Patent ID: 8935017
Filing Date: 2015-01-13
Classification: B60T,B64C

Abstract:
1. A control system for anti-skid computers of an aircraft, the system comprising: a first integrated modular avionics computer of a first side of the aircraft, comprising a first Avionics Computer Control Device of the first side of the aircraft and a first Avionics Computer Monitoring Device of the first side of the aircraft, and including at least one first dual data acquisition means and at least one first dual processing means, a second integrated modular avionics computer of a second side of the aircraft, comprising a second Avionics Computer Control Device of the second side of the aircraft and a second Avionics Computer Monitoring Device of the second side of the aircraft, and including at least one second dual data acquisition means and at least one second dual processing means, a first Anti-skid computer of the first side of the aircraft, a second Anti-skid computer of the second side of the aircraft, and one or more main landing gear control elements; wherein the first Avionics Computer Control Device of the first side of the aircraft and the first Avionics Computer Monitoring Device of the first side of the aircraft are connected to the first Anti-skid computer of the first side of the aircraft, and the second Avionics Computer Control Device of the second side of the aircraft and the second Avionics Computer Monitoring Device of the second side of the aircraft are connected to the second Anti-skid computer of the second side of the aircraft, and wherein each of the first and second Avionics Computer Control Devices and each of the first and second Avionics Computer Monitoring Devices are further connected to the first and second anti-skid computers of the other of the first side and the second side.