Avionics Control and Display Unit Reducing Weight
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Solution Overview
Problem
Avionics systems in aircraft face challenges in minimizing weight, size, electrical power usage, failure rates, and complexity, particularly due to the need for multiple mechanical or electro-mechanical gauges that provide limited functionality and take up valuable space, add weight, and increase maintenance needs.
Innovation Solution
An integrated avionics system incorporating multi-product avionics control and display units (CDUs) that can operate in two modes: one to display independent standby primary flight information and another to control and display various aircraft systems, using configurable software images and independent electronic components to reduce common-mode failures and save resources.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple mechanical or electro-mechanical gauges are used to display flight information, then reliability is improved through redundancy, but weight increases and valuable space is consumed
Solution Approach 1:
The patent combines multiple separate flight instrument gauges (attitude indicator, altimeter, airspeed indicator, heading indicator, turn and bank indicator) into a single integrated electronic display system. This consolidation maintains the redundancy and reliability of having multiple independent failure modes while eliminating the weight penalty of having physically separate mechanical or electro-mechanical gauge assemblies mounted in the instrument panel.
Solution Approach 2:
The integrated electronic display system is designed to provide multiple flight information functions through a single device. The display can show attitude, altitude, airspeed, heading, and turn/bank information simultaneously or selectively, replacing multiple specialized gauges with one multi-functional electronic instrument that adapts its display based on operational needs.
2Reliability
If multiple mechanical or electro-mechanical gauges are used to display flight information, then reliability is improved through redundancy, but the area occupied increases
Solution Approach 1:
The patent consolidates multiple flight instrument functions into a single integrated electronic display unit, dramatically reducing the instrument panel area required. Instead of mounting separate mechanical or electro-mechanical gauges that each require their own physical space, the system uses one electronic display that can present all flight parameters in a compact format, freeing up valuable panel real estate.
Solution Approach 2:
The system transitions from a two-dimensional array of separate gauge faces to a flexible electronic display that can dynamically reconfigure information presentation. The display can show multiple parameters simultaneously using graphical representations, symbols, and multi-level information density, effectively packing more information into less physical space by utilizing the electronic display's ability to vary information density and layout.
3Reliability
If dedicated instruments are used for standby primary flight information, then reliability is improved, but device complexity increases
Solution Approach 1:
The integrated electronic display system is designed to operate in multiple modes including normal operation and standby/reversionary modes. The same display hardware and processing system that provides primary flight information also provides standby capability, eliminating the need for separate dedicated standby instruments. The system can automatically or manually switch between displaying integrated electronic flight instrument information and independent standby flight parameters from separate sensors.
Solution Approach 2:
The system dynamically adapts its functionality based on operational conditions. The display can transition between showing integrated avionics information and displaying independent standby flight parameters, with the capability to reconfigure its display content and data sources in real-time. This dynamic behavior provides standby capability without requiring a permanently configured separate instrument system.
Data Source
AI summary
A multi-product avionics control and display unit (CDU). In implementations, the CDU may include a display and a processor coupled with the display. The processor is configurable to operate in a first mode to cause the display to present standby primary flight information associated with the aircraft and a second mode to control and display operation of one or more aircraft systems associated with the aircraft.