Flight Guidance Knob Interface for Reconfigurable Autopilot Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Traditional flight guidance controller units for aircraft are cumbersome, requiring numerous physical components and hardware changes for customization, which affects reliability, maintainability, and cost, while also being less adaptable to different cockpit philosophies.
Innovation Solution
A flight guidance controller interface featuring a rotatable knob with a touch control display that allows for the selection and setting of multiple target parameters through graphical sections, reducing the number of physical parts and enabling easier customization by using a single knob to control various functions, such as altitude, vertical speed, and flight path angle.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional flight guidance controller units use multiple physical components (knobs, buttons, switches) for different functions, then each function can be controlled independently, but the number of parts increases and reliability decreases
Solution Approach 1:
The patent combines multiple separate control functions (heading control, course control, altitude control, vertical speed control) into a single integrated flight guidance controller unit. This single unit uses a touch-sensitive display with a rotatable element that can selectively activate different control functions, eliminating the need for multiple separate physical components and thereby improving reliability while reducing part count.
Solution Approach 2:
The single flight guidance controller unit is designed to perform multiple functions through a unified interface. The touch-sensitive display with rotatable element can activate different control modes (heading, course, altitude, vertical speed) depending on the selected function, allowing one device to replace multiple specialized components while maintaining full functionality.
2Adaptability or versatility
If traditional flight guidance controller units are customized for different cockpit installations, then specific cockpit philosophies can be accommodated, but hardware changes are required which increase cost and complexity
Solution Approach 1:
The flight guidance controller incorporates a dynamic, reconfigurable interface where the touch-sensitive display can present different functional sections based on user selection. The system can adapt its control modes and displayed parameters (heading, course, altitude, vertical speed) through software configuration rather than hardware changes, enabling customization for different cockpit philosophies without physical modifications.
Solution Approach 2:
The patent replaces traditional mechanical control components (physical knobs, buttons, switches) with an electronic touch-sensitive display and rotatable element. This substitution allows for software-based reconfiguration and customization of control functions, eliminating the need for hardware changes when adapting to different cockpit installations while maintaining full adaptability.
3Adaptability or versatility
If traditional flight guidance controller units use numerous electronic parts and movable elements, then multiple functions can be implemented, but maintainability and cost of maintenance increase
Solution Approach 1:
By consolidating multiple control functions into a single integrated unit with a touch-sensitive display and rotatable element, the patent reduces the total number of electronic parts and movable elements. This consolidation improves maintainability as there are fewer components that can fail, while still providing comprehensive functionality through the unified interface that can activate different control modes as needed.
Data Source
Figure 1
Figure 2
Figure 3A~3C
AI summary
Methods and systems are provided including a flight guidance controller interface. The flight guidance controller interface includes a rotatable knob including a rotatable element disposed around a periphery of a touch control display. A graphical presentation is output on the touch control display including a plurality of sections. The plurality of sections includes an indication of respective functions of an automatic flight control system. A touch input is received to one of the plurality of sections, thereby activating control of a corresponding one of the respective functions of the automatic flight control system. A rotation input to the rotatable element is received, thereby providing information about a value for the corresponding one of the respective functions of the automatic flight control system. The information about the value is output to the automatic flight control system so that the automatic flight control system can responsively control aircraft trajectory while maintaining/honoring selected target references and values.