An Aircraft Hydraulic Brake System Model Analysis Using LMS Amesim Tool

Developing a new system architecture from scratch and validating its functional behavior is a time-consuming and complex task. Instead, an analogy-based design approach allows for the development of new systems derived from existing designs, reducing both development time and cost. This study presents the design and simulation of an aircraft hydraulic brake system using the LMS Amesim software tool. The simulation results demonstrate that the proposed brake system effectively meets aircraft hydraulic system design requirements, including MIL-H-5440H standards. The hydraulic pump achieved a stable system pressure of 209 bar, with peak pressure reaching 272 bar during high-demand conditions. The brake accumulator successfully charged to 100 bar within 6.5 seconds, storing 310 cc of oil and compressing 355 cc of nitrogen gas. The pressure reducing valve (PRV) effectively regulated system pressure from 210 bar to 100 bar for braking applications. The brake actuators responded within 0.75 seconds, delivering the required force to counteract wheel torque, while the shuttle valve successfully managed the transition between normal and emergency braking conditions. The return line maintained a stable backpressure of approximately 4 bar, preventing fluid surges. Overall, the simulation results validate the feasibility of the proposed hydraulic brake system, demonstrating compliance with military hydraulic standards and confirming its suitability for aircraft applications. Future improvements, such as antiskid integration, optimized flow control, and further system refinement, are discussed to enhance performance.