Aircraft Yoke Control System with Breakable Link
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Solution Overview
Problem
Current aircraft control systems require two humans at separate locations for mission-critical redundancies, lacking remote access and efficiency, especially in scenarios where one pilot is less qualified or incapacitated, and there is a need for reduced costs and enhanced safety.
Innovation Solution
A method and system that combines inputs from two control yokes, utilizing a pre-programmed robot arm with a breakable connection element to allow remote operation, enabling a single pilot to control an aircraft with assistance from a remote pilot, and includes features like emergency stop, video streaming, and automated landing sequences.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If two separate control stations are provided for mission-critical redundancy, then safety and reliability are improved, but device complexity and personnel requirements increase
Solution Approach 1:
The patent combines two separate control stations into a single integrated control system where a first control device and second control device are merged into one aircraft control system. The first input from the first control device and second input from the second control device are combined to control the aircraft, eliminating the need for two separate physical control stations while maintaining redundancy through the ability to receive inputs from both control devices simultaneously.
Solution Approach 2:
The control system is designed to perform multiple functions: it can operate with both control devices simultaneously for normal dual-pilot operations, switch to single-control-device operation when one pilot is incapacitated, and provide remote access capabilities. This multi-functionality allows the system to maintain reliability under various operational scenarios without requiring separate dedicated systems for each mode.
2Reliability
If two pilots are required to operate the aircraft, then safety through redundancy is improved, but operational efficiency and cost increase
Solution Approach 1:
The control system dynamically adapts its configuration based on operational needs. During normal operations, both control devices can be used simultaneously for enhanced control authority. When one pilot becomes incapacitated or during certain phases of flight, the system can operate with a single control device. The connection element can be dynamically connected or disconnected based on the situation, allowing the system to optimize between redundancy and efficiency in real-time.
Solution Approach 2:
The patent extracts the essential redundancy function from requiring two physically present pilots and implements it through the control system architecture itself. The second control device and its associated pilot can be physically removed or disconnected when not needed, yet the system maintains the capability for redundant control through the preservable input from the second control device, thereby improving operational efficiency without sacrificing safety.
3Ease of operation
If a robot arm is used for remote control access, then ease of operation and accessibility are improved, but device complexity increases
Solution Approach 1:
The robot arm serves as an intermediary device that physically connects to and operates the control devices. Instead of requiring a remote operator to directly manipulate controls over a communication link, the robot arm acts as a mechanical mediator that can be remotely controlled to perform control inputs. This intermediary approach simplifies remote operation while the modular design of connecting the robot arm to the existing control system minimizes the increase in overall system complexity.
Data Source
AI summary
An approach is disclosed for directing an aircraft. A first yoke is connected to a second yoke by a connection element where a first input force applied to the first yoke is added to a second input force applied to the second yoke to form a resulting force and where the resulting force is applied to an aircraft control surface used for directing the aircraft. When a difference between the first input force and the second input force exceeds a predetermined value, the second yoke is disconnect preventing the second input force from contributing to the resulting force.