamics principle by making the compression surface extendable and adjustable during flight. The compression surface can be extended forward from the engine inlet and repositioned dynamically in response to detected pressure field conditions, allowing the aircraft to maintain compliance with sonic boom limits across varying operational conditions rather than being restricted to fixed design conditions.
Solution Approach 2:
The patent implements feedback by using pressure sensors to continuously monitor the pressure field around the aircraft and feeding this information back to the control system. The controller compares the measured pressure field with the desired pressure field and automatically adjusts the compression surface position to reduce deviations, thereby maintaining sonic boom compliance through closed-loop control.
2Object-affected harmful factors
If the propulsion system operates at design conditions, then the pressure field remains stable without steep gradients, but operation at other conditions (different throttle settings, speeds, engine cycles) creates steep pressure gradients that increase sonic boom magnitude
Solution Approach 1:
The extendable compression surface provides dynamic adjustment capability that allows the propulsion system to operate across a wider range of conditions while maintaining pressure field stability. By adjusting the compression surface position in response to operating conditions, the system can mitigate steep pressure gradients even when the propulsion system operates away from design conditions.
Solution Approach 2:
The patent applies parameter changes by modifying the physical configuration of the compression surface (its position and extension) in response to changes in propulsion system operating parameters. This allows the pressure field to be maintained within acceptable limits across different throttle settings, speeds, and engine cycles by dynamically adjusting the compression surface geometry.
3Adaptability or versatility
If no active pressure field control is implemented, then the aircraft can operate freely without complex control systems, but the pressure field cannot be maintained without steep gradients when operating conditions deviate from design conditions
Solution Approach 1:
The control system uses feedback from pressure sensors to automatically adjust the compression surface, reducing the need for complex manual intervention or overly sophisticated control algorithms. The feedback loop continuously monitors pressure field conditions and makes automatic adjustments to maintain compliance.
Solution Approach 2:
The system applies self-service by using the aircraft's own pressure field measurements to automatically control the compression surface position. The pressure sensors and control system work together to self-regulate the pressure field without requiring external intervention or complex external control systems.
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
Effectively controls the pressure field around an aircraft in flight, reducing the magnitude of sonic booms to within regulatory limits by dynamically adjusting aircraft components in response to deviations from design conditions.
Implementation Method 1
a plurality of pressure sensors arranged on the aircraft to measure the pressure field
Implementation Method 2
transmit an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation
Data Source
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AI summary
A system for controlling a pressure field around an aircraft in flight is disclosed herein. In a non-limiting embodiment, the system includes, but is not limited to, a plurality of pressure sensors that are arranged on the aircraft to measure the pressure field. The system further includes, but is not limited to, a controller that is communicatively coupled with the plurality of pressure sensors. The controller is configured to receive information that is indicative of the pressure field from the plurality of pressure sensors. The controller is also configured to determine when the pressure field deviates from a desired pressure field based on the information. The controller is also configured to transmit an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation.