Abstract: An electric brake system for an aircraft as described herein is capable of operating in a normal full power mode, a low power mode, and a sleep mode. The full power mode is supported by the active power supply of the aircraft, while the low power and sleep modes are supported by the backup power supply (e.g., a battery) of the aircraft. The low power mode is activated in response to the detection of certain conditions or operating states where full braking performance is not required. For example, the low power mode can be utilized in connection with towing operations and parking brake adjustment operations. The sleep mode is activated in response to the absence of braking commands for an extended period of time. Various parameters and/or settings of the electric brake system are adjusted, controlled, or regulated during the low power and sleep modes to achieve reduced power consumption relative to the full power mode.

Abstract: A system and method for switching power sources for an aircraft electric brake system is disclosed. The method removes battery power from electric brake actuator controls during flight until landing gear extension occurs. The method utilizes a logic circuit to switch between available power sources based on a plurality of control signals. The method minimizes the total power drawn during flight, and saves battery power if the aircraft calls for operating on battery power only.

Abstract: A power management architecture as disclosed herein is suitable for use in connection with an electric brake system of an aircraft. During ground towing operations when the aircraft engines are off, the power management architecture provides operating power to the electric brake system (and other aircraft systems that are required to support towing operations) via the main aircraft battery. This towing power mode prevents the battery from powering other aircraft systems during towing operations, thus reducing the load on the battery.

Abstract: An electric brake system for an aircraft includes a power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The interlock removes operating power from the brake mechanisms whenever the brake system sensor data does not indicate a legitimate brake application condition. The interlock processing occurs in parallel with the brake command processing such that even if an inadvertent brake command is generated, the brake mechanisms will be unable to act upon the inadvertent brake command.

Abstract: A system and method for switching power sources for an aircraft electric brake system is disclosed. The method removes battery power from electric brake actuator controls during flight until landing gear extension occurs. The method utilizes a logic circuit to switch between available power sources based on a plurality of control signals. The method minimizes the total power drawn during flight, and saves battery power if the aircraft calls for operating on battery power only.

Abstract: An electric brake system for an aircraft as described herein is capable of operating in a normal full power mode, a low power mode, and a sleep mode. The full power mode is supported by the active power supply of the aircraft, while the low power and sleep modes are supported by the backup power supply (e.g., a battery) of the aircraft. The low power mode is activated in response to the detection of certain conditions or operating states where full braking performance is not required. For example, the low power mode can be utilized in connection with towing operations and parking brake adjustment operations. The sleep mode is activated in response to the absence of braking commands for an extended period of time. Various parameters and/or settings of the electric brake system are adjusted, controlled, or regulated during the low power and sleep modes to achieve reduced power consumption relative to the full power mode.

Abstract: An electric brake system for an aircraft includes a power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The interlock removes operating power from the brake mechanisms whenever the brake system sensor data does not indicate a legitimate brake application condition. The interlock processing occurs in parallel with the brake command processing such that even if an inadvertent brake command is generated, the brake mechanisms will be unable to act upon the inadvertent brake command.

Abstract: A power management architecture as disclosed herein is suitable for use in connection with an electric brake system of an aircraft. During ground towing operations when the aircraft engines are off, the power management architecture provides operating power to the electric brake system (and other aircraft systems that are required to support towing operations) via the main aircraft battery. This towing power mode prevents the battery from powering other aircraft systems during towing operations, thus reducing the load on the battery.

Abstract: A system and procedures for adjusting a parking brake for an aircraft having an electric brake system are disclosed. Adjustment of a parking brake as described herein can compensate for thermal expansion or contraction of components of a parking brake mechanism, generally seen during and subsequent to an aircraft landing. Procedures for adjusting an aircraft parking brake as disclosed herein include setting the aircraft brakes to an initial state, comparing a measured elapsed time to a threshold time, measuring a brake temperature, adjusting the brakes to achieve a desired clamping force or brake actuator position, and engaging a friction brake in order to conserve power needed by an electric brake actuator.