Smart Aircraft Valves With Integrated Actuators for Scalable Fluid Control
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Solution Overview
Problem
Aircraft fluid systems, such as air conditioning systems, face scalability issues due to complex wiring and the need for frequent modifications, which increase system mass and require upgrades to the central computer when adding or moving equipment.
Innovation Solution
Implementing a fluid system with 'smart valves' equipped with integrated actuators and multiplexed digital communication buses, allowing decentralized control and power supply, reducing the need for extensive rewiring and central computer upgrades, and enabling local regulation subsystems to lighten the load on the central computer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional electric valves with separate electronic control cards are used in the central computer, then each valve can be controlled independently, but the system becomes complex and difficult to scale when adding or moving equipment
Solution Approach 1:
The patent merges the electronic control card into the actuator assembly, creating an integrated unit that combines the motor, control electronics, and valve body. This integration eliminates the need for separate electronic cards in the central computer and reduces wiring complexity, allowing easier scaling of the system without requiring complex rewiring or modifications to the central computer architecture
Solution Approach 2:
The integrated actuator assembly serves multiple functions: it acts as the valve body, houses the electric motor, contains the electronic control card, and provides the interface for fluid control. This multi-functional design allows the same component to perform various roles, reducing the overall number of components needed and simplifying system expansion
2Reliability
If multiple electronic control cards are installed in the central computer to control numerous electric valves, then each valve receives proper control signals, but the central computer becomes overloaded and the system mass increases
Solution Approach 1:
The patent segments the control functionality by moving the electronic control card from the central computer to the distributed actuator assemblies. Each actuator becomes an independent control unit with its own electronics, eliminating the need for multiple control cards in the central computer. This segmentation reduces the central computer's mass and workload while maintaining reliable control through distributed intelligence
3Adaptability or versatility
If equipment is added or moved in the fluid system, then system functionality is enhanced, but extensive rewiring and central computer modifications are required
Solution Approach 1:
The integrated actuator assembly is designed as a self-contained unit that includes all necessary control electronics and power supply components. When adding or moving equipment, these self-sufficient modules can be installed or relocated without requiring modifications to the central computer or extensive rewiring, as each unit independently manages its own control signals and power requirements
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
The system becomes easily scalable, reduces overall mass, and decreases the central computer's workload by transferring regulation tasks to local subsystems, minimizing wiring and power supply requirements.
Implementation Method 1
an electric motor controlled by said electronic control card and configured to be able to move said regulatory member in said fluid pipe
Data Source
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AI summary
The invention relates to an aircraft fluid system comprising at least one fluid circulation line, at least one electric valve (30, 40, 50) for regulating the fluid flow in said fluid line by moving a regulating element in said fluid line, a central computer (20) configured to be able to deliver control instructions to each electric regulating valve (30, 40, 50) according to the flight conditions of said aircraft, and an electrical circuit (60) for supplying said computer and each electric regulating valve, characterized in that at least one electric regulating valve, called a 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 communication bus (22, 24, 42, 44).