Redundant Nacelle Control for a Shared Power Module
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Solution Overview
Problem
Existing electrical control systems for aircraft nacelles are costly and bulky due to redundancy requirements, despite improving availability, and have inefficiencies in component reliability and space usage.
Innovation Solution
An electrical control system with two control modules connected to a single power module via an approval module, which selectively authorizes control, ensuring high availability and reducing costs and space requirements by using discrete electronic components and passive reconfiguration without dedicated software.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a fully redundant electrical control system with two control modules and two power modules is used, then system availability is improved, but cost and device complexity increase significantly
Solution Approach 1:
The patent merges two power modules into a single shared power module that can be controlled by either control module. This consolidation reduces the total number of components while maintaining the ability to tolerate failures, as the single power module can serve both control modules alternately or simultaneously depending on operational needs
Solution Approach 2:
The single power module is designed with universal functionality to be controlled by either control module 10 or control module 20. The approval module enables this multi-functionality by dynamically authorizing which control module can command the power module, allowing the system to adapt to failure conditions without requiring dedicated power modules for each control module
2Reliability
If two control modules and two power modules are used, then system availability is improved, but the space required in the nacelle increases
Solution Approach 1:
By merging the power modules into a single shared unit, the physical space required in the nacelle is reduced. The approval module enables this space reduction by managing control authorization between two control modules for one power module, eliminating the need for a second dedicated power module and its associated space requirements
3Reliability
If two control modules and two power modules are used, then system availability is improved, but manufacturing cost increases
Solution Approach 1:
The patent merges two power modules into one, directly reducing component count and manufacturing cost. The approval module manages this consolidated architecture by authorizing control from either control module to the single power module, maintaining reliability while reducing the cost of acquiring, installing, and maintaining two separate power modules
Solution Approach 2:
Instead of duplicating the power module (which is expensive), the system copies only the control modules (which are less expensive) and uses the approval module to manage access to the single power module. This selective copying strategy reduces overall system cost while maintaining the redundancy needed for high availability
4Ease of manufacture
If discrete electronic components are used instead of software-based control, then system cost is reduced, but control flexibility may be limited
Solution Approach 1:
The patent replaces software-based control logic with a hardware-based approval module using discrete electronic components. This substitution reduces system cost and complexity while providing deterministic control behavior. The approval module's hardwired logic provides sufficient flexibility for the control authorization function without requiring programmable software
Data Source
AI summary
An electrical control system intended for an aircraft turbojet engine nacelle includes two control modules of a single power module controlling an electric machine and an approval module linking each of the control modules to the single power module. The approval module selectively authorizes the control of the single power module by one of the control modules.