Aircraft Electronic Flight Control System for Rotor Speed Adaptation
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Solution Overview
Problem
Existing electronic flight control systems for helicopters are inflexible and limited in their ability to safely and automatically control rotor speed, particularly in critical conditions, which can lead to loss of control or damage during transitions between low and high rotor speed modes.
Innovation Solution
An electronic flight control system that allows for flexible and mission-adaptable control of rotor speeds, using a block diagram architecture with a pilot control block, FADEC block, speed control block, and sensors to adjust rotor speeds based on flight parameters and conditions, enabling automatic mode selection between high-performance and low-noise modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If automatic electronic flight control systems switch between low and high rotor speed modes based on flight information, then noise reduction is achieved in normal conditions, but safety and control stability are compromised in critical conditions
Solution Approach 1:
The system dynamically adapts control strategies based on flight conditions. In normal conditions, automatic switching between speed modes reduces noise. In critical conditions, the system dynamically shifts to manual control mode, allowing the pilot to override automatic control and maintain full authority over rotor speed, thus ensuring safety while managing noise
Solution Approach 2:
The system changes the control parameter from fully automatic to manual based on detected critical conditions. When critical conditions are detected, the system parameter changes the level of automation, disengaging automatic control and transferring authority to the pilot, thereby resolving the conflict between noise reduction and safety
2Ease of operation
If automatic flight control systems rigidly control rotor speed switching based on flight information, then operational simplicity is maintained, but adaptability to critical conditions and personalized missions is limited
Solution Approach 1:
The system provides dynamic adaptability by allowing mode switching between automatic and manual control based on mission requirements and critical conditions. The pilot can select different operational modes (automatic, manual, semi-automatic) to match specific mission profiles, enabling the system to adapt to diverse scenarios while maintaining ease of operation through automated assistance in normal conditions
3Object-generated harmful factors
If rotor speed is reduced to minimize noise, then noise levels decrease, but control authority and emergency response capability are compromised
Solution Approach 1:
The system prepares for potential emergencies by maintaining the capability for immediate high-speed response. The automatic control system is designed to quickly transition to high rotor speed modes when critical conditions are detected or when the pilot initiates emergency procedures, ensuring that noise reduction during normal operation does not compromise emergency response capability
Solution Approach 2:
The system dynamically adjusts rotor speed based on operational requirements. During normal operation, reduced speeds minimize noise. Upon detecting critical conditions or emergency inputs, the system dynamically increases rotor speed to maximum levels, restoring full control authority and emergency response capability when needed
Data Source
AI summary
An electronic flight control system for an aircraft capable of hovering and having at least one rotor. The flight control system is configured to operate in a manual flight control mode, in which the flight control system controls rotor speed in response to direct commands from the pilot; and in at least two automatic flight control modes corresponding to respective flight modes of the aircraft, and in which the flight control system controls rotor speed automatically on the basis of flight conditions. The flight control system is also configured to memorize, for each automatic flight control mode, a respective flight table relating different speed values of the rotor to different values of at least one flight quantity; and to automatically control rotor speed in the automatic flight control modes on the basis of the respective flight tables.