67results about "Brake regulators" patented technology

The invention provides an aircraft ground steering system and an aircraft ground steering control method, which can realize steering and runway separation of an aircraft under a low-speed condition even if a front wheel turning system cannot work normally, and can inhibit or avoid additional weight increase. The aircraft ground steering system comprises a turning hand wheel assembly used for controlling a front wheel turning system to achieve steering of an aircraft when the aircraft slides on the ground at a low speed; the brake system comprises a brake control part, and the brake control part is used for controlling the brake pressure of the left main undercarriage wheel and the brake pressure of the right main undercarriage wheel; and a standby turning control unit capable of switching to a standby mode in which the brake pressure of the left main landing gear wheel and the brake pressure of the right main landing gear wheel are controlled via a brake control unit according to the angle of the hand wheel of the turning hand wheel assembly operated by a pilot.

An emergency autoland braking system for aircraft includes an electromechanical actuator configured to provide a braking force to rudder pedals for actuating a braking system without altering the existing braking system of the aircraft. An equalized braking force may be applied to both rudder pedals via a force balancing mechanism and a single linear actuator, or differential braking force may be applied via independent linear actuators. The system is compatible with both open and closed loop control for commanding a braking force.

The invention relates to the technical field of brake control, in particular to a dual-redundancy brake system capable of interactively sharing and reconstructing data and a brake control method.The dual-redundancy brake system comprises an anti-skid control parameter acquisition module, an anti-skid brake control box, a main signal system and an auxiliary signal system, the acquisition module is used for acquiring antiskid control parameters of a brake system; a main control board and an auxiliary control board are arranged in the anti-skid brake control box and communicate with each other through a bus. The main signal system is used for transmitting a redundancy signal of the anti-skid control parameter acquisition module to the main control board; and the auxiliary signal system is used for transmitting the other redundancy signal of the anti-skid control parameter acquisition module to the auxiliary control board. According to the invention, the working continuity and safety of the system are ensured, and the use efficiency and reliability of the brake system are greatly improved.

A method for controlling anti-skid braking in civil aircraft involves constructing an anti-skid braking model and flight dynamics and kinematics models of the aircraft to analyze the forces acting on the aircraft system and obtain the corresponding forces and torques. For the anti-skid braking system, a BSMC controller is designed to control the braking coefficient μ. Brake This invention controls the braking force to ultimately control the anti-skid braking system of civil aircraft. It uses a backstepping slip mode controller (BSMC) to control the aircraft's braking commands, ensuring the system maintains the optimal slip ratio during braking, maximizing braking efficiency, reducing wheel wear, and minimizing the cost of the aircraft's braking system.

The invention discloses a passive undercarriage braking system and method for an eVTOL aircraft. The system comprises a front undercarriage, a main undercarriage and a braking system. In the braking system, a comprehensive controller is used for receiving a braking fault signal sent by a braking controller, an emergency braking fault signal sent by a passive emergency braking control valve unit and a braking instruction signal sent by a ground work station, and normal braking or emergency braking is judged to be executed; when it is judged that normal braking is executed, a braking instruction signal is sent to a braking controller so as to control a left airplane wheel and a right airplane wheel to execute normal braking through a left airplane wheel braking control channel and a right airplane wheel braking control channel; and when it is judged that emergency braking is executed, a braking instruction signal is sent to the passive emergency braking control valve unit so as to control the left airplane wheel and the right airplane wheel to execute emergency braking through the emergency braking control channel. The problem that when an existing hydraulic brake system is applied to an eVTOL aircraft, the unique operation requirement of the eVTOL cannot be met is solved.

The invention relates to the technical field of aircraft anti-skid brake control systems, in particular to a stop valve for a brake system of a high-pressure system aircraft, which comprises a valve casing, a slide valve and an electromagnetic valve assembly are arranged in the valve casing, and the slide valve comprises a valve sleeve and a reset assembly; an end cover is arranged at one end of the valve shell; the valve sleeve is arranged in the valve shell, a valve element is movably arranged in the valve sleeve, an oil inlet cavity is formed between the valve element and the oil inlet, a control cavity hole and an output cavity hole are formed in the valve sleeve, and the control cavity hole is used for being communicated with an output channel of the electromagnetic valve assembly through a control oil way arranged on the valve shell. The output cavity hole is used for supplying oil to a brake servo valve of a brake system through an output oil way arranged on the valve shell when the output cavity hole communicates with the oil inlet cavity, and a second seal and a third seal are arranged on the periphery of the valve sleeve. The reset assembly is arranged between the valve element and the end face of the end cover. The length of the slide valve is reduced, so that the structure is more compact; and the reliability of the stop valve in a high-pressure system airplane brake system is improved.

This application addresses the problems of large runway space occupation and potential airport traffic congestion during turning in current aircraft ground coordinated turning control methods. It proposes an aircraft ground coordinated turning system, and a sliding mode control method and system thereof. Based on real-time parameters of an aircraft, the state of the aircraft ground coordinated turning system is controlled on a composite sliding mode surface for nose wheel-main wheel coordinated turning through a nose wheel-main wheel coordinated turning control law. Specifically, a model for the aircraft ground coordinated turning system is developed. Aiming at the control problem in the traditional aircraft ground turning phase, and considering the problems such as oversteering of the nose landing gear and a large turning radius in the traditional nose wheel steering technology. Through coordinated turning of the nose wheel and main wheels, the turning radius is effectively reduced.

An aircraft (fig.1,100) has a brake system 248 that issues a command for a target deceleration level during landing and limits the aircraft braking when skid conditions are detected. A control system

A kind of airplane brake system air-ground signal control method, through air-ground signal control circuit, determine magnetic latching relay, determine airplane ground signal, determine airplane air signal and determine airplane air-ground control logic realize the control of airplane brake system air-ground signal, the original airplane brake system electrical control system landing gear system landing switch and landing gear is retracted to position switch respectively increase magnetic latching relay in this application, the ground state of airplane is determined by landing gear system landing switch and magnetic latching relay, the air state of airplane is determined by landing gear is retracted to position switch and magnetic latching relay, completely solve the problem of unstable and unreliable airplane air / ground signal due to landing gear system landing switch simultaneously determining the air / ground state of airplane during airplane landing phase due to landing gear system landing switch repeatedly disconnecting and connecting, improve the safety of airplane brake system.

The invention discloses a control method for suppressing an aircraft wheel speed interference signal, and belongs to the technical field of aircraft brake control. According to the method, in the braking process, firstly, the airplane wheel speed vw0 at the t0 moment is recorded, and the virtual airplane speed vc0 is generated; at the moment t1, if the increment of the airplane wheel speed vw1 relative to the vw0 is larger than a preset threshold value delta, a virtual airplane speed vc1 is generated in a transient state, a to-be-confirmed identifier is set, and meanwhile the vc0 is kept effective continuously; and at the moment t2, if the reduction amount of the airplane wheel speed vw2 relative to the vw1 is larger than a preset threshold value delta j, the increment at the moment t1 is judged to be a false interference signal, the vc1 is cleared away, and the effectiveness of the vc0 is recovered. According to the method, the pulse type interference characteristic of increasing first and then decreasing is recognized, accurate filtering of instantaneous increasing distortion of the airplane wheel speed is achieved, braking pressure loss or anti-skid faults caused by the instantaneous increasing distortion are avoided, meanwhile, the real airplane wheel speed increasing process is not affected, and the braking efficiency is guaranteed.

The invention provides an automatic balancing device and method for the braking torque of an airplane in the high-speed taxiing stage. The device comprises a braking pressure sensor, an anti-skid control unit, a servo valve, a speed sensor, an instruction sensor and a central controller. The signal output end of the brake pressure sensor is respectively connected with the left brake pressure signal input end and the right brake pressure signal input end of the central controller; the signal output end of the speed sensor is connected with the airplane wheel rotating speed signal input end of the antiskid control unit; the output end of the instruction sensor is connected with the brake instruction input end of the central controller; the collaborative pressure relief instruction output end of the central controller is connected with the collaborative pressure relief instruction input end of the anti-skid control unit; an anti-skid current output end of the anti-skid control unit is connected with a control current input end of the servo valve; the pressure output end of the servo valve is connected with a brake pipeline of a corresponding airplane wheel; the input end of the instruction sensor is connected with a brake pedal; and the airspeed signal input end of the central controller is connected with an airspeed system.

An aircraft, comprising: a brake lever for receiving a pilot braking input as a lever stroke of the brake lever; a brake wheel operatively coupled to the brake lever to brake the aircraft based on the lever stroke; a brake actuator operatively coupled to the brake wheel to apply a braking force in response to a braking pressure supplied to the brake actuator; and a brake pressure circuit. The brake pressure circuit is configured to: estimate a maximum braking pressure above which the brake wheel will slip relative to the ground surface; scale a lever gain of the brake lever to command the maximum braking pressure at a full stroke of the brake lever such that a remaining brake lever stroke indicates an amount of remaining braking capacity of the aircraft; and brake the brake wheel based on the lever gain and the lever stroke.

Provided is an aircraft hand controls. The aircraft hand controls may comprise a set of left and right brake hand controls and a rudder hand control. The set of left and right brake hand controls may be operatively connected to the rudder pedals or toe brakes. The set of left and right brake hand controls may also comprise a hydraulic brake adaptation for plumbing hydraulic pressure into the aircraft's hydraulic brake system. The aircraft hand controls may comprise one or push-to-talk buttons.

Disclosed is an aircraft system (10) for an aircraft (100). The aircraft system (10) has a controller (12) configured to determine, based on a criterion indicative of an aircraft condition or a runway condition, a maximum braking level able to be applied to a brake of the aircraft (100) in an emergency braking mode.

The application discloses a kind of low leakage high response high reliability pressure servo valve, the pressure servo valve includes torque motor, valve body, spool, reset spring and oil inlet nozzle, oil return nozzle and baffle composition, oil inlet nozzle is close to baffle at zero, oil return nozzle and baffle exist initial spacing, by designing the internal flow passage of valve body, make nozzle control cavity pressure and working oil port pressure respectively act on the left and right ends of spool, adjust spool rod diameter so that the action area of both ends is not equal, reach the purpose of using lower nozzle control cavity pressure to control higher working oil port pressure, improve the response speed of pressure servo valve.The right end of spool is equipped with reset spring, push spool to the leftmost position at zero, connect working oil port and oil return port, realize safety protection function.The application can solve the problem of low leakage and high response conflict of existing double-nozzle baffle pressure servo valve, and achieve the development goal of low leakage, high response and high reliability.

An anti-skid braking system based on an adaptive reference speed module and a control method. By means of the adaptive reference speed module, an aircraft speed is divided into three sections, i.e., a high section, a medium section and a low section, and an aircraft deceleration rate is calculated. On the basis of the aircraft deceleration rate, the aircraft speed and a wheel speed, a corresponding reference speed deceleration rate is calculated, and a reference speed for the next moment is output. Since the reference speed deceleration rate in the method is determined on the basis of a runway condition, the aircraft speed and the wheel speed, it can be ensured that a slip rate of a wheel relative to the aircraft is kept within an optimal slip rate range, and a ground adhesion torque is used to the maximum extent, thereby improving the braking efficiency and reducing the braking distance.

The present invention relates to the technical field of aircraft wheel brakes, and more specifically, to a redundant aircraft wheel brake control system and its switching method. The system includes: a second brake control module controls wheel deceleration when a first brake control module fails; and a third brake control module controls wheel deceleration when both the first and second brake control modules fail. This system reduces the time required by the pilot to manually switch to the third brake control module, shortens the aircraft's braking time, and ensures the safety and reliability of the wheel brake system.

The invention discloses a low-speed large-angle turning control system and method for a large aircraft, and belongs to the field of aircraft ground control. A low-speed large-angle turning controller and an auxiliary turning switch are designed and incorporated into an existing aircraft control system to jointly form a low-speed large-angle turning control system, cooperative turning control over front wheels and main wheels of an aircraft is achieved, and an additional mechanical executing mechanism does not need to be added; by means of the control method, when the aircraft turns, differential thrust and differential brake are provided, front wheel turning is assisted, and the target turning radius of the aircraft and lateral force borne by tires are effectively reduced.

The present invention relates to a device (10) for braking a wheel (R), comprising: · - a brake which at least comprises a first actuator (11.1) and a second actuator (11.2), which are designed to apply a braking torque to the wheel (R); · - a control system (13), which is designed to control the first actuator and the second actuator respectively according to a required braking value; · - at least a first braking torque sensor (15.1), which is designed to provide a first measured value of the braking torque applied to the wheel by the brake to a control unit. According to the invention, the control system is designed to interrupt the control of the first actuator (11.1) or the control of the second actuator (11.2) when the braking torque measured by the first sensor (15.1) exceeds a pre-determined braking torque limit value.

A complex nonlinear load variable control method based on UAV electric braking is proposed. When the UAV aborts takeoff or during landing roll, the electric braking control system first iterates the mathematical model of the control system by querying parameters such as ground conditions and weather conditions from the flight control system, updating the control objective and threshold values ​​of various output parameters. Then, the electric braking control system incorporates parameters such as the UAV's current mass, airspeed, ground speed, and wheel speed into the closed-loop control logic of the braking process, and introduces differential control and ABS anti-skid control strategies to achieve rapid response and adjustment in abnormal situations during braking. Finally, closed-loop control of the actuator braking force is achieved primarily using current and secondarily using position. This invention can replace hydraulic braking control, enabling rapid short-distance braking of UAVs under complex nonlinear load variables and solving problems such as wheel lock-up during braking and single-sided wheel lock-up in crosswinds.

The present invention provides an anti-skid control system and method for the ground taxiing brake of an unmanned aerial vehicle, including: S1 obtaining the maximum allowable braking amount to prevent the main wheels from locking according to the state information of the unmanned aerial vehicle during taxiing and the aerodynamic force and moment balance relationship; S2 presetting a threshold value for the heading deviation information of the unmanned aerial vehicle during taxiing to determine whether the unmanned aerial vehicle is unstable; S3 giving a brake correction value according to the judgment result of S2. In the unstable state, the brake correction value <0; in the non-unstable case, the brake correction value = 0; S4 giving a brake set value and sending the brake set value to the brake valve system to implement braking. S5 repeating S1 to S4 to achieve fast and stable braking. The present invention can obtain the maximum allowable braking supply amount to prevent the main wheels from locking during the ground taxiing brake of the unmanned aerial vehicle, monitor in real time whether the heading of the unmanned aerial vehicle during the ground taxiing brake is unstable, and correct the braking supply amount in real time according to whether it is unstable, so as to avoid accidents of heading instability caused by inappropriate braking amount during the ground taxiing brake of the unmanned aerial vehicle.

The invention provides a taxiing control method, system and device, electronic equipment, a storage medium and a product. The taxiing control method comprises the steps of obtaining inlet and outlet pressure of an aircraft motor; judging whether aircraft wheels slip or not based on the inlet and outlet pressure and preset conditions; the preset condition is determined based on the pressure change rate and / or the slip coefficient; the motor and the airplane wheel are in transmission connection through a transmission structure; when it is determined that the airplane wheel slips, the output pressure of the motor is reduced, and airplane wheel slipping is restrained. Therefore, the ground condition does not need to be estimated, and the slipping state is quickly and accurately identified for sliding control directly according to the pressure change and the preset condition by utilizing the relationship that the pressure difference between the inlet and the outlet of the motor is reduced or the pressure change rate fluctuates drastically during slipping.

The application discloses a method and system for rapid pressure relief of an airplane wheel brake, which is characterized in that a cut-off valve is arranged between a brake pressure servo valve and a hydraulic system, the brake pressure servo valve and the cut-off valve are electrically connected with a BCU, the BCU receives brake working instructions in real time, judges, outputs a cut-off valve control signal, and connects the pressure supply of the brake pressure servo valve; meanwhile, the BCU outputs a control current of the brake pressure servo valve, the brake pressure servo valve outputs corresponding brake pressure, and brakes; during the braking process, when the wheel is in deep skidding or the brake pressure servo valve main valve core is stuck, the B port of the brake pressure servo valve cannot be relieved, the BCU does not output the cut-off valve control signal, the cut-off valve core returns to the initial position, the B port of the brake pressure servo valve is directly connected with the hydraulic system return port R, and the purpose of rapid pressure relief of the hydraulic system is achieved.

A method of controlling and optimizing braking and directional control of a vehicle operated on a contaminated, compliant, or non-compliant surface. The method includes steps of: collecting data from a plurality of sensors, the data being indicative of a condition of the contaminated, compliant, or non-compliant surface; sending the data to a neural controller having an algorithm configured to process the data. The algorithm includes: determining optimum braking and directional control instructions for the vehicle, generating warnings and alerts based on the calculated optimum braking and directional control instructions, and sending the optimum braking and directional control instructions to a braking and steering system of the vehicle and the warnings and alerts to an alert and warning system of the vehicle. The method further includes adjusting the steering and directional control of the braking and steering system in accordance with the optimum braking and directional control instructions provided by the neural controller.

The application discloses a control circuit for outputting reliable airplane air / ground signal, which comprises a power supply, a landing switch, a landing signal input end, a power supply ground, a landing gear retracting to position switch and a power supply input end, and further comprises a magnetic latching relay; the power supply is communicated with the power supply input end of an anti-skid brake controller; the power supply is respectively communicated with the power supply input ends of the landing switch and the landing gear retracting to position switch; two positive connection terminals of the magnetic latching relay are respectively communicated with the power supply output ends of the landing switch and the landing gear retracting to position switch, and the magnetic latching relay is respectively communicated with two negative connection terminals and the power supply ground; the positive connection terminal of a working end of the magnetic latching relay is communicated with the landing signal input end; and the negative connection terminal of the working end of the magnetic latching relay is communicated with the power supply ground. The application completely solves the problems of unstable and unreliable airplane air / ground signal caused by repeated disconnection and connection of the landing gear system landing switch, loss of brake function in the airplane braking process, reduction of man-machine efficiency of the airplane and long braking distance.

The present invention relates to an anti-skid pneumatic emergency brake system for aircraft wheel brakes. The system comprises an air pressure source, a brake pressure reducing valve, a wheel, an electromagnetic valve, a pressure switch, a time delay relay, a circuit breaker contact switch, and a power supply. The air pressure source, the brake pressure reducing valve, the electromagnetic valve, and the wheel are sequentially connected; the pressure switch, the time delay relay, and the electromagnetic valve are sequentially connected via electrical signals; the pressure switch is also connected to the brake pressure reducing valve. The pressure switch senses the air pressure output by the brake pressure reducing valve and outputs an electrical signal to the time delay relay. The power supply is a 28V DC power supply that supplies power to the pressure switch and the time delay relay via the circuit breaker contact switch. The anti-skid pneumatic emergency brake system senses the emergency brake pressure through the pressure switch, and the time delay relay controls the electromagnetic valve to periodically connect and disconnect, thereby achieving periodic brake release and braking operations. This achieves anti-skid braking and solves the problem of wheel dragging caused by continuous braking.

A method is provided for diagnosing a failure on an aircraft that includes aircraft systems configured to report faults to an onboard reasoner. The method includes receiving a fault report at an onboard computer of the aircraft from an aircraft system of the aircraft systems, the fault report indicating failed tests reported by the aircraft system. The onboard reasoner accesses an onboard diagnostic causal model represented by a graph describing known causal relationships between possible failed tests reported by the respective ones of the aircraft systems, and possible failure modes of the respective ones of the aircraft systems. The onboard reasoner diagnoses a failure mode of the aircraft system or another of the aircraft systems, from the failed tests, and using a graph-theoretic algorithm and the onboard diagnostic causal model. A maintenance action is determined for the failure mode, and a maintenance message is generated including the maintenance action.