Rotorcraft Autorotation Control for Rotor Speed Stabilization
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Solution Overview
Problem
Current rotorcraft flight control systems are inadequate in automating the entry into autorotation and maintaining stabilized autorotation, relying heavily on pilot recognition and manual intervention, which can lead to excessive loss of rotor speed and increased pilot workload during engine failure.
Innovation Solution
A system that utilizes a full-authority aircraft flight control system to automatically adjust collective pitch and provide tactile cueing, employing model-matching techniques for quicker response and axis decoupling, allowing for direct control of main rotor swashplate and tail rotor collective pitch to maintain rotor speed and reduce pilot workload.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If pilot recognition and manual intervention are used to enter autorotation, then pilot control and decision-making are maintained, but excessive loss of rotor speed occurs and pilot workload increases
Solution Approach 1:
The flight control system automatically detects engine failure conditions and executes autorotation entry procedures without pilot intervention. The system monitors engine parameters, identifies failure conditions, and autonomously adjusts collective pitch and rotor controls to maintain autorotation, making the system self-serve during critical failure scenarios
Solution Approach 2:
The system continuously monitors engine failure conditions and rotor speed parameters, using this feedback to automatically adjust control surfaces and collective pitch. The feedback loop enables real-time optimization of autorotation entry and maintenance, ensuring rotor speed is preserved while reducing pilot workload
2Speed
If traditional flight control systems are used, then system simplicity is maintained, but response time to engine failure is insufficient
Solution Approach 1:
The system pre-configures autorotation control parameters and automatically executes pre-programmed control sequences upon detecting engine failure. By having control actions prepared in advance and automatically initiating them, the system achieves rapid response without requiring complex real-time calculations during the critical failure moment
Solution Approach 2:
The patent replaces manual mechanical control operations with an automated electronic flight control system. Sensors detect engine failure conditions and electronically actuate control surfaces and collective pitch, substituting pilot mechanical manipulation with automated electronic control to achieve faster response times
3Reliability
If manual cyclic manipulation is required to maintain rotor speed, then precise control is achieved, but pilot workload and complexity increase
Solution Approach 1:
The flight control system automatically maintains rotor speed during autorotation by continuously monitoring rotor RPM and autonomously adjusting collective pitch and cyclic controls. The system serves itself by detecting rotor speed deviations and executing corrective control actions without pilot intervention, ensuring precise rotor speed control while eliminating complex manual operations
Data Source
AI summary
The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation.