The global environment has been severely influenced by the green-house effects, and it will cause greater impact on the environment for the pollutant gas emitted by the aircraft during the high-altitude flight, compared with those emitted on the ground. Additionally, the density of the commercial airlines is still increasing, thus more electric aircraft (MEA) or even all electric aircraft (AEA) becomes a trend for the commercial aircraft in order to achieve carbon-free travel. Compared to the traditional aircraft, the brake system for both the MEA and AEA adopts the electric actuator to replace the hydraulic actuator, and it is one of the critical factors of safe and stable landing of MAE/AEA for the performance and quality of the electrical actuated brake system. Through summarizing the technical progress of MEA/AEA and electrical actuated brake system worldwide, the structure schematic and the modeling methods of the subsystems and their interactions are introduced. Since the electrical actuated brake system can be regarded as a multi-body system which is consisted with multiple rigid systems, it has discontinuous interaction forces due to the clearance and friction between the subsystems. Then, it has impact when the aircraft landing on the ground, and the friction coefficient between the wheel of the aircraft and the ground is time-varying due to the slip effects. Therefore, it will introduce discontinuity into the dynamical system of the brake system. It becomes important to study the mechanism of the complex dynamic behaviors due to the discontinuous interaction forces between the subsystems and the discontinuous external excitations of the electrical actuated brake system of the civil MAE aircraft in the future.