29results about "Brake regulators" patented technology

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 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.

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.

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.

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 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 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 application relates to the technical field of airplane brake control, in particular to an airplane brake control method and system based on deceleration rate control and a medium, the method comprising the following steps: judging whether a brake system enters a deceleration rate control mode; acquiring a theoretical deceleration rate of a current period; acquiring a theoretical speed of the current period, acquiring a speed error of the current period, acquiring a final brake current, and controlling airplane brakes according to the final brake current. The application reduces the influence of brake disc torque differences on the control effect of the brake system, so as to improve the brake control capability of the anti-skid brake system.

The invention relates to the technical field of aircraft braking, in particular to an anti-skid braking control method based on self-adaptive reference speed, which comprises the following steps: a pilot steps on a pedal, a braking control unit receives a braking instruction, and an initial reference speed deceleration rate is set; the wheel speed is obtained, and the reference speed is calculated according to the current reference speed reduction rate; a reference slip rate is obtained through the airplane wheel speed and the reference speed, if the reference slip rate exceeds an anti-slip threshold value, the reference speed reduction rate is reduced by 0.8 m / s < 2 >, the brake pressure is reduced, and the airplane wheel is made to exit the slip state; if the reference slip rate does not exceed the anti-skid threshold value, the wheel speed reduction rate is calculated according to the wheel speed. According to the method, the accurate reference speed is obtained through the self-adaptive method, anti-slip control is carried out through the speed difference limiting the maximum brake pressure and the pressure bias, slip rate control can be carried out more accurately, the airplane wheels are in the optimal slip rate state, the brake efficiency is improved, and the brake distance is shortened.

A method of taxiing an aircraft may comprise: determining, via a brake controller, whether the aircraft is taxiing with a first thrust provided from a first side of the aircraft, a second thrust from a second side of the aircraft, or both the first thrust and the second thrust; and modifying, via the brake controller, a first brake pressure supplied to a first brake disposed on the first side of the aircraft as a function of pedal deflection in response to the taxiing with the first thrust only.

The application provides a digital valve array brake system and a control method, which comprises a pressure increasing valve group, a pressure reducing valve group and a control system, the pressure increasing valve group comprises a plurality of first switch valves, the plurality of first switch valves are connected in parallel between a high pressure end and a brake control end respectively, the pressure reducing valve group comprises a plurality of second switch valves and third switch valves, the plurality of second switch valves and third switch valves are connected in parallel between a low pressure end and the brake control end respectively, the flow area of the second switch valve is smaller than that of the third switch valve, and the control system selectively controls at least one first switch valve to work for increasing the pressure of the brake control end or selectively controls at least one second switch valve and / or third switch valve to work for reducing the pressure of the brake control end according to the slip rate of a wheel. The application can realize rapid pressure reduction when the brake pressure needs to be suddenly reduced, improve the anti-pollution ability of an airplane brake system and improve the reliability of the airplane brake system.

An aircraft including a control system configured to receive: an indication of the deceleration of the aircraft during landing, an indication of a target deceleration level for the aircraft, and an indication of factors that might prevent the aircraft from meeting that target deceleration level. The control system is configured to output a command to indicate to the pilot that the target deceleration level of the aircraft is not being met. The control system is configured to indicate whether this was caused by one of the brake systems of the aircraft being skid-limited or whether the aircraft is achieving maximum available braking and is still not able to meet the target deceleration level. The control system may be retrofitted by the installation of software on an existing aircraft. A method for determining and indicating scenarios that limit the aircraft's ability to decelerate during landing.

A braking unit (100) is described herein that comprises a braking means and means (120), configured to receive power from a power line (110), for engaging and disengaging the braking means. A first power signal line (130) is provided that is connected to the means (120) for engaging and disengaging said braking means and a second power signal line (140) is also provided that is connected to said means (120) for engaging and disengaging said braking means. The first power signal line (130) is connected to the means for engaging and disengaging the braking means via a first power switching device (150a) and the second power signal line (140) is connected to the means for engaging and disengaging the braking means via a second power switching device (150b).

A method for controlling brake assemblies of a vehicle is provided. Responsive to identifying a locked wheel protection event for a first wheel of a paired set of wheels on the vehicle, where the paired set of wheels is the first wheel on one side of the vehicle and a second wheel on an opposite side of the vehicle, a first brake pressure to a first brake assembly (160a, 160b, 160c, 160d) associated with the first wheel is released to zero pounds per square inch (PSI) and a second brake pressure to a second brake assembly (160a, 160b, 160c, 160d) associated with the second wheel of the paired set of wheels is reduced by a predetermined amount thereby reducing a yaw effect to the vehicle.

There is provided a pivot turn load alleviation (PTLA) brake system (12) for alleviating structural loads (28A) on a pivoting main landing gear (32) of an aircraft (10, 316, 96) in a pivot turn maneuver (30A, 30). The PTLA brake system (12) includes a brake control system (14) operatively coupled to at least two main landing gear (24), each having two or more wheels (46). The PTLA brake system (12) further includes a PTLA brake inhibit subsystem (16) coupled to the brake control system (14). The subsystem inhibits braking of one or more of the two or more wheels (46) of the pivoting main landing gear (32), in the pivot turn maneuver (30A, 30), so that at least one wheel (46) of the two or more wheels (46) is in an unbraked state (52), and a remaining number of the two or more wheels (46) are in a braked state (56). The PTLA brake system (12) alleviates structural loads (28A), and reduces wear (136) on the at least one wheel (46) that is in the unbraked state (52).

The invention relates to the technical field of aircraft anti-skid brake control, in particular to an aircraft self-adaptive anti-skid brake control method with runway / tire combination characteristic identification and pressure optimization functions, and the method comprises the following steps: estimating a current runway combination characteristic level in real time according to an aircraft wheel motion state and brake pressure; according to the updated basic brake pressure, the maximum brake pressure capable of being accepted is found, and the optimization pressure is obtained; comparing the expected brake pressure with the optimization pressure, and taking a minimum value of the two as a brake pressure instruction; when the airplane wheel slips, the output brake pressure is obtained according to the difference between the brake pressure instruction and the anti-slip instruction; and when the airplane wheels do not slip, the brake pressure instruction is used as the output brake pressure. According to the brake pressure optimization based on the runway combination characteristic estimation result, the maximum brake pressure allowed under the current runway and working condition is output on the premise of avoiding frequent slipping of airplane wheels, and efficient short-distance brake is achieved.

An aircraft system for an aircraft having a controller 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 in an emergency braking mode, wherein the maximum braking level is determined to be a first maximum braking level when a value of the criterion is above a pre-determined threshold and a second maximum braking level when a value of the criterion is no greater than the pre-determined threshold.

The invention provides an aircraft brake control system for controlling antiskid braking of an aircraft wheel, the system comprising a control assembly 300 having a mode controller 327 which sets the mode of operation of an antiskid brake calculator 325, configured to set a first mode, when an input of the indication of a brake energy supply configuration 305 indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command 330, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command. The invention also provides other aircraft brake control systems, aircraft landing gear, aircraft and methods of braking an aircraft.

The present application provides a system for the coordinated turning of an aircraft on the ground, its glide mode control procedure, and an associated system. The state of the coordinated turning system is controlled by a nosewheel-mainwheel-coordinated turning control law based on real-time aircraft parameters, such that the aircraft is maintained at a combined nosewheel-mainwheel-coordinated turning glide mode surface. A model of the coordinated turning system is specifically developed.In view of the conventional control problem during the turning of an aircraft on the ground, taking into account the problems of excessive steering of a nose landing gear and the large turning radius in the traditional technique of turning by nose wheel actuation, a glide mode control method is proposed for a system for the coordinated turning of an aircraft on the ground.

The invention belongs to the technical field of airplane control system design, and particularly relates to a multifunctional airborne comprehensive controller which has the functions of comprehensive hanging object control management, electromechanical control driving, external lighting control and anti-skid brake control. The comprehensive controller comprises a central processing module, a hanging object putting control module, a power supply module, a lighting control module, an electromechanical control module, an anti-skid brake control module and a case welding part; wherein the case welding assembly has a radio frequency signal processing function; the central processing module is the core of the multifunctional airborne comprehensive controller and is used for controlling the working logic of the whole multifunctional airborne comprehensive controller; the hanging object putting control module is used for controlling and managing hanging objects; the power supply module is mainly used for supplying power to each module in the multifunctional airborne integrated controller; the illumination control module is used for illumination and state indication; the electromechanical control module is used for outputting related electromechanical control signals; and the anti-skid brake control module is used for realizing output control of brake related signals.

The application discloses a kind of inhibiting aircraft brake pressure overshoot control method, considering that the step change of brake pressure can produce moment mutation, so as to cause wheel to enter frequent skidding state, if not timely pressure relief, brake pitch, brake efficiency is low, tire wear problem is prone to appear, the application is based on aircraft sliding speed according to left / right brake command signal, brake pressure speed-up control is carried out, can effectively avoid the frequent skidding of wheel caused by brake moment overshoot change, simultaneously, on the basis of pressure speed-up control, left / right brake pressure consistency control is carried out, so that aircraft can complete stable, efficient brake in normal landing brake process, improve the reliability and safety of brake system, and increase the brake distance of inhibiting overshoot control rear brake system under the same working condition, improve the deceleration rate, and avoid anti-skid work, brake performance is obviously improved.

The invention provides an aircraft brake control system for controlling antiskid braking of an aircraft wheel, the system comprising a control assembly 300 having a mode controller 327 which sets the mode of operation of an antiskid brake calculator 325, configured to set a first mode, when an input of the indication of a brake energy supply configuration 305 indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command 330, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command. The invention also provides other aircraft brake control systems, aircraft landing gear, aircraft and methods of braking an aircraft.

The invention belongs to the field of undercarriage brake control, and particularly relates to a single-wheel anti-deflection brake system of a main undercarriage. The brake system comprises a brake hydraulic energy source, a differential brake instruction switch, a brake instruction sensor, a brake device, a pressure sensor, a wheel speed sensor, a brake control unit, a brake control valve assembly and a differential brake electromagnetic valve. According to the main landing gear single-wheel anti-deflection braking system, a control framework of the main landing gear single-wheel anti-deflection braking system is designed, the problem that left braking and right braking are inconsistent possibly caused by main landing gear single-wheel braking is solved, and meanwhile the differential braking function can be achieved.