Flight Control Computer Self-Test Mode for Fault Detection
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Solution Overview
Problem
Current flight control system testing methods are time-consuming, costly, and unreliable, with 80% of faults detected during assembly related to simulation tools rather than the system itself, making it difficult to locate faults, especially after the construction phase when simulation tools are no longer available.
Innovation Solution
A flight control system with a second processing mode and interface means for external command reception and information transmission, along with a test device that connects to flight control computers in two operational phases: data reception and test phases, allowing real-time access and takeover of flight control systems, enabling non-intrusive observation and fault detection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If complex simulation tools and exhaustive procedures are used to test flight control systems, then testing completeness is improved, but testing time and cost increase significantly
Solution Approach 1:
The patent extracts the essential testing functionality from complex simulation tools by implementing a self-test mode within the flight control computer itself. This allows the system to test its own wiring and components without requiring external simulation equipment, thereby reducing testing time while maintaining completeness.
Solution Approach 2:
The flight control computer is equipped with a self-test capability that allows it to autonomously diagnose faults in its wiring and components. The system can independently activate test modes, execute diagnostic routines, and identify faults without external intervention, significantly reducing both testing time and resource requirements.
2Reliability
If redundant flight control computers automatically reconfigure upon fault detection, then system reliability is improved, but fault detectability worsens
Solution Approach 1:
The patent implements a self-test mode that is activated before normal operation begins. This preliminary testing allows the system to detect faults in wiring and components before they affect operational reliability, capturing faults that would otherwise be masked by automatic reconfiguration during normal operation.
Solution Approach 2:
Instead of testing the system during normal operational mode where faults are masked by redundancy, the patent inverts the approach by implementing a dedicated test mode that deliberately suspends normal operational logic. This allows direct observation of system components and wiring without the interference of automatic fault masking mechanisms.
3Difficulty of detecting and measuring
If traditional measurement methods are used for fault location after construction, then fault detection capability is maintained, but maintenance complexity and resource requirements increase
Solution Approach 1:
The flight control computer performs self-diagnosis using integrated test routines that automatically locate faults in wiring and components. The system generates detailed fault location information without requiring external measurement equipment or complex manual testing procedures, thereby simplifying maintenance while maintaining detection capability.
Solution Approach 2:
The patent replaces traditional mechanical measurement methods (continuity testing, insulation testing with external equipment) with electronic self-diagnosis routines implemented within the flight control computer. This substitution eliminates the need for complex external testing equipment and manual procedures, reducing maintenance complexity while maintaining fault detection capability.
Data Source
AI summary
A test system for testing a flight control system of an aircraft includes a test device that: (1) accesses information available from the flight control system and (2) controls a computer of the flight control system.