Aircraft Rotor Blade Proximity Control via Sensor Feedback
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Solution Overview
Problem
Tilt-rotor and rotor-wing aircraft experience coning or flapping, causing rotor blades to displace relative to non-rotating components, leading to potential unsafe proximity issues, which existing solutions address through pilot training and aerodynamic adjustments that increase weight and impact performance.
Innovation Solution
A flight control system with proximity sensors (ultrasonic, LiDAR, pressure, or tripwire) measures rotor blade positions relative to non-rotating components and initiates corrective actions via actuators or servo motors when blades approach a minimum safe distance, ensuring safe clearance without weight penalties.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If rotor assembly is extended further away from non-rotating components, then rotor blade clearance is improved, but aircraft weight increases and aerodynamics are negatively impacted
Solution Approach 1:
The patent replaces the mechanical solution of extending the rotor assembly with an electronic control system. Proximity sensors detect the distance between rotor blades and non-rotating components, and the flight control computer automatically adjusts flight parameters to maintain safe clearance, eliminating the need for additional structural extensions that would increase weight.
Solution Approach 2:
The system continuously monitors rotor blade proximity to non-rotating components using sensors and provides real-time feedback to the flight control computer. This closed-loop control enables dynamic adjustment of flight parameters to maintain safe clearance without requiring permanent structural modifications that would increase aircraft weight.
2Reliability
If rotor assembly is extended further away from non-rotating components, then rotor blade clearance is improved, but aerodynamic performance deteriorates
Solution Approach 1:
The patent replaces the mechanical solution of extending the rotor assembly with an electronic control system. Proximity sensors detect the distance between rotor blades and non-rotating components, and the flight control computer automatically adjusts flight parameters to maintain safe clearance, eliminating the need for additional structural extensions that would disrupt aerodynamics.
3Ease of operation
If pilot training and flight control software are used to address rotor blade clearance, then operational procedures are improved, but system complexity increases
Solution Approach 1:
The system enables the aircraft to monitor and adjust its own rotor blade clearance automatically through proximity sensors and flight control computer integration. This self-service capability reduces reliance on pilot training and manual procedures, simplifying the overall system by automating the clearance management function.
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 system effectively maintains safe rotor blade clearance without adding weight, improving aerodynamics and reducing the risk of collisions by dynamically adjusting flight parameters in response to real-time blade positions.
Implementation Method 1
The proximity sensor can comprise one or more of an ultrasonic sensor, a pressure sensor, a LiDAR sensor, or a tripwire
Implementation Method 2
The proximity sensor can comprise one or more of an ultrasonic sensor, a pressure sensor, a LiDAR sensor, or a tripwire
Implementation Method 3
The proximity sensor can comprise one or more of an ultrasonic sensor, a pressure sensor, a LiDAR sensor, or a tripwire
Implementation Method 4
at least one of an actuator and a servo motor electrically coupled to the flight control computer, the at least one of the actuator and the servo motor operable to control a flight parameter
Data Source
AI summary
The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.