Rotary Wing Pitch Control System for Direct Thrust Management
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Solution Overview
Problem
High-speed rotary wing aircraft with variable pitch propeller systems require a new control and interface for pilots to directly manage propeller thrust output, as existing systems rely on turbojets and lack direct control mechanisms for propeller pitch adjustment.
Innovation Solution
A pitch control system with a switch that can be moved to various positions to generate commands for actuating propeller blades, allowing for manual or automatic adjustment of pitch angles based on airspeed and rotor revolutions per minute, enabling pilots to control propeller thrust output efficiently.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a variable pitch propeller system is introduced to provide translational thrust, then high speed flight capability is improved, but the complexity of the control system increases due to the need for direct propeller pitch control
Solution Approach 1:
A flight control computer serves as an intermediary between the pilot and the propeller pitch control system. The computer automatically calculates and adjusts pitch commands based on flight conditions (airspeed, rotor RPM), eliminating the need for direct pilot manipulation of complex pitch control mechanisms while enabling precise propeller thrust control for high speed flight.
Solution Approach 2:
The propeller pitch control system is designed to automatically adjust pitch angles based on measured flight parameters without requiring direct pilot intervention. The system self-regulates by comparing actual flight conditions with desired performance parameters and making autonomous pitch adjustments, thereby maintaining simplicity at the pilot interface while achieving complex control objectives.
2Ease of operation
If manual pitch control is implemented, then direct control over propeller thrust is achieved, but pilot workload increases
Solution Approach 1:
The flight control computer acts as an intelligent intermediary that translates simple pilot inputs into complex pitch control commands. The computer handles the computational burden of calculating optimal pitch angles based on multiple flight parameters, providing the pilot with intuitive control while eliminating the need to manually manage complex pitch adjustment mechanisms.
Solution Approach 2:
Manual mechanical pitch control mechanisms are replaced with an automated electro-mechanical system. The flight control computer generates electrical commands that automatically adjust propeller pitch, substituting complex mechanical pilot manipulations with an automated control system that reduces pilot workload while maintaining direct thrust control capability.
3Ease of operation
If automatic pitch control is used, then pilot workload is reduced, but the system requires complex sensors and computation
Solution Approach 1:
The flight control computer is designed as a multi-functional system that simultaneously performs multiple tasks: monitoring airspeed, measuring rotor RPM, calculating optimal pitch angles, and controlling propeller actuators. By consolidating these diverse functions into a single integrated computer system, the patent avoids the need for separate complex subsystems, thereby reducing overall system complexity while achieving automatic pitch control.
Solution Approach 2:
The system implements closed-loop feedback control where the flight control computer continuously monitors flight parameters (airspeed, rotor RPM), compares actual performance with desired performance, and automatically adjusts propeller pitch accordingly. This feedback mechanism enables simple pilot operation while the underlying complexity is managed through automated sensing and computation that continuously adapts to changing flight conditions.
Data Source
AI summary
A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.