Distributed Engine Control Modules via Serial Bus
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Solution Overview
Problem
The existing centralized electronic engine control systems for aircraft gas turbine engines are large, heavy, and application-specific, leading to reliability concerns and high redesign costs, particularly due to the need for long wiring harnesses and harsh environment compatibility.
Innovation Solution
A distributed electronic engine control system comprising an airframe module, an electronic engine control module, and an engine I/O module, interconnected via a serial communications bus, with inner loop control logic in the engine I/O module and outer loop control logic in the electronic engine control module, allowing for remote module placement and reduced wiring, weight, and increased reliability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a centralized electronic engine control system is used, then all connections for engine and airframe are integrated in one location, but the system becomes large, heavy, and requires long wiring harnesses
Solution Approach 1:
The centralized control system is divided into multiple distributed control modules, each handling specific control functions locally. This segmentation eliminates the need for long wiring harnesses connecting a single centralized controller to all engine components, as each module operates independently with local connections only.
Solution Approach 2:
The control architecture transitions from a single-point centralized control to a distributed spatial arrangement of control modules throughout the engine system. This dimensional redistribution of control functions reduces wiring length by placing controllers closer to the components they control.
2Device complexity
If a centralized electronic engine control system is used, then all control functions are in one location, but redesign costs become very high due to application-specific design
Solution Approach 1:
The control system is segmented into standardized modular units that can be independently designed and manufactured. Each module handles specific control functions but uses common standardized interfaces and communication protocols, allowing individual modules to be redesigned without affecting the entire system, thus reducing redesign costs.
Solution Approach 2:
The distributed control modules are designed with universal interfaces and standardized communication protocols, enabling them to perform multiple functions across different applications. This universality allows the same module design to be reused in various engine configurations, significantly reducing redesign costs compared to application-specific centralized designs.
3Weight of moving object
If control modules are placed remotely from one another, then wiring length is reduced, but system complexity increases due to distributed architecture
Solution Approach 1:
A standardized communication bus serves as an intermediary between the distributed control modules, simplifying the architecture by providing a common communication infrastructure. This mediator handles data exchange between modules, reducing the complexity of direct point-to-point connections while maintaining the weight benefits of distributed placement.
Solution Approach 2:
All control modules use identical standardized interfaces, communication protocols, and data formats, creating homogeneity across the distributed system. This uniformity reduces architectural complexity by eliminating the need for custom integration logic between different modules, making the distributed system as manageable as a centralized one.
Data Source
Figure 1~4
Figure 3
AI summary
A distributed electronic engine control system (19) includes an airframe module (26), an electronic engine control module (28), and an engine I/O module (30a,30b). The modules are arranged in locations remote from one another. A serial communications bus (40,42) interconnects the modules with one another. A first engine controls device (34b,34c) is connected to the engine I/O module and is configured to interact with an engine component and provide a first data. The engine I/O module includes inner loop control logic that uses the first data and produces a second data in response thereto. The electronic engine control module includes an outer loop control logic using the second data and produces a third data in response thereto. The airframe module receives power and distributes the power to the electronic engine control and engine I/O modules. The first, second and third data are provided on the serial communications bus.