Aircraft Braking Power Supply Unit Merging High and Low Voltage
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Solution Overview
Problem
Aircraft braking systems have complex connections with the electrical systems, leading to potential reliability issues and increased complexity.
Innovation Solution
A simplified braking system architecture that generates both high and low voltage within the power supply unit, allowing direct powering of the braking system components and incorporating controlled switches to prevent untimely braking, reducing connections to the aircraft's power sources and enhancing safety.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the braking system uses separate high voltage and low voltage power sources from the aircraft electrical system, then the power supply reliability is improved, but the system complexity and number of connections increases
Solution Approach 1:
The patent merges the high voltage and low voltage power supply functions into a single integrated power supply unit. This unit includes a high voltage converter, a low voltage converter, and a battery all in one module, reducing the number of separate connections to the aircraft electrical system while maintaining reliable power supply for both high power actuators and low power control electronics
Solution Approach 2:
The integrated power supply unit serves multiple functions: it provides high voltage power to the power module, low voltage power to the control module and electronic cards, and includes a battery for emergency or ground operation. This multi-functional design reduces system complexity by eliminating the need for separate power supply connections
2Adaptability or versatility
If the braking system includes multiple voltage converters and separate power connections, then the power distribution flexibility is improved, but the ease of installation and maintenance deteriorates
Solution Approach 1:
By combining multiple voltage converters and power management functions into a single integrated power supply unit, the patent simplifies installation and maintenance procedures. The unit connects to the aircraft electrical system through a single interface while internally providing both high voltage and low voltage outputs, reducing the complexity of wiring and connection points
3Speed
If the braking system operates without controlled switches, then the response time is improved, but the safety and prevention of accidental braking deteriorates
Solution Approach 1:
The patent implements controlled switches that are activated only when appropriate braking conditions are detected. The control module monitors system state and only enables power delivery to actuators when a valid braking command is received, preventing accidental braking while maintaining rapid response when needed
Solution Approach 2:
The control module continuously monitors the braking system state and uses feedback control to manage the controlled switches. It receives braking commands, determines appropriate response, and controls power delivery accordingly, ensuring safety while maintaining fast response time when braking is required
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
This solution improves availability, reliability, and simplifies the system by reducing voltage converters and supply inputs, optimizing battery consumption, and enhancing transparency while preventing accidental braking.
Implementation Method 1
at least one power supply unit, comprising means for generating a high voltage from an electrical power bus of the aircraft and/or from an aircraft battery, to supply the power module with the high power required to supply the actuators
Implementation Method 2
the power supply unit further comprises means for generating a low voltage to supply low voltage at least to the control module
Implementation Method 3
electromechanical actuator brakes for selectively applying braking force to respective disc stacks to exert braking torque on respective wheels
Data Source
Figure 1
Figure 2
AI summary
The invention relates to an aircraft braking system architecture comprising: - brakes with electromechanical actuators (3) for selectively applying a braking force on respective stacks of discs (2) to exert a braking torque on respective wheels; - at least one power module (7) adapted to send phase currents to the electromechanical actuators so that they exert a braking force; - at least one control module (8) for controlling the power module in response to a braking command so that appropriate phase currents are sent to the actuators so that they develop the desired braking force;- at least one power supply unit (20) comprising means for generating (21) a high voltage (HVDC) to supply the power module with the high power required to supply the actuators, and means for generating (22) a low voltage (LVDC) to supply at least the control module with low voltage.