A detachable airplane wheel prerotation/landing brake cooling device is disclosed that comprises: an outer circular cage rim, an inner circular cage rim confronting and spaced apart from the outer circular cage rim, and a plurality of spaced apart arcuate blades spanning across and connecting the outer circular cage rim to the inner circular cage rim at a slant. Each arcuate blade includes a first section connected to the outer circular cage rim and a second section connected to inner circular cage rim. The plurality of slanted arcuate blades are, when the detachable airplane wheel prerotation/landing brake cooling device is being impinged by an airstream during the landing of the airplane, configured to (i) rotate the wheel about the axle in a forward direction, and (ii) funnel air into the plurality of annular spaces adjacent to the plurality of heat shields to thereby remove heat away from the disc brake assembly.

Apparatuses, systems, and methods apply, with a fan, a braking force to a vehicle that includes an axle. The fan is rotated at a first rotational speed based on a rotation of the axle that rotates at a second rotational speed. The first rotational speed is different from the second rotational speed. The fan applies the braking force when the fan rotates at the first rotational speed.

A brake cooling system of the present disclosure includes an external cooling apparatus located externally from an aircraft (e.g., available on the ground at the gate during parking of the aircraft). The external cooling apparatus is in electronic communication with the aircraft via a communication channel such that the external cooling apparatus receives live data from the aircraft for intelligent aircraft brake cooling. The live data includes measured brake temperature. The brake cooling system further includes a controller for collecting aircraft data and generating a cooling apparatus control signal.

A brake assembly for landing gear of an aircraft includes a caliper member and a carrier member. The caliper member includes a gas inlet configured to receive a cooling gas supplied by an on board fuel inerting gas supply system of the aircraft, and a manifold fluidly coupled to the gas inlet. The manifold is configured to distribute the cooling gas to one or more outlet ports of the caliper member. The carrier member is configured to be coupled to the caliper member. The carrier member includes a cylindrical section configured to receive a stacked arrangement of stators and rotors. The cylindrical section defines one or more interior passages configured to fluidly couple the outlet ports of the caliper member to one or more outlet ports of the cylindrical section. The outlet ports of the cylindrical section are arranged proximate the stacked arrangement of stators and rotors to facilitate forced convective cooling of the stacked arrangement of stators and rotors with the cooling gas supplied by the on board fuel inerting gas supply system.

The invention discloses a friction simulating device, comprising: a first driving shaft, a first driving gear, a second driving gear, a second driving shaft, a plurality of friction plates and a driving mechanism. The first driving gear is coaxially fixedly connected to the first driving shaft. The second driving gear is located on a radial outer side of the first driving gear and is provided coaxially with the first driving gear. The second driving shaft is coaxially fixedly connected to the second driving gear. The plurality of friction plates being provided subsequently between the first driving gear and the second driving gear in a direction of an axis of the first driving gear, wherein some of the friction plates are axially movably connected to the first driving gear in a circumferential direction, and the other friction plates are axially movably connected to the second driving gear in the circumferential direction. The friction simulating device is able to simulate the friction applied to the wheels of the vehicle by the ground.

A motor assembly having a brake device and a downsized cooling system is provided. The motor assembly comprises a drive motor, a brake device that stops rotation of a motor shaft, and a casing that holds the drive motor and the brake device. The motor assembly further comprises a hollow passage formed in the motor shaft to allow cooling medium to flow therethrough, a centrifugal passage formed in the brake rotor from the hollow passage to an opening of the brake rotor, and a return passage that returns the cooling medium discharged from the opening to the hollow passage.

A system for cooling the brakes of a brake system of a landing gear of an aircraft, including: a compressor configured to generate a pressurized airflow, the compressor including at least one air outlet, and an air jet pump including: a pump tube including a first end connected to the air outlet and a second end, the pump tube being designed to carry the pressurized airflow between the first and second ends, and a plurality of injectors connected to the second end of the pump tube, and configured to inject the pressurized airflow.

An aircraft brake temperature control system (BTCS) 100 for controlling a temperature of a brake 220 of a landing gear 201 of the aircraft 200. The BTCS 100 includes a controller 110 configured to cause a thermal management system 2000 to regulate the temperature of the brake 220, on the basis of a selection of an objective for regulating the temperature of brake from a plurality of objectives 121, 122 for regulating the temperature of the brake. An aircraft 200 includes the BTCS; and a method 300 controls a temperature of a brake of a landing gear of an aircraft.

An aircraft brake temperature control system (BTCS) 100 for controlling a temperature of a brake 220 of a landing gear 201 of the aircraft 200. The BTCS 100 includes a controller 110 configured to cause at least one fluid moving device 230, 231, 232 to drive a flow of fluid onto the brake 220, selectively in one of a plurality of modes, to control the temperature of the brake 220. The BTCS 100 may be incorporated into an aircraft system 1000 with at least one fluid moving device 230, 231, 232, wherein the aircraft system is on an aircraft 200.

The action of braking generates massive amounts of heat. It is known to install brake ducts 9, which channel air from the front of the vehicle to the brake discs 17. The air introduced by the brake ducts 9 is at an ambient temperature, much cooler than the brakes, and the airflow is closer to laminar (rather than turbulent) and continuously moves the hotter air away. This allows the brakes to shed heat at a faster rate and dramatically lowers the average operating temperature. The present invention provides a vortex tube 3 for supplying a stream of air 5 at a temperature substantially different from ambient temperature into brake ducts 9 to improve efficiency of the brake ducts 9.