404results about "Aircraft brake actuating mechanisms" patented technology

A system, apparatus and method provide a means for testing operation of vehicle brake system. More particularly, a brake actuator is automatically commanded to engage a brake disk stack while the vehicle is in a benign state. An engagement force applied to the brake-disk stack by the actuator then is determined, and the engagement force is compared to a first threshold value. If the engagement force is within a predetermined range of the first threshold value, it is concluded that the brake system is operating normally, otherwise it is concluded that the brake system is operating abnormally.

A brake system control unit controls one of first and second portions of a wheel brakes electric brake actuators to activate one of the first and second portions of the actuators and deactivate the other during an inhibited braking mode. The control unit controls the activated portion of the brake actuators to generate a braking force greater than the commanded braking force of the brake pedal command, such as twice the commanded braking force, to compensate for the deactivated portion of the brake actuators. The inhibited braking mode is discontinued during emergency braking when the commanded braking force is greater than or equal to a predetermined braking force. The inhibited braking mode is also discontinued when failure of one or more brake actuators is detected.

An aircraft braking system includes a brake disk stack (22) that has at least one brake rotor (26) rotatable with an aircraft wheel (16) and at least one brake stator (24), at least one actuator (36) movable in response to a braking command to compress the brake disk stack (22) and slow the wheel (16), at least one actuator motor (32) operably connected to the at least one actuator (36) for moving the at least one actuator (36), a generator (40, 82, 100) having a generator rotor (42) and a generator stator (44), the generator (40, 82, 100) being operably connectable to the aircraft wheel (16) such that said generator rotor (42) rotates when the wheel (16) rotates, and a controller (50) electrically connected to the generator (40, 82, 100) and the at least one actuator motor (32). Also a method of generating electrical power from an aircraft wheel (16).

The disclosed embodiments relate to methods and systems for avoiding a collision between an obstacle and a vehicle, such as an aircraft, on a ground surface. A processor receives a detection signal from one of a plurality of proximity sensors. The detection signal indicates that the obstacle has been detected. In response to receiving the detection signal, a video image signal is transmitted from the processor to a display in the cockpit of the aircraft. The video image signal corresponds to a particular video imager that is associated with the particular proximity sensor that detected the obstacle. A video image, of a particular region around the aircraft that includes the obstacle is displayed on a display. In response to receiving the detection signal, the processor can also transmit an alert signal, and a brake activation signal to activate a braking system to prevent the aircraft from colliding with the obstacle.

The invention relates to a system architecture for managing aircraft landing gear and suitable for extending/retracting retractable undercarriages, steering steerable wheels, and braking braked wheels. According to the invention, the architecture comprises a communications network having connected thereto extension/retraction actuators, steering actuators, and braking actuators, together with one or more control units adapted to control all of the actuators connected thereto, the communications network having transmission characteristics that are adapted to enabling the control unit(s) to implement antilock servo-control for controlling the braking actuators.

A redundant architecture for a brake-by-wire system is provided. The system includes a pressure source; at least one brake actuator for exerting a braking force on a wheel as a result of pressure provided by the pressure source; at least one servo valve for controlling an amount of pressure provided from the pressure source to the at least one brake actuator in response to a servo valve command signal; a shutoff valve in line with the at least one servo valve for preventing pressure from the pressure source from being provided to the at least one brake actuator in response to a shutoff valve command signal; a processor which executes code in order to carry out brake control operations, the processor outputting the servo command signal and the shutoff valve command signal in response to system inputs provided to the processor; a shutoff valve enable device for performing brake control operations redundant at least in part with the processor and based on the system inputs, and selectively enabling shutoff valve command signals from the processor to be provided to the shutoff valve based on the redundant brake control operations.

The invention relates to apparatus for braking a set of aircraft wheels, the apparatus comprising a normal hydraulic circuit and an emergency hydraulic circuit, both circuits leading to each of the various brakes via associated brake valves. According to the invention, the brake valves of the normal circuit and/or of the emergency circuit are constituted by direct drive valves that are electrically controlled by an associated electronic control unit.

A brake control system of a multi-wheel-train brake machine wheel is divided into an electrical part and a hydraulic part, wherein the electrical part of the airplane brake control system comprises a dual-redundancy brake instruction sensor, a pressure sensor, a normal brake control unit, a standby brake control unit, a first dual-redundancy hydraulic cut-off valve, an electromagnet of a second dual-redundancy hydraulic cut-off valve, a moment motor of a dual-redundancy pressure servo valve, and a main channel and a standby channel of the electrical part are formed; the hydraulic part of the airplane brake control system comprises a main valve body of the dual-redundancy hydraulic cut-off valve, a jet valve body of the dual-redundancy pressure servo valve and a brake machine wheel body, and the hydraulic part is divided into an inner side channel and an outer side channel. The electrical part can ensure that a brake system can work normally in the presence of any single-point electrical faults. The hydraulic part can ensure that when any single hydraulic source is lost or loses effect, and the brake system just loses one second of brake capacity at most and still can meet the requirement for braking of an airplane.

The monitor for uncommanded braking controls uncommanded brake application on one or more wheels during takeoff of an aircraft. Brake pedal application is determined, brake pressure is measured, and brake pressure is compared with a selected threshold brake pressure. A brake pressure applied signal is generated when the brake pressure exceeds the threshold brake pressure. The pedal application signal and brake pressure applied signal are received by a fault latch logic circuit that generates a fault latch output signal when uncommanded braking has occurred. A test inhibit signal is also generated when weight is not applied on the wheel. The test inhibit signal is also input to the fault latch logic circuit so that uncommanded braking can occur when the aircraft is in the air and weight is off the wheel. The monitor disables or latches off the shutoff valve when pressure is detected without pedal application. A fail-safe feature re-enables the shutoff valve to allow it to turn on, and monitoring is stopped, when pedal application is detected.

The invention relates to a protection method for protecting from overheating in a vehicle brake system comprising at least one brake provided with at least one electromechanical actuator which comprises a pusher actuated by an electric motor to apply a force selectively onto friction elements of the brake, it being possible for the brake system to operate, at the request of the pilot of the vehicle, either in a controlled mode in which the pusher of the actuator is actuated by the electric motor so as to apply a braking force selectively to the friction elements in response to a braking instruction, or in a parking mode in which the pusher of the actuator is locked in a position in which it exerts a parking force on the friction elements. According to the invention, the method includes the step of acting, while the vehicle is at a standstill, while the brake system is in the controlled mode, and while the pusher is controlled to apply a force on the friction element, to switch automatically and without intervention from the pilot from the controlled mode to the parking mode.

The invention relates to a method of managing a parking force in a brake system for a vehicle equipped with at least one electric brake having at least one electromechanical actuator which comprises a pusher actuated by an electric motor to apply a force selectively onto friction elements of the brake, the method including the step of causing the pusher to exert a parking force that is initially equal to a nominal parking force on the friction elements so that the parking force is maintained in the absence of drive from the electric motor. According to the invention, the method includes the step of adjusting said parking force at least once.

The invention relates to an airplane braking system for preventing an emergency brake from being improperly used. The airplane braking system comprises a normal braking system and an emergency braking system, wherein the normal braking system comprises a braking command sensor, an electromagnetic hydraulic lock, an electromagnetic servo valve, a control box and an airplane wheel speed sensor; the emergency braking system comprises an emergency braking valve, a converting valve and a switch; and the normal braking system and the emergency braking system are contacted and converted through the converting valve. According to the airplane braking system disclosed by the invention, during emergency braking, if normal braking is also used, the normal braking system is forced to release pressure, so that pressure does not exist in a normal input opening of the converting valve, the situation that the converting valve is completely converted to the emergency braking system is guaranteed, the application of the emergency braking is guaranteed, and emergency braking failure and accident hidden danger caused by that the emergency braking and the normal braking are used at the same time are eliminated fundamentally; and according to the airplane braking system disclosed by the invention, only one electrical switch element is additionally arranged on a conventional braking system, so that conventional equipment is convenient to refit.

A braking system with a selectable airplane brake mode comprises a hydraulic brake valve, a hydraulic control valve, an electro-hydraulic servo valve, a control box and an airplane wheel speed sensor, wherein the control box, the electro-hydraulic servo valve and the airplane wheel speed sensor form a brake anti-slip control part. A small brake apparatus is selected to run through the hydraulic control valve so as to achieve partial braking of airplane wheels or a small brake apparatus and a big brake apparatus are selected to run simultaneously so as to achieve all braking of airplane wheels. A hydraulic pipeline for the braking system output to an airplane wheel brake apparatus is divided into a small brake apparatus hydraulic pipeline and a big brake apparatus hydraulic pipeline, wherein the small brake apparatus hydraulic pipeline keeps unblocked, and on-off of the big brake apparatus hydraulic pipeline is controlled by a control device so as to achieve selection of the airplane brake mode; the problems that an existing single-wheel single-side-brake carbon brake disc has serious abrasion and the service life is short are solved; the service life of the carbon brake disc is prolonged, and the economic benefit of the carbon brake disc is improved.

The invention relates to a single-wheel dual-brake electronic transmission brake system of an aircraft, capable of choosing a braking manner. A brake antiskid control system is formed by an aircraft wheel speed sensor, a control box and an electro-hydraulic servo valve; a brake control system is formed by a braking instruction sensor, the control box and the electro-hydraulic servo valve. The electro-hydraulic servo valve responds to an electric current control signal of the control box to output and adjust the braking pressure outputted to a braking aircraft wheel; braking selection is realized through a hydraulic control valve; a hydraulic braking valve is replaced with the braking instruction sensor; and the electro-hydraulic servo valve is a positive gain valve. The single-wheel dual-brake electronic transmission brake system disclosed by the invention is suitable for a single-wheel dual-brake aircraft wheel using a carbon brake; the requirements for selective brake use of the single-wheel dual-brake aircraft wheel can be met, and the using conditions of a carbon disk is adjusted, so that the good characteristics of wear resistance of a carbon-carbon composite friction material can be fully exerted, the difficult problems that a conventional single-wheel single-brake carbon brake disk is high in wear and short in service life are effectively solved, the service life of the carbon disk is prolonged, and the economic benefits of the carbon disk are improved.

An airplane wheel fly-by-wire operation brake system capable of selecting brake modes comprises a brake instruction sensor, a control box, an electro-hydraulic servo valve, an electromagnetic valve, an airplane wheel speed sensor and a pressure sensor. The airplane wheel speed sensor, the control box and the electro-hydraulic servo valve form a brake anti-slip control part. The control box and the electromagnetic valve conducts oil path opening and closing through a brake pressure control method to control an airplane to be partly braked through a small brake device or achieve complete brake through a large brake device. The brake pressure value is set to be 40-65% of normal brake pressure. The system is suitable for a single-wheel double-brake airplane wheel with a carbon brake, can meet the requirement that the single-wheel double-brake airplane wheel selects and uses the brake so that the use state of a carbon disc can be adjusted, the good characteristic of abrasion resistance of a carbon-carbon composite friction material is given full play to, the problems that an existing single-wheel single-brake carbon brake disc is large in abrasion and short in service life are effectively solved, the service life of the carbon disc is prolonged, and economic benefits of the carbon disc are improved.

A brake control valve of an airplane is characterized in that two ends of a jet nozzle of a torque motor are communicated with those of a slide valve control cavity through an outlet of an orifice; the brake port of the brake control valve of the airplane is communicated with that of the slide valve through an oil line; a brake port oil filter is serially connected between the brake port of the slide valve and that of the brake control valve of the airplane; the oil inlet of a brake port pressure sensor is connected to the oil line between the brake port of the slide valve and the oil inlet of the brake port oil filter; the oil inlet is communicated with that of a change-over valve through the oil line; a solenoid valve is serially connected to the oil line between the oil inlet and that of the change-over valve; an inlet filter is serially connected between the solenoid valve and the oil inlet; the oil inlet of a flow controller is communicated with the oil outlet of the change-over valve through the oil line; and the oil inlet of the pressure sensor is communicated with the oil line at the outlet of the flow controller through a pipeline. The brake control valve has good working stability and reliability, and provides inlet pressure and outlet pressure signals.

A system and method display a hazard free area around an aircraft that is modified to alert a pilot if a threshold distance between a detected object and the aircraft is reached. The modification may include, for example, altering the size of the hazard free area and its color. Additional information that may be displayed includes distance to the object, width of the hazard free area, stopping distance of the aircraft, and a route to avoid the object.

An electrically actuated braking system for an aircraft, comprising: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a first motor controller for generating a first drive signal for the EMAbrake, and a second motor controller for generating a second drive signal for the EMAbrake, wherein the first motor controller and the second motor controller are dissimilar so as to provide protection against common mode failure of the first and second motor controllers.

A brake control circuit for determining if a brake command from a brake pedal is valid is provided. The brake control circuit includes at least two independent channels configured to receive data indicative of brake pedal deflection for the brake pedal, and logic circuitry operatively coupled to the at least two independent channels. The logic circuitry is configured to generate a valid brake flag when the respective channels receive data that are within a predetermined range of one another, and to generate an invalid brake flag when the respective channels receive data that are not within a predetermined range of one another.