Integrated Smart Valve Architecture for Aircraft Fluid Wiring Reduction
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Solution Overview
Problem
Aircraft fluid systems, such as air-conditioning systems, face challenges with complex wiring and limited upgradability due to the need for extensive rewiring and additional electronic boards when new equipment is added, leading to increased mass and potential changes in line impedances and capacitive coupling.
Innovation Solution
Implementing a fluid system with smart valves equipped with integrated actuators and a multiplexed digital bus for communication, allowing direct motor control and reducing the need for complex wiring by connecting new equipment to a digital communications bus and power supply, enabling local sub-systems to relieve the central computer's load.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional electric valves with separate electronic boards are used in the central computer, then each valve can be controlled independently, but the wiring becomes complex and the system mass increases
Solution Approach 1:
The patent combines the electronic control board, electric motor, and valve assembly into an integrated actuator unit. This merging eliminates the need for separate wiring connections between the central computer and each valve, as the integrated unit contains all control electronics locally. The integration directly reduces wiring complexity while maintaining independent control capability through the onboard electronics.
Solution Approach 2:
The integrated actuator serves multiple functions: it houses the electric motor for valve actuation, the electronic control board for signal processing, and the valve mechanism for fluid control. This multi-functional design consolidates what were previously separate components, reducing the overall system complexity and wiring requirements while preserving independent valve control.
2Adaptability or versatility
If new equipment is added to the aircraft fluid system, then system functionality is improved, but extensive rewiring and additional electronic boards are required
Solution Approach 1:
The system is divided into modular integrated actuator units that can be independently added or removed. Each unit is a self-contained module with its own electronics and actuation mechanisms. This segmentation allows new equipment to be added by simply connecting additional modular units to the system without requiring rewiring of existing components or modifications to the central computer.
Solution Approach 2:
The integrated actuators contain all necessary control electronics within each unit, making them self-sufficient. When new equipment is added, each new integrated actuator brings its own control capabilities, eliminating the need to add corresponding electronic boards to the central computer. This self-service approach enables easy system expansion without increasing central computer complexity.
3Ease of operation
If multiple separate electronic boards are integrated into the central computer for each valve, then each valve can be controlled, but the central computer becomes complex and difficult to upgrade
Solution Approach 1:
The control electronics are extracted from the central computer and placed locally within each integrated actuator unit. This extraction eliminates the need for the central computer to contain multiple separate electronic boards for each valve. The central computer's role is reduced to issuing high-level control commands, while the detailed control functionality resides in the distributed integrated units, making the central computer simpler and more upgradeable.
4Loss of information
If extensive wiring is used to connect the central computer to each electric valve, then control signals can be transmitted, but system mass increases
Solution Approach 1:
By merging the electronic control board with the valve assembly in an integrated actuator unit, the patent eliminates the need for extensive wiring between the central computer and each valve. The control electronics are co-located with the actuator, requiring minimal wiring (only power and communication buses). This directly reduces the mass associated with wiring harnesses and connectors throughout the system.
Data Source
AI summary
The invention relates to a fluid system of an aircraft comprising at least one flow conduit for a fluid, at least one electric valve (30, 40, 50) for regulating the flow of fluid in said fluid conduit by movement of a regulating member in said fluid conduit, a central computer (20) configured to be able to issue control instructions to each electric regulating valve (30, 40, 50) depending on the in-flight conditions of said aircraft, and an electric circuit (60) for powering said computer and each electric regulating valve, characterized in that at least one electric regulating valve, referred to as smart valve, is equipped with an integrated actuator connected to the central computer and/or to another smart valve of the fluid system by at least one multiplexed data communications bus (22, 24, 42, 44).