Aircraft CAN Bus Layout for Dual-Failure Flight Control
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Solution Overview
Problem
Existing flight control systems in aircraft do not adequately balance bandwidth, optimize bus length and weight, and ensure safe flight after failure scenarios, particularly in multiple bus failures.
Innovation Solution
A controller area network (CAN) distribution system with three bus bundles is implemented, each connected to multiple flight control computers, ensuring redundancy and balanced bandwidth, optimizing total bus length and weight, and maintaining control after the failure of any two busses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple bus bundles are implemented for redundancy, then reliability is improved, but device complexity increases
Solution Approach 1:
The communication system is segmented into three separate bus bundles (first, second, and third bus bundles), each independently connecting flight control computers to rotor assemblies. This segmentation allows the system to maintain functionality even if one or two bundles fail, as other bundles remain operational to provide control signals.
Solution Approach 2:
Each bus bundle is configured with specific connectivity patterns tailored to its function. The first bus bundle connects to certain rotor assemblies while the second and third bundles connect to different combinations, creating localized optimization where each bundle serves specific redundancy requirements without requiring complete duplication of the entire system.
2Weight of stationary object
If bus bundles are optimized for minimum length, then weight is reduced, but bandwidth balance deteriorates
Solution Approach 1:
The bus bundles are configured with asymmetric routing patterns optimized for the specific aircraft layout. Rather than using symmetric equal-length paths, the system accepts varying bus lengths in different bundles to achieve better overall bandwidth distribution and control signal delivery to rotor assemblies positioned at different locations in the aircraft.
Solution Approach 2:
The system distributes communication paths across multiple spatial dimensions by creating three separate bus bundles with different routing configurations. This multi-dimensional approach allows optimization of both total wire length and bandwidth balance simultaneously, as each bundle serves different spatial relationships between flight control computers and rotor assemblies.
Data Source
AI summary
A controller area network (CAN) distribution system for an aircraft includes flight control computers (FCCS) for operation of the aircraft; a first bus bundle is in communication with the FCCs, and directs communication from the FCCs to a left front rotor assembly and a right rear rotor assembly; a second bus bundle in communication with the FCCs, the second bus bundle directs communication from the FCCs to a right front rotor assembly and a left rear rotor assembly; and a third bus bundle in communication with the FCCs, the third bus bundle directs communication from the FCCs to a left wing tip rotor assembly and a right wing tip rotor assembly; the first bus bundle, the second bus bundle, and the third bus bundle are to balance bandwidth, optimize total bus length and width, and provide adequate control after a failure of any two busses.