Automatic Yaw Axis Control for Mechanical Aircraft
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Solution Overview
Problem
Aircraft with mechanical flight controls face high pilot workload and passenger discomfort due to asymmetrical flight caused by lateral forces, especially during engine failures, as pilots must constantly adjust rudder pedals and trim controls to maintain symmetry, leading to increased fuel consumption and risk of stalling.
Innovation Solution
An automatic yaw axis control method that simultaneously controls the yaw actuator and yaw trim actuator, using sensors to estimate lateral forces and calculate setpoints and trim commands to reduce torque oscillations, thereby reducing pilot workload and enhancing flight symmetry.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the pilot manually controls yaw using rudder pedals and trim controls, then the aircraft can be operated with mechanical flight controls, but the pilot workload becomes heavy and passenger comfort deteriorates due to constant adjustments needed to counteract lateral forces
Solution Approach 1:
The system enables automatic yaw axis control where the flight control system autonomously manages yaw control surfaces and trim surfaces without continuous pilot intervention. The control system self-adjusts to counteract lateral forces, reducing pilot workload while maintaining aircraft symmetry and passenger comfort
Solution Approach 2:
The patent replaces manual mechanical control operations with an automated electronic control system that processes sensor data and actuates control surfaces. This substitution eliminates the need for constant manual adjustments while preserving the mechanical flight control architecture
2Reliability
If the pilot constantly adjusts trim controls to maintain flight symmetry, then lateral forces can be counteracted, but fuel consumption increases and the risk of asymmetrical stalling during engine failures rises
Solution Approach 1:
The system continuously monitors flight parameters including lateral forces, aircraft attitude, and control surface positions. This feedback loop enables the automatic control system to detect asymmetrical conditions and adjust yaw control surfaces and trim surfaces in real-time to maintain flight symmetry, reducing fuel consumption and preventing asymmetrical stalling during engine failures
Solution Approach 2:
The automatic control system proactively maintains flight symmetry by continuously adjusting control surfaces before asymmetrical conditions can develop into critical situations. During engine failures, the system immediately counteracts lateral forces, preventing the development of asymmetrical stalling conditions
3Ease of operation
If mechanical flight controls are used without automatic yaw control, then the aircraft structure remains simple, but passenger comfort deteriorates due to asymmetrical flight and the pilot must maintain constant attention
Solution Approach 1:
The automatic yaw control system autonomously manages yaw axis control without requiring pilot intervention. The system self-adjusts control surfaces and trim surfaces to maintain flight symmetry, ensuring passenger comfort while preserving the mechanical flight control architecture and minimizing the extent of automation required
Data Source
AI summary
A method for automatic yaw axis control in aircraft with mechanical controls, said aircraft including a yaw actuator to control orientation of a yaw control surface and deliver a measured value of the torque on the control surface, a yaw trim actuator driving movement of a yaw trim control surface limiting the force applied by the yaw actuator to orient the yaw control surface, and sensors supplying an estimate of a lateral yaw force, includes calculating a setpoint value for the position of the yaw control surface determined by the estimated lateral force, an estimated torque of the yaw actuator determined by the measured value of the torque of the yaw actuator and a measured position of the yaw control surface, the estimated torque calculated having a lower oscillation dynamic range than the measured torque, and a trim command for activating/deactivating the yaw trim actuator determined by the estimated torque.