Vibration suppression method for multi-valve parallel braking system for large aircraft

In airplane braking systems, electro-hydraulic pressure servo valves are essential control elements. Large tonnage airplanes often need many sets of servo regulator for brake pressures operating in tandem to meet their takeoff and landing requirements. But since the servo valves were linked in parallel, there was a greater oil return volume, which led to oscillations that were self-excited due to positive feedback from the return pressure. This phenomenon has a substantial influence on the precision and stability of the regulation of the servo regulator for brake pressures, leading to aviation safety incidents. This research provides a new design for the servo regulator for brake pressure structure based on a vibration analysis of the aircraft brake system. Because of the design, there is no longer a feedback stage spool and there is no chance of positive feedback from oil return. Furthermore, the design ensures that the power stage spool is consistently maintained under a controlled strain. A dynamic model of the new servo regulator for brake pressure was constructed and its capacity to suppress vibrations was verified by brake performance testing and MATLAB/Simulink simulation. The study demonstrates that the new servo regulator for brake pressure, when compared to the previous valve, displays a consistent output pressure and exceptional ability to reduce vibrations in both single set and multiple set parallel operation.