Aircraft Power Control System for Retrofit Instrumentation
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Solution Overview
Problem
General aviation aircraft face challenges in adding new electrically based instrumentation without affecting safety margins or requiring electrical system upgrades, due to high susceptibility to power loss and the need for burdensome load analysis, especially when replacing mechanical instruments with electronic equivalents.
Innovation Solution
A system and method that automatically decouples electronic aircraft instruments from the existing electrical system, allowing for the addition of new electrically operated equipment without upgrades or load analysis, using a power control system with a primary and secondary battery, an alternator, and a controller to switch between power sources based on voltage levels.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If new electrically based instrumentation is added to general aviation aircraft, then the functionality and modernization of the aircraft is improved, but the susceptibility to power loss increases and requires burdensome load analysis
Solution Approach 1:
The patent divides the electrical system into separate segments: a primary electrical system (battery and alternator) and a secondary electrical system (separate battery). This segmentation allows new electronic instrumentation to be added to the secondary system without increasing the load on the primary system, thereby maintaining reliability while improving adaptability.
Solution Approach 2:
The patent introduces a dual-battery system where the second battery acts as an intermediary between the alternator and the added electronic instrumentation. This intermediary protects the primary electrical system from additional loads, preventing power loss susceptibility while enabling modernization.
2Measurement precision
If mechanical instruments are replaced with electronic equivalents, then the precision and information capability is improved, but the electrical system complexity and load requirements increase
Solution Approach 1:
The patent segments the electrical system into primary and secondary systems, allowing electronic instruments to be installed in the secondary system without complicating the primary system's wiring and power distribution architecture.
Solution Approach 2:
The second battery serves multiple functions: it powers added electronic instrumentation, provides backup power, and isolates the primary electrical system from additional complexity. This multi-functionality reduces overall system complexity despite adding electronic capabilities.
3Device complexity
If the aircraft relies on a single battery and alternator system, then the device simplicity is improved, but the ability to operate during engine or alternator failures is reduced
Solution Approach 1:
The patent changes the configuration parameter of the electrical system from a single battery to a dual-battery system. This parameter change enables the system to maintain simplicity in operation while dramatically improving reliability during engine or alternator failures through automatic or manual battery switching.
Solution Approach 2:
The second battery serves as a pre-prepared backup power source that cushions against the harmful effect of alternator or engine failure. This prior cushioning ensures continued operation of essential systems without requiring complex real-time power management during emergencies.
4Ease of operation
If the battery voltage is used as an indicator of electrical system health, then the monitoring simplicity is improved, but the ability to detect alternator failures is reduced when the alternator is not generating
Solution Approach 1:
The second battery acts as an intermediary that enables independent testing of the alternator. By isolating the second battery from the alternator, the system can monitor alternator health through voltage differential detection without compromising the simplicity of voltage-based monitoring for overall system health.
Solution Approach 2:
The patent implements feedback mechanisms that monitor voltage differentials between the two batteries to detect alternator failures. This feedback system maintains monitoring simplicity while improving failure detection capability by using the second battery as a reference point.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enables the replacement of mechanical instruments with electronic ones without impacting the aircraft's electrical power generation safety margins, eliminates the need for load analysis, and ensures continued operation during engine or alternator failures by autonomously switching to a secondary power source.
Implementation Method 1
The alternator functions by converting mechanical energy created by the engine into electrical energy by spinning the shaft on the alternator, which creates electrical power by inducing voltages and currents into coil windings
Implementation Method 2
A single, sealed lead-acid battery, a regulator, and an automotive style alternator is a commonly employed configuration
Data Source
AI summary
A system and method to automatically disconnect a retrofit electrical unit from an electrical system in the event of an emergency situation and maintain power to the retrofit electrical unit.