Independent Speed and Attitude Control for Rotary Wing Aircraft
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Solution Overview
Problem
Conventional rotary wing aircrafts require manual coordination of attitude, position, speed, and altitude, which increases pilot workload and limits visibility and comfort during maneuvers and transitions, especially in slope landings.
Innovation Solution
A flight control system with a flight control computer that interfaces with the main rotor and translational thrust systems, executing control logic for independent speed and attitude control, including a pitch attitude reference generator, longitudinal reference generator, attitude-to-propulsor crossfeed, main rotor controller, and propeller pitch controller, to automate and prioritize control inputs based on pilot commands.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If manual control of propulsor pitch is provided using a beeper, then control of additional degree of freedom is enabled, but pilot workload significantly increases
Solution Approach 1:
The system enables self-service control by implementing automatic coordination between the main rotor controller and propeller pitch controller. The flight control computer autonomously manages the additional degree of freedom provided by the propulsor, eliminating the need for manual beeper input while maintaining enhanced control capability.
Solution Approach 2:
The patent merges the control functions of the main rotor system and translational thrust system into a unified flight control computer. This integration automatically coordinates pitch attitude and longitudinal speed control, combining multiple control functions into a single automated system that reduces pilot workload while maintaining versatility.
2Speed
If conventional helicopter uses attitude change to control aircraft speed, then speed control is achieved, but visibility and ride comfort are impacted
Solution Approach 1:
The patent segments the speed control function from the attitude control function. The main rotor controller manages pitch attitude independently while the propeller pitch controller handles longitudinal speed, allowing speed changes without compromising attitude stability and thereby preserving visibility and ride comfort.
Solution Approach 2:
The flight control computer acts as an intermediary that coordinates between pilot inputs and the separate control systems. It translates speed demands into appropriate propeller pitch adjustments while maintaining optimal attitude, mediating between speed control requirements and comfort/visibility constraints.
3Stability of the object's composition
If hybrid helicopter hovers at fixed pitch attitude, then stability is maintained, but ability to hover at various attitudes for optimal visibility and transitions is limited
Solution Approach 1:
The system implements dynamic control where the flight control computer continuously adjusts both main rotor pitch and propeller pitch based on real-time flight conditions. This dynamic coordination enables the helicopter to maintain stable hover at various attitudes by actively managing the interaction between rotor thrust and propeller thrust.
Solution Approach 2:
The patent utilizes parameter changes in both the main rotor system and translational thrust system to achieve versatile hover attitudes. By independently adjusting pitch attitudes and propeller pitch, the system can optimize visibility and transition characteristics while maintaining hover stability through coordinated control.
Data Source
AI summary
One aspect is a flight control system for independent speed and attitude control of a rotary wing aircraft that includes a main rotor system and a translational thrust system. The flight control system includes a flight control computer configured to interface with the main rotor system and the translational thrust system. The flight control computer includes processing circuitry configured to execute control logic. A pitch attitude reference generator provides a pitch attitude reference to a main rotor controller to command the main rotor system based on pilot input. A longitudinal reference generator produces a longitudinal reference as a longitudinal position or longitudinal velocity based on pilot input. An attitude-to-propulsor crossfeed converts the pitch attitude reference into a propulsor trim adjustment. A propeller pitch controller combines the longitudinal reference and the propulsor trim adjustment into a propeller command, and provides the propeller command to the translational thrust system.