210results about "Brake regulators" patented technology

A method includes receiving an input brake command that indicates a desired amount of braking for a vehicle. A brake control signal is then derived from the input brake command to facilitate applying a braking force to a wheel of the vehicle, and the braking force facilitates achieving the desired amount of braking for the vehicle. The method further comprises determining that data from a sensor associated with the wheel is unavailable, and then modifying the brake control signal in response to determining that the data is unavailable. The modification may be based on sensor data or controller output associated with a second wheel where data is available. Such modification facilitates the desired amount of braking for the vehicle.

According to the present invention, an electromechanical braking system is provided. The braking system includes at least one brake system control unit (BSCU) for converting an input brake command signal into a brake clamp force command signal. In addition, the braking system includes a first electromechanical actuator controller (EMAC) and a second electromechanical actuator controller (EMAC) configured to receive the brake clamp force command signal from the at least one BSCU and to convert the brake clamp force command signal to at least one electromechanical actuator drive control signal. Further, the braking system includes at least one electromechanical actuator configured to receive the at least one drive control signal and to apply a brake clamp force to at least one wheel to be braked in response to the at least one drive control signal. Moreover, the first EMAC and the second EMAC are configured to perform antiskid control in relation to the at least one wheel to be braked.

Improved methods and systems for controlling hydraulically or electrically actuated anti-lock brake systems (ABS) on air and land vehicles requiring only measurement of wheel angular speed although brake torque measurements can also be employed if available. A sliding mode observer (SMO) based estimate of net or different wheel torque (road / tire torque minus applied brake torque) derived from the measured wheel speed is compared to a threshold differential wheel torque derived as a function of a “skid signal” also based on wheel speed only to generate a braking control signal. The braking control signal can be employed to rapidly and fully applying and releasing the brakes in a binary on-off manner and, as an additional option, possibly modulating the maximum available brake hydraulic pressure or electrical current when the brakes are in the “on” state in a continuous manner. In the case of the basic on-off component of braking, the brakes are released when the estimate of differential wheel torque is less than the threshold differential wheel torque (i.e. for relatively high values of brake torque), and the brakes are applied fully when the estimate of differential wheel torque is greater than or equal to the threshold differential wheel torque. For aircraft landing gear applications, a fore-aft accelerometer mounted on the landing gear can be used to suppress nonlinear gear displacement oscillations commonly called gear walk in the direction of wheel roll.

The invention relates to an airplane anti-skid brake control system and an airplane anti-skid brake control method. In the airplane anti-skid brake control system, two airplane wheel speed sensors are respectively applied to a left airplane wheel and a right airplane wheel of the airplane and connected with the input end of an electronic anti-skid control box; an electro-hydraulic servo valve is connected with a brake valve, a brake device, the electro-hydraulic servo valve and the electronic anti-skid control box respectively; the input port of the electronic anti-skid control box is connected with the airplane wheel speed sensors; and the output port of the electronic anti-skid control box is connected with the electro-hydraulic servo valve. In the invention, the electronic anti-skid control box judges true and false of the received airplane speed signal by comparing the airplane speed signal to be judged with the speed of the airplane wheels at different time or comparing the speed signals of the two airplane wheels so as to perform anti-skid control according to the speed signals of the airplane wheels which are judged to be true; and the airplane wheel brake pressure is adjusted according to the received instruction through the electro-hydraulic servo valve, so safe and reliable brake of the airplane wheels is realized.

The invention relates to an airplane electrical signal transmission brake antiskid control system. When brake is carried out, an electro hydraulic servo valve can not output brake pressure, a control box emits a control signal to an electromagnetic hydraulic lock, the electromagnetic hydraulic lock unlocks by energization, the hydraulic power source is switched on, and the brake is carried out on a brake machine wheel with maximum brake pressure. During a brake process, if the machine wheel slips, the control box controls the electromagnetic valve for energization to release pressure. The system is simple and easy to be carried out, the reliability and security of the brake system operation can be greatly increased during taking off, landing rollout processes, the work load of a driver is reduced, even the electro hydraulic servo valve generates fault, the tire burst can be effectively avoided, and the airplane usage safety is ensured.

The invention relates to a mixed airplane brake system and a control method. A brake valve of the mixed airplane brake system is connected to a airplane pressure supply system, an electro hydraulic servo valve oil inlet and an oil returning tank through a pipeline; the electro hydraulic servo valve is connected to a brake nozzle of the brake valve, an oil inlet of the electromagnetic valve and an airplane oil return tube through the pipeline; and an electromagnetic hydraulic lock and the electro hydraulic servo valve are parallel channels on a hydraulic line. An oil inlet pressure transducer is arranged on the pipeline between the brake valve and the electro hydraulic servo valve; a brake port pressure transducer is arranged on the pipeline between the electromagnetic valve and a brake machine wheel. Under the failure of the electro hydraulic servo valve, an airplane antiskid brake control system can automatically convert a current normal brake mode to a standby brake mode and then enables reliable operation, driver intervention is not required, so that the work load of the driver is reduced. The mixed airplane brake system enables mode record on a fault state of the electro hydraulic servo valve, and is convenient for troubleshooting and maintenance by maintainer after flight.

The invention relates to an antiskid control method for an aircraft brake and an aircraft brake system. An active control concept is adopted, and through combination of aircraft speeds during braking, and through consideration of the influence of lifting force for the high-speed aircraft, actual brake pressure is gradually increased along with the decelerating of the aircraft, dangers that at the beginning of brake, ground attachment coefficients are small, so that the aircraft skids, and even tyres can be exploded due to brake are avoided; besides, requirements for braking skills of a pilot are further reduced, overcoming of human factors is facilitated, and using safety of the aircraft at high speed is guaranteed; the braking pressure is gradually enlarged along with the decelerating of the aircraft, so that potential accident hazards existing in brake of the aircraft at high speed are solved, but also the operating frequency of antiskid control is reduced, and the braking efficiency is improved. The antiskid control method of the aircraft brake and the aircraft brake system disclosed by the invention are suitable for development of a new aircraft, and are suitable for refitting of active service aircraft types.

The invention discloses an airplane telex brake system directly controlled by a brake instruction. An electrical output interface of a brake instruction sensor is connected with an electrical input interface of a brake control box; an electrical output interface of the brake control box is connected with a brake control valve; an electrical interface of the brake control valve is connected with the brake instruction sensor and the brake control box respectively; and the electrical output interface of the brake instruction sensor is connected with an electrical input of an electro-hydraulic servo valve through a cable. A brake instruction electric signal sent by the brake instruction sensor in the airplane telex brake system directly reaches the brake control valve without passing through the brake control box to directly operate the airplane telex brake system which controls the brake control valve to brake, so that the middle procedure is eliminated, and entry and interference of a false signal are avoided; and furthermore, transmission of a brake instruction current signal is high in interference resistance, so that the reliability and the safety of operation of the telex brake system during taking off and landing of an airplane are obviously improved.

Various brake control systems and methods are provided herein. In one implementation, a brake pressure control system having a shutoff valve (24) in a hydraulic conduit (26, 30) between a pressure origination source (16, 18) and a wheel brake (20), the shutoff valve selectively isolates the pressure origination source from the brake responsive to an indication that a wheel associated with the brake meets a skid condition, and an actuator assembly (28) comprising an actuator (34) that regulates fluid brake pressure after the shutoff valve isolates the pressure origination source from the brake. The actuator assembly operates independently of the shutoff valve and is coupled to the hydraulic conduit between the shutoff valve and the brake. The actuator assembly also effects displacement of the actuator for increasing and decreasing brake pressure. A controller (44) determines if the skid condition has been reached and controls the shutoff valve and the actuator assembly based upon the skid condition.

The invention relates to a braking system architecture for an aircraft having wheels 1 braked by means of respective brakes 2, each brake having a plurality of electromechanical actuators 3a, 3b, the braking system having controllers 8a, 8b for distributing electric power Ps to the actuators 3a, 3b in response to a braking setpoint, each controller 8a, 8b being associated with some of the actuators of any given brake. According to the invention, each controller 8a, 8b has an input Ev for receiving information about the rotary speed of the wheel 1 braked by the actuators associated with said controller, the controller including processor means 13 for modulating the power transmitted to the actuators as a function of the speed of rotation of the wheel in order to provide anti-skid protection.

A system and method for adjusting a yaw of an aircraft having an antilock braking system is disclosed. The antilock braking system includes a controller configured to receive a directional input from a rudder. The controller is further configured to deliver a braking output to at least one of a left wheel brake and a right wheel brake. A position of the rudder indicates a pilot's desired steering response, and to allow for braking optimization by the antilock braking system, the pilot depresses fully the left wheel brake pedal and the right wheel brake pedal. The controller receives the directional input after both the right wheel brake pedal and the left wheel brake pedal have been fully depressed. The controller then delivers the braking output and a pressure on one of the left wheel brake and the right wheel brake is reduced in accordance with the directional input.

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.

The invention relates to an anti-skid brake control system of an airplane. According to the anti-skid brake control system of the airplane, a robust interference-resisting property of a differentiator or a second order sliding mode differentiator is tracked to construct an airplane speed deceleration rate signal for calculating a slippage force, and a longitudinal dynamics process is prevented from being learned and identified; the method does not need to assume that a brake longitudinal force is distributed uniformly, and can be used for a multi-wheel brake system; furthermore, a safe working range of the brake system is considered and a brake pressure is restrained; the anti-skid brake efficiency and the anti-locking safety are considered and the anti-skid brake control system of the airplane has the certain advancement.

The invention provides an aircraft electro hydrostatic brake actuator. The output shaft of a brushless direct current motor is coaxially connected with a displacement-fixed two-way plunger pump, a pressurized tank is used for supplying initial pressure for the inlet of the displacement-fixed two-way plunger pump, one outlet of the displacement-fixed two-way plunger pump is connected with a hydraulic cylinder through an oil filter and a two-position two-way solenoid valve, the other outlet of the displacement-fixed two-way plunger pump is connected with the two-position two-way solenoid valve through the oil filter and a relief valve, the pickup state of the two-position two-way solenoid valve is controlled by a solenoid valve control unit, thus switching between brake pressure tracking and take-off line brake pressure maintaining functions is realized, the internal pressure of the hydraulic cylinder is measured by a pressure measuring unit, the pressure information is transmitted to a controller for pressure closed-loop control, the controller receives a brake pressure instruction through an instruction port, to further control the solenoid valve control unit and the brushless direct current motor and a brake disc is driven by the hydraulic cylinder. The aircraft electro hydrostatic brake actuator is simple in structure, high in efficiency, high in frequency response and small in size and weight, and take-off line brake pressure maintaining can be realized for a long time.

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.

An airplane inertia anti-skid brake system capable of guaranteeing emergency brake comprises a normal brake system and an emergency brake system, wherein the normal brake system and the emergency brake system adopt two independent pressure supply source systems and are switched through a switching valve. The system structure is improved through addition of a control device, so that normal brake fails during emergency brake, the switching valve is completely switched under the action of emergency brake pressure, and even though the emergency brake and the normal brake are used simultaneously, the switching valve can be switched to the emergency brake system. The control device adopts an electrical switch, a circuit of a solenoid valve is off by the switch, if the normal brake is used, the solenoid valve releases pressure of the normal brake system, the switching valve is thoroughly switched without hindrance, and emergency brake pressure is output.

The invention relates to a dual-brake system for a single-wheel brake of an aircraft. A brake antiskid control part is formed by an aircraft wheel speed sensor, a control box and an electro-hydraulic servo valve; and the aircraft wheel speed sensor, the control box and an electromagnetic valve are used for realizing braking selection of a braking aircraft wheel through adopting an aircraft braking speed control method. According to the dual-brake system disclosed by the invention, a hydraulic pipeline through which a brake system is outputted to an aircraft wheel brake device is divided into a small brake device hydraulic pipeline and a large brake device hydraulic pipeline, the small brake device hydraulic pipeline is kept unblocked, and the on-off of the large brake device hydraulic pipeline is controlled by a control device, so that the function that when the airplane slides on the ground, only the small brake device runs, and in other situations, all the brake devices run is realized, and therefore the purposes that during sliding braking, the wear of a carbon disk is reduced, and the service life of the carbon disk is prolonged are achieved. According to the dual-brake system disclosed by the invention, 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 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 motor controller for generating a drive signal for the EMAbrake; and a braking control unit for generating a braking force command signal for the EMAC; wherein the braking control unit and the EMAC are disposed together with the EMAbrake in a common line replaceable unit (LRU).

The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.

Provided is an airplane wheel brake system capable of selecting a slipping braking mode according to braking pressure. The airplane wheel brake system comprises a hydraulic brake valve, an electro-hydraulic servo valve, a control box, a magnetic valve, a pressure sensor and an airplane wheel speed sensor. The control box, the electro-hydraulic servo valve and the airplane wheel speed sensor form a brake slipping prevention control part. The magnetic valve, the pressure sensor and the control box are used for achieving braking selection for a brake airplane wheel. The pressure sensor is installed on a hydraulic pipeline at a brake opening of the electro-hydraulic servo valve. The hydraulic pipeline delivered from the brake system to an airplane wheel brake device is divided into two paths, and the two paths communicate with a small brake device oil inlet and a large brake device oil inlet correspondingly. By controlling the two paths of the hydraulic pipeline, only a small brake device operates when an airplane glides on the ground, and the two brake devices operate simultaneously under other situations, abrasion to a carton plate during slipping braking is reduced, and the service life of the carbon plate is prolonged. The problems that an existing carbon brake plate for a single-wheel single-brake mode is badly abraded and is short in service life are solved, the service life of the carbon plate is prolonged, and the economic benefits of the carbon plate are increased.

A system and method for objectively evaluating an airport runway condition, where conditions pertaining to aircraft landing factors are compiled and used to determine a runway braking condition. One set of conditions pertains to aircraft landing factors, including brake metered pressure, wheel speed, and aircraft deceleration, and a second set of factors relate to pilot controlled parameters. A condition report is generated and made available to pilots of subsequently landing aircrafts prior to landing.

The invention provides a power-on self-test protection method for an anti-skid brake system of an airplane. Comprehensive fault diagnosis is conducted for all electrical functions in the anti-skid brake system, and whether the anti-skid brake system can continue to be used or not is determined according to a fault diagnosis result. After a power-on self-test, periodical self-testing of the anti-skid brake system is conducted automatically. Fault diagnosis is conducted for only part of the electrical functions during periodical self-testing. The period refers to the control period of an anti-skid brake of the airplane, and the control period is generally 20 ms or 40 ms. The power-on self-test protection method is suitable for protection of the anti-skid brake system of the airplane in the abnormal starting process of the anti-skid brake system of the airplane and also suitable for emergency restarting of the anti-skid brake system of the airplane when specific brake faults occur after the anti-skid brake system of the airplane is started. By adoption of the power-on self-test protection method for the anti-skid brake system of the airplane, the reliability and safety of the anti-skid brake system of the airplane are improved.

The adaptive brake application and initial skid detection system allows rapid brake application and prevents deep initial skids. Brake pressure is compared with a predetermined threshold brake pressure. Wheel velocity error signals are also generated to indicated the difference between the wheel velocity and a reference velocity signal. A pressure bias modulator integrator responsive to brake pressure signals adjusts the wheel velocity error signals to provide an anti-skid control signal. The pressure bias modulator integrator can also be initialized to the value of the measured brake pressure when the wheel velocity error signals indicate the beginning of a skid. Brake pressure difference signals are generated to indicate the difference between brake pressure and a commanded brake pressure, and an adjusted brake pressure error signal is generated in response to the brake pressure difference signals.

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.

The load on an aircraft component, such as the load on a landing gear leg during braking, is measured with a contactless, all-weather displacement measuring system. The system includes a control unit a controllable microwave emitter of electromagnetic radiation and a microwave detector comprising a plurality of antennae. When the aircraft component is subjected to a load relative movement of the emitter and detector is caused. The detector generates in response to microwave radiation received from the focused beam of radiation emitted by the emitter a signal that is received by a signal processor of the control unit. The signal received by the control unit depends on the relative positions of the emitter and detector. The control unit is arranged to provide an output signal representative of the load sustained by the aircraft component. The system may be used to control braking in dependence on the output signal so as to maximise braking efficiency without overloading the landing gear leg.

The invention relates to an aircraft anti-skid brake control method based on brake moment feedback. The aircraft anti-skid brake control method comprises steps as follows: brake moment and revolving speed of aircraft wheels are detected; an actual slip factor is determined on the basis of the brake moment and the revolving speed; the actual slip factor and a slip factor threshold value are compared; if the actual slip factor is equal to the slip factor threshold value, the slip factor threshold value is updated; the brake moment is reduced so as to enable the actual slip factor to be smaller than the updated slip factor threshold value. According to the scheme, skid of the aircraft wheels can be avoided, and the anti-skid brake efficiency of an aircraft under the condition of complicated runway surfaces is improved.

Disclosed is an airplane turning limitation control method through differential braking. The ground friction is utilized to the utmost extent, on the premise of guaranteeing the stable and safe airplane turning process, according to different turning requirements, the engine thrusting force and braking torque state parameters controlling the airplane turning most efficiently are provided to pilots correspondingly, the airplane turns in the highest turning speed, the airplane operating potential is played to the utmost extent, the front and main wheel wearing is reduced during turning, the engine oil consumption is low, and the airplane is prevented from skidding and tipping. Thus, the maximum friction coefficient of the wheels and runway is of the input amount, and the method has the advantages of high turning speed and stability, safety and efficiency of the turning process.

Provided is a determination method for a tyre and ground optimum brake slipping point. An optimum brake slipping point of a tyre and the ground is determined during the brake process through the method, the combination coefficient of the optimum brake slipping point is calculated, calculation of a distance efficiency and a combination coefficient utilization rate of a brake system can be carried out according to test data detected in brake tests and according to requirements of standards, and the working efficiency of the brake system can be evaluated accurately. Through the method, an ideal curve of a brake resistance, a combination moment and a combination coefficient can be obtained in a 100% working efficiency condition, the resistance efficiency, the distance efficiency and the combination coefficient utilization rate of the brake system are calculated according to the ideal curve, and the working efficiency of the brake system is evaluated accurately.

The invention discloses a DSP+FPGA (digital signal processor and field programmable gate array)-based anti-skid brake control box of an aircraft brake system, and aims at solving the technical problem that a conventional DSP-based anti-skid brake controller of an aircraft has the poor control accuracy. The technical scheme is that the control box comprises a power panel, a control panel and a monitoring panel, wherein the control panel and the monitoring panel adopt high-performance DSP+FPGA as a control core, and the complex control operation capacity of the DSP and the high-efficiency data processing capacity of the FPGA are combined, so that the number of discrete elements in the panels is reduced, the number of the panels in the brake control box is reduced, the system operation speed is increased, and the control accuracy is high. The integration and the modularization of the anti-skid brake control system of the aircraft are realized, and the reliability of the system is relatively high. According to the anti-skid brake control box of the aircraft brake system, the complex control operation capacity of the DSP and the high-efficiency data processing capacity of the FPGA are combined, so that the system operation speed is increased and the control accuracy is improved; the control accuracy is improved from 1 percent in the prior art to 0.5 percent.

The invention relates to an electric hydraulic pressure servo valve, wherein two ends of a nozzle in a torque motor are respectively communicated with two ends of a slide valve control cavity through the outlet of a throttling hole; the brake port of the electric hydraulic pressure servo valve is communicated with that of a slide valve; a brake port oil filter is connected in series between the brake ports of the slide valve and the electric hydraulic pressure servo valve; the oil inlet of a brake port pressure sensor is connected to an oil path between the brake port of the slide valve and the oil inlet of the brake port oil filter; a throttler is arranged between the oil inlet of the electric hydraulic pressure servo valve and an inlet oil filter; the oil inlet of an oil inlet pressure sensor is communicated with the oil path of the inlet oil filter; the oil inlet of a hydraulic control valve is communicated with that of the slide valve; the control cavity of the hydraulic control valve is communicated with the oil path of the oil return port of the slide valve; and the oil outlet of the hydraulic control valve is also communicated with the oil path of the oil return port of the slide valve. According to the electric hydraulic pressure servo valve, the damage caused by pollutants in oil fluid is prevented effectively, so that the working stability and the working reliability of the servo valve are improved; and the inlet pressure signal and the outlet pressure signal of the servo valve can be provided, so that the working stability and the working reliability of the servo valve are improved.