Aircraft Brake Temperature Control With Variable Cooling Modes
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Solution Overview
Problem
Aircraft braking systems face increased brake temperatures during operation, leading to longer braking distances, increased wear, and extended turnaround times between flights, which existing temperature control systems do not adequately address.
Innovation Solution
An aircraft brake temperature control system that uses a controller to manage fluid flow from devices like brake cooling fans to regulate brake temperature based on flight conditions, operational considerations, and noise, vibration, and harshness factors, allowing for variable flow rates and modes to maintain optimal temperature within specific ranges.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If high flow rate cooling is applied continuously, then brake temperature is reduced effectively, but noise and vibration increase
Solution Approach 1:
The system applies cooling in periodic cycles rather than continuously. The controller alternates between high flow rate cooling periods and low flow rate or idle periods, achieving effective temperature reduction while minimizing noise and vibration during low-flow periods.
Solution Approach 2:
The system dynamically adjusts the flow rate of cooling fluid based on real-time brake temperature conditions. The controller modulates the flow rate between high and low levels, optimizing cooling effectiveness while reducing noise and vibration when high cooling is not required.
2Temperature
If high flow rate cooling is used, then brake temperature reduces faster, but energy consumption increases
Solution Approach 1:
The system dynamically adjusts cooling intensity based on actual temperature needs. High flow rate is applied only when rapid cooling is necessary, while low flow rate or idle mode is used during sufficient cooling periods, optimizing energy consumption.
Solution Approach 2:
The controller implements periodic cooling cycles with alternating high and low flow rates, reducing overall energy consumption compared to continuous high flow rate operation while maintaining effective temperature control.
3Temperature
If cooling is applied during flight, then brake temperature is controlled, but system complexity increases
Solution Approach 1:
The system uses temperature sensors to provide feedback to the controller, which automatically adjusts cooling intensity based on measured brake temperature. This closed-loop control simplifies the overall system by using sensor feedback rather than complex predictive control algorithms.
Solution Approach 2:
The cooling system self-regulates based on temperature feedback, with the controller automatically determining when high or low flow rate is needed without requiring complex external control inputs or manual intervention.
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 system effectively reduces brake temperatures, improving brake performance and lifespan, reducing turnaround times, and minimizing the cumulative temperature effects across successive flights, while also reducing noise and vibration during operation.
Implementation Method 1
a fluid moving device to drive a flow of fluid onto the brake
Implementation Method 2
drive a flow of fluid onto the brake to control the temperature of the brake
Data Source
Figure 1
Figure 2a~2b
Figure 3~5
AI summary
Disclosed is an aircraft brake temperature control system (BTCS) 100 for controlling a temperature of a brake 220 of a landing gear 201 of the aircraft 200. The BTCS 100 comprises a controller 110 that is configured to cause at least one fluid moving device 230, 231, 232 to drive a flow of fluid onto the brake 220, selectively in one of a plurality of modes, to control the temperature of the brake 220. Also disclosed is: an aircraft system 1000 comprising the BTCS 100 and the at least one fluid moving device 230, 231, 232; an aircraft 200 comprising the BTCS 100 or the aircraft system 1000; and a method 300 of controlling a temperature of a brake of a landing gear of an aircraft.