Distributed Flight Control Using Physical Redundancy for Failure Tolerance
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Solution Overview
Problem
Existing automated flight control systems face challenges in implementing redundancy without increasing complexity or cost, which is critical for ensuring safety against failures.
Innovation Solution
A distributed flight control system is implemented, where each actuator is controlled by a separate processor, and the system utilizes the physical redundancy of the aircraft to provide redundancy in flight control, allowing for continued safe operation even if one processor or actuator fails.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional redundant flight control systems are implemented, then safety and reliability are improved, but device complexity and cost increase
Solution Approach 1:
The flight control system is segmented into multiple independent flight control computers, each capable of independently controlling the aircraft. This segmentation allows redundancy without requiring a centralized complex redundant system, as each computer operates autonomously with its own sensors and actuators, thereby maintaining reliability while reducing overall system complexity.
Solution Approach 2:
Each flight control computer is designed as a universal, multi-functional unit that can perform all flight control functions independently. This universality means that any single computer can take over completely if others fail, providing redundancy without needing specialized backup systems, thus improving reliability without proportionally increasing complexity.
2Reliability
If traditional redundant flight control systems are implemented, then safety and reliability are improved, but cost increases
Solution Approach 1:
By dividing the flight control system into separate, independent computers rather than building complex redundancy into a single system, the patent enables modular manufacturing. Each flight control computer can be produced independently using standardized components and processes, reducing overall manufacturing cost while maintaining safety through redundancy.
Solution Approach 2:
The system uses identical copies of flight control computers rather than complex unique redundant systems. Each computer is a complete functional copy capable of independent operation, providing redundancy through replication rather than through complex design, thereby reducing cost while improving reliability.
3Reliability
If physical redundancy is utilized, then safe operation during failure is improved, but device complexity increases
Solution Approach 1:
The aircraft is divided into multiple independent flight control modules, each with its own processors and actuators. This segmentation allows physical redundancy to be implemented in a modular fashion where failure of one module does not affect others, improving failure tolerance while keeping each module simple and manageable.
Solution Approach 2:
Each flight control computer is designed with local quality - it has its own dedicated sensors, processors, and actuators that are physically separated and independent. This localization of control functions allows redundancy without requiring complex interconnections between systems, as each unit operates autonomously with its own local resources.
Data Source
AI summary
A set of commands for each of a plurality of actuators to alter an aircraft's state responsive to one or more inputs is produced. The set of commands is provided to fewer than all actuators comprising the plurality of actuators.