Aircraft Landing Gear Differential Braking Control During De-rotation
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Solution Overview
Problem
Existing aircraft braking systems do not provide differential braking capabilities during the de-rotation phase after landing, which can lead to excessive braking and potential damage to the aircraft.
Innovation Solution
A method and control system that adjusts the braking parameters of the left and right landing gear wheels by reducing the braking force while maintaining the differential braking difference, ensuring that the desired differential braking is applied without exceeding safety thresholds, thereby reducing the risk of damage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If full desired braking parameters are applied during de-rotation phase, then differential braking effectiveness is improved, but risk of aircraft damage increases
Solution Approach 1:
The system changes the braking parameter values by applying a reduction factor to the desired braking parameters during the de-rotation phase. This reduces the absolute braking force applied to the wheels while preserving the differential braking capability, thus preventing damage while maintaining steering effectiveness.
Solution Approach 2:
The system preemptively reduces the braking force before damage can occur by detecting the de-rotation phase and automatically applying reduced braking parameters. This prevents the harmful effect of excessive braking stress on the aircraft structure during the vulnerable de-rotation period.
2Object-affected harmful factors
If braking force is reduced during de-rotation phase, then risk of aircraft damage is limited, but differential braking capability may be compromised
Solution Approach 1:
The system applies a proportional reduction to both left and right braking parameters while maintaining their difference. This ensures that the differential braking capability (L'-R'=L-R) is preserved even though the absolute braking force is reduced, allowing effective steering while preventing damage.
3Device complexity
If automatic braking function is applied without differential capability, then system simplicity is maintained, but turning control during de-rotation is insufficient
Solution Approach 1:
The braking control is segmented into independent left and right channel controls, allowing differential braking to be applied during de-rotation phase. This maintains the simplicity of automatic braking while adding the capability for differential control through separate parameter adjustment for each side.
Data Source
Figure 1a~1c
Figure 2
Figure 3
AI summary
A method of braking left and light landing gear wheels on respective left and right sides of an aircraft. A desired left braking parameter (L) is received for the left wheel and a desired right braking parameter (R) is received for the right wheel. The left wheel is braked with a reduced left braking parameter (L') which is less than the desired left braking parameter (L), and the right wheel is braked with a reduced light braking parameter (R') which is less than the desired right braking parameter (R). A difference between the braking parameters is maintained so that L'-R'=L-R.