Abstract: A brake stack is disclosed. The brake stack comprises a first stator, a second stator, and a first rotor disposed between the first stator and the second stator. The brake stack further comprises a first spring disposed between the first stator and the second stator. The first spring is disposed radially inward of the first rotor. The first spring is disposed axially between the first stator and the second stator. The first spring is configured to partially compress when a force applied to a pressure plate of the brake stack is less than a threshold force.

Abstract: An aircraft landing gear arrangement may comprise a landing gear bogie having an axle, a torque tube surrounding the axle and mechanically coupled to the landing gear bogie. A brake stack may surround the torque tube. The torque tube may comprise a cylindrical body extending between a first end and a second end. A flange may be disposed at the first end. A mating surface may be disposed on the first end or the second end of the torque tube for mating the torque tube to the landing gear bogie. A bogie flange may extend from the landing gear bogie whereby the torque tube may be mounted to the landing gear bogie.

Abstract: A brake stack is disclosed. The brake stack comprises a first stator, a second stator, and a first rotor disposed between the first stator and the second stator. The brake stack further comprises a first spring disposed between the first stator and the second stator. The first spring is disposed radially inward of the first rotor. The first spring is disposed axially between the first stator and the second stator. The first spring is configured to partially compress when a force applied to a pressure plate of the brake stack is less than a threshold force.

Abstract: An aircraft landing gear arrangement may comprise a landing gear bogie having an axle, a torque tube surrounding the axle and mechanically coupled to the landing gear bogie. A brake stack may surround the torque tube. The torque tube may comprise a cylindrical body extending between a first end and a second end. A flange may be disposed at the first end. A mating surface may be disposed on the first end or the second end of the torque tube for mating the torque tube to the landing gear bogie. A bogie flange may extend from the landing gear bogie whereby the torque tube may be mounted to the landing gear bogie.

Abstract: An aircraft landing gear arrangement may comprise a landing gear bogie having an axle, a torque tube surrounding the axle and mechanically coupled to the landing gear bogie. A brake stack may surround the torque tube. The torque tube may comprise a cylindrical body extending between a first end and a second end. A flange may be disposed at the first end. A mating surface may be disposed on the first end or the second end of the torque tube for mating the torque tube to the landing gear bogie. A bogie flange may extend from the landing gear bogie whereby the torque tube may be mounted to the landing gear bogie.

Abstract: Systems and methods for aircraft electric taxi brake optimization are provided. The system may comprise an aircraft having a landing gear comprising a wheel, a friction brake having a brake material coupled to the wheel, a regenerative brake comprising a reversible taxi motor coupled to the wheel, a sensor configured to measure a wheel parameter of the wheel and a temperature of the friction brake, a tangible, non-transitory memory configured to communicate with a controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising: receiving, by the controller, a command signal and the friction brake temperature and calculating, by the controller, a brake material temperature based on the wheel parameter, the friction brake temperature, and the command signal.

Abstract: Systems and methods for aircraft electric taxi brake optimization are provided. The system may comprise an aircraft having a landing gear comprising a wheel, a friction brake having a brake material coupled to the wheel, a regenerative brake comprising a reversible taxi motor coupled to the wheel, a sensor configured to measure a wheel parameter of the wheel and a temperature of the friction brake, a tangible, non-transitory memory configured to communicate with a controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising: receiving, by the controller, a command signal and the friction brake temperature and calculating, by the controller, a brake material temperature based on the wheel parameter, the friction brake temperature, and the command signal.

Abstract: An aircraft landing gear arrangement may comprise a landing gear bogie having an axle, a torque tube surrounding the axle and mechanically coupled to the landing gear bogie. A brake stack may surround the torque tube. The torque tube may comprise a cylindrical body extending between a first end and a second end. A flange may be disposed at the first end. A mating surface may be disposed on the first end or the second end of the torque tube for mating the torque tube to the landing gear bogie. A bogie flange may extend from the landing gear bogie whereby the torque tube may be mounted to the landing gear bogie.

Abstract: The present disclosure relates to brake control and monitoring, and more particularly, to a brake control and monitoring system that monitors brake actuation force.

Abstract: The present disclosure relates to brake control and monitoring, and more particularly, to a brake control and monitoring system that monitors brake actuation force.

Abstract: A wheel assembly (10) is disclosed, including a wheel base (14) and a wheel rim member (16). The wheel base (14) has along at least a portion of its length a non-circular cross sectional outer surface (86). The wheel rim member (16) has along at least a portion of its length a mating non-circular cross sectional inner surface (88). The inner surface (88) of the wheel rim member (16) interacts with the outer surface (86) of the wheel base (14) to restrict relative rotation of the wheel rim member (16) on the wheel base (14).

Abstract: A wheel assembly (10) is disclosed, including a wheel base (14) and a wheel rim member (16). The wheel base (14) has along at least a portion of its length a non-circular cross sectional outer surface (86). The wheel rim member (16) has along at least a portion of its length a mating non-circular cross sectional inner surface (88). The inner surface (88) of the wheel rim member (16) interacts with the outer surface (86) of the wheel base (14) to restrict relative rotation of the wheel rim member (16) on the wheel base (14).

Abstract: An aircraft wheel for a pneumatic tire that has a generally cylindrical wheel section with an annular inboard rim flange and an annular outboard rim flange which seat the respective beads of the tire, The respective rim flanges have curvilinear configurations that extend radially outwardly from each other with the curvilinear portion of the inboard rim flange having a radius of curvature that is based on a single radius of curvature while the curvilinear portion of the outboard rim flange has a compound radius defining an outboard rim flange that has a greater radial dimension than the inboard rim flange.