Rotorcraft Yaw Control System Using Electrical Actuation
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Solution Overview
Problem
Current yaw control systems for rotorcraft face challenges such as inconsistent rotorcraft rotation rates due to external environments, mechanical friction in kinematic chains, and involuntary pilot interventions, leading to reduced pilot comfort and stability issues.
Innovation Solution
A yaw control system incorporating a third kinematic chain with objective piloting means, allowing the pilot to control the anti-torque rotor blades via electrical signals and actuators, independent of the rudder bar, to improve interface efficiency and stability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a traditional rudder bar with mechanical kinematic chain is used for yaw control, then the pilot can directly control the anti-torque rotor, but mechanical friction and external environment influences cause inconsistent rotorcraft rotation rates and reduced pilot comfort
Solution Approach 1:
The patent replaces the traditional mechanical kinematic chain connecting the rudder bar to the anti-torque rotor with an electrical control system. The pilot's inputs are converted to electrical signals that directly control the rotor blades' pitch angle, eliminating mechanical friction and play in linkages. This substitution of mechanical transmission with electrical control resolves the contradiction by providing both smooth operation (improved comfort) and precise, consistent control (improved reliability).
Solution Approach 2:
The patent introduces an intermediary computational system between the pilot's control inputs and the anti-torque rotor actuation. This intermediary processes pilot commands, calculates appropriate rotor blade pitch adjustments, and coordinates with the main rotor system to achieve desired yaw motion. This intermediary layer filters out mechanical imperfections and provides consistent, predictable control response, resolving the contradiction between ease of operation and control stability.
2Adaptability or versatility
If the rudder bar is replaced by a control column or joystick, then paraplegic pilots can control yaw, but the interface complexity increases and may not solve all control precision issues
Solution Approach 1:
The patent implements a universal control system where the primary flight control stick serves multiple functions: it controls both the main rotor (for pitch and roll) and the anti-torque rotor (for yaw). By making the control stick multi-functional and integrating all three degrees of freedom into a single interface, the system achieves adaptability for various pilot abilities while avoiding the complexity of multiple separate control devices. The electrical control system accommodates different pilot physical capabilities without requiring specialized control mechanisms.
3Adaptability or versatility
If multiple kinematic chains are used for different control functions, then each control function can be independently implemented, but the overall system complexity increases and coordination becomes difficult
Solution Approach 1:
The patent merges the previously separate kinematic chains for main rotor control and anti-torque rotor control into a unified electrical control system. Instead of having independent mechanical linkages for each control function, the system uses a single electrical architecture that can independently control all rotor systems. This merging reduces overall mechanical complexity while maintaining the independence of control functions through software-based control logic that can selectively actuate different control surfaces as needed.
Data Source
AI summary
The device has a kinematic chain that integrates a target control unit (16) whose setting in work is placed under dependence of a movable control element (12) trained by a man. The movable control element transmits a control signal (11) toward another target control unit (17), which generates a control command (29) in yaw towards a calculation unit of another kinematic chain, where the command in yaw is relative in a progression state to reach a rotorcraft (1). Implementation of the calculation unit is placed under dependence of a control button actuated by the man. An independent claim is also included for a method for controlling flight in yaw of a rotorcraft.