Aircraft Control Systems: Configurable Remote Units for Fault Isolation
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Solution Overview
Problem
Existing aircraft systems require multiple, specially developed computers with specific interfaces, leading to high development costs, complex maintenance, and increased downtime due to the inability of devices to be shared across different systems, and existing integrated modular avionics systems face complexity and fault isolation challenges.
Innovation Solution
A system utilizing identical remote electronics units with configurable interfaces and separate data buses for different aircraft functions, based on generic hardware and a deterministic field bus, allowing for shared components across systems like flight control, landing gear, and air conditioning.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If specially developed computers with specific interfaces are used for each aircraft system, then system functionality and reliability are ensured, but development costs and device complexity increase significantly
Solution Approach 1:
The patent implements a universal computer architecture where a single computer type can perform multiple aircraft system functions through configurable interfaces. The computer includes programmable processors and configurable communication interfaces that can be adapted to different systems (flight control, landing gear, actuation, air conditioning) via software configuration rather than hardware differentiation, thereby reducing device complexity while maintaining system functionality.
2Adaptability or versatility
If standalone computers are developed for specific aircraft systems, then system-specific requirements are met, but manufacturing costs and maintenance complexity increase
Solution Approach 1:
The invention employs a universal computer design that can be manufactured in larger volumes for multiple aircraft systems. The computer achieves system-specific adaptability through software configuration and configurable communication interfaces rather than through custom hardware development, enabling cost-effective series production while still meeting diverse system requirements.
Solution Approach 2:
The patent utilizes configurable parameters including communication protocols, data formats, and interface configurations that can be adjusted via software to meet different aircraft system requirements. This parameter configurability allows a single hardware platform to serve multiple systems without requiring custom manufacturing for each application.
3Ease of operation
If multiple different devices are used across aircraft systems, then specific functional requirements are satisfied, but maintenance time and downtime increase
Solution Approach 1:
The patent implements a fleet of identical or similar computers that can be interchangeably deployed across different aircraft systems. When a failure occurs, replacement with an identical unit can be performed quickly without complex interface adaptations, significantly reducing maintenance time and aircraft downtime while maintaining functional requirements through software configuration.
4Productivity
If integrated modular avionics with data concentrators are used, then resource efficiency improves, but fault isolation becomes difficult and system complexity increases
Solution Approach 1:
The patent segments the aircraft systems into independent computer units, each responsible for specific functions but using identical hardware architectures. This segmentation allows for easier fault isolation compared to tightly integrated data concentrators, as failures can be contained to individual computer units while maintaining overall system resource efficiency through standardized interfaces and protocols.
Data Source
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AI summary
The invention relates to a system for controlling, regulating and/or monitoring an aircraft, comprising: at least one main processor unit, which is designed to process and output data; at least one first remote electronic unit having an interface which is designed to interact with a first aircraft function; and at least one second remote electronic unit having an interface, which is designed to interact with an interface of a second aircraft function, characterized in that the first remote electronic unit and the second remote electronic unit are identical to each other in terms of their hardware construction.