Rotor Blade Proximity Control via Flight Parameter Adjustment
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Solution Overview
Problem
Tilt-rotor and rotor-wing aircraft face challenges in maintaining safe rotor blade clearance from non-rotating components due to coning and flapping, leading to potential collisions, and existing solutions increase aircraft weight and affect aerodynamics.
Innovation Solution
Incorporating a flight control system with proximity sensors and antennas on rotor blades to measure and control blade clearance, initiating corrective actions when blades approach a minimum safe distance from non-rotating components, thereby adjusting flight parameters to maintain safe distances without adding weight or compromising aerodynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the rotor assembly is extended further away from non-rotating components, then rotor blade clearance safety is improved, but aircraft weight increases and aerodynamics are adversely affected
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 position using proximity sensors and feeds this information back to the flight control computer. Based on the feedback, the computer dynamically adjusts flight parameters to maintain safe clearance, creating a closed-loop control system that ensures reliability without adding structural weight.
2Reliability
If the rotor assembly is extended further away from non-rotating components, then rotor blade clearance safety is improved, but aerodynamic performance deteriorates
Solution Approach 1:
The patent replaces the mechanical modification of extending the rotor assembly with an electronic control system that uses proximity sensors and flight parameter adjustment. This substitution maintains the original aerodynamic configuration while achieving safe clearance through active control, preserving aerodynamic performance.
Solution Approach 2:
The system dynamically adjusts flight parameters in real-time based on rotor blade position feedback. This dynamic control allows the aircraft to maintain safe clearance during various flight conditions without requiring static structural modifications that would compromise aerodynamic efficiency.
3Reliability
If proximity sensors and flight control systems are implemented, then rotor blade clearance control is improved, but device complexity increases
Solution Approach 1:
The patent integrates the proximity control function into the existing flight control computer, which already performs multiple flight control functions. By utilizing the existing multi-functional platform, the system avoids adding separate dedicated hardware systems, thereby limiting the increase in overall device complexity while achieving improved clearance control.
Solution Approach 2:
The proximity sensing and clearance control functions are merged with the existing flight control system rather than being implemented as a separate system. This integration consolidates control functions and reduces the number of independent components, thereby managing device complexity while improving rotor blade clearance 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
Effectively manages rotor blade clearance to prevent collisions while optimizing aircraft performance by using proximity sensors and flight control systems to adjust blade positions dynamically, ensuring safe operation without the drawbacks of increased weight or aerodynamic impact.
Implementation Method 1
measuring, via a proximity sensor, a position of a rotor blade relative to a leading edge of a wing
Data Source
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AI summary
The aircraft includes a rotor (115). The rotor (115) includes a plurality of rotor blades (119). The aircraft further includes a non-rotating aircraft component. A proximity sensor (406) is disposed with at least one of the non-rotating aircraft component and the rotor blades (119). A flight control computer (304) is electrically coupled to the proximity sensor.