Aircraft redundant wheel brake control system and switching method thereof

Abstract

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.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft wheel brakes, and in particular to an aircraft redundant wheel brake control system and a switching method thereof. Background Art

[0002] An aircraft's wheel brake control module (WBC) is one of its most critical systems, playing a crucial role during takeoff and landing. It typically includes a normal brake with anti-skid functionality and a third brake without anti-skid functionality, ensuring highly reliable and safe braking.

[0003] In the prior art, aircraft wheel brake control modules typically have two architectures. One employs two hydraulic sources, one providing hydraulic pressure to a normal brake control module and another to a backup brake control module. The normal brake control module is controlled by a normal brake controller, while the backup brake control module is controlled by a backup brake controller. A tertiary brake control panel is installed in either the normal or backup brake controller, sharing electrical and hydraulic equipment with the normal or backup brake control system. The other architecture employs both a normal brake control module and a tertiary brake control module, with the normal brake control module being fly-by-wire and the tertiary brake control module being a mechanical backup.

[0004] In both of the above architectures, the pilot must independently determine whether to apply the tertiary brake based on the status of the normal brake control module and the backup brake control module. However, if the control valve of the normal brake control module or the backup brake control module fails, the tertiary brake function will be lost accordingly. Therefore, how to quickly switch to ensure aircraft safety and braking efficiency when a failure occurs is an urgent problem that needs to be solved.

[0005] Therefore, it is necessary to provide an aircraft redundant wheel brake control system and a switching method thereof to solve the above problems. Summary of the Invention

[0006] The present invention provides an aircraft redundant wheel brake control system and a switching method thereof, thereby solving the existing problems.

[0007] The present invention provides an aircraft redundant wheel brake control system, which adopts the following technical solution:

[0008] a first brake control module, a second brake control module, a third brake control module, and a hydraulic source module;

[0009] The first brake control module, the second brake control module and the third brake control module each include a brake controller and a hydraulic control module, wherein a hydraulic control module is connected to the brake device of each wheel;

[0010] A hydraulic source module, the output end of which is connected to the three hydraulic control modules through output pipelines;

[0011] The hydraulic control modules of the first brake control module and the second brake control module include: a control valve, a shut-off valve, and a hydraulic fuse, which are sequentially arranged on each output pipeline of the hydraulic source module; the outlet of the output pipeline is connected to the oil inlet of the piston of the brake device on the wheel; and a switching valve is further arranged on the output pipeline between the control valve and the hydraulic fuse of one of the hydraulic control modules of the first brake control module and the second brake control module;

[0012] The hydraulic control module of the third brake control module includes: a third control valve and a third shut-off valve sequentially provided on the third output pipeline of the hydraulic source module, the third control valve being in communication with the switching valve;

[0013] The command input module is used to send a command signal corresponding to the braking command to the first brake module, the second brake module and the third vehicle module;

[0014] An anti-skid switch is used to input a control command to prevent the wheels from locking when each brake control module is operating;

[0015] A fault detection module, used to detect whether the first brake control module and the second brake control module are faulty;

[0016] The second brake control module is used to control the deceleration of the wheels when the first brake control module fails, and the third brake control module is used to control the deceleration of the wheels when both the first brake control module and the second brake control module fail.

[0017] Preferably, the anti-skid switch includes three gears, namely ON, OFF and AUTO. The anti-skid switch includes a first redundancy and a second redundancy. The first redundancy of the anti-skid switch is used to input a control instruction to prevent the wheels from locking when the first brake control module is working, and the second redundancy of the anti-skid switch is used to input a control instruction to prevent the wheels from locking when the second brake control module is working.

[0018] Preferably, the hydraulic source module includes:

[0019] a first hydraulic source, a second hydraulic source, and a third hydraulic source;

[0020] The input end of the third hydraulic source is connected to the first hydraulic source and the second hydraulic source respectively, and a one-way valve is provided between the third hydraulic source and the first hydraulic source, and between the third hydraulic source and the second hydraulic source. The one-way valve is only used for the oil of the first hydraulic source or the second hydraulic source to flow to the third hydraulic source;

[0021] Among them, the first hydraulic source is connected to the control valve of the first brake control module, the second hydraulic source is connected to the control valve of the second brake control module, the output end of the third hydraulic source is connected to the third cut-off valve, and the output end of the first hydraulic source is connected to the cut-off valve of the first brake control module, and the output end of the second hydraulic source is connected to the cut-off valve of the second brake control module.

[0022] Preferably, the command input module includes: four command sensors, the four command sensors are the main driver's left foot pedal command sensor, the main driver's right foot pedal command sensor, the co-driver's left foot pedal command sensor, and the co-driver's right foot pedal command sensor, each command sensor has three command signals; wherein, the three command signals are: a first command signal, a second command signal and a third command signal, the first command signal is the input of the brake command of the first brake control module, the second command signal is the input of the brake command of the second brake control module, and the third command signal is the input of the brake command of the third brake control module.

[0023] Preferably, the hydraulic control module of the first brake control module includes two first output pipes and four first hydraulic control channels, each first output pipe is connected to two first hydraulic control channels, and each first hydraulic control channel controls one wheel; the second brake control module includes a second output pipe and two second hydraulic control channels, each second output pipe is connected to two second hydraulic control channels, and each second hydraulic control channel controls two wheels.

[0024] A switching method for an aircraft redundant wheel brake control system of the present invention adopts the following technical solution, comprising: switching the brake system of the aircraft redundant wheel brake control system;

[0025] Get the initial state of the anti-skid switch, which includes four states: ON gear, OFF gear, AUTO gear and fault;

[0026] When the anti-skid switch is initially in the OFF position, the braking system switches from the first brake control module to the third brake control module to control wheel deceleration;

[0027] When the initial state of the anti-skid switch is in the ON position, the initial state of the anti-skid switch is in the AUTO position, or the initial state of the anti-skid switch is faulty, the first brake control module operates:

[0028] When one of the first hydraulic source, the braking function of the first brake control module, and the anti-skid function of the first brake control module fails, the first brake control module fails, and when the second hydraulic source is normal, the braking system switches from the first brake control module to the second brake control module to control wheel deceleration;

[0029] When the first brake control module fails and one of the second hydraulic source, the braking function of the second brake control module or the anti-skid function of the second brake control module fails, the first brake control module and the second brake control module fail at the same time. When the third cut-off valve is normal, the brake system is switched from the first brake control module to the third brake control module to control wheel deceleration.

[0030] Preferably, when the first hydraulic source fails and the second hydraulic source fails, the braking system switches from the first brake control module to the third brake control module to control wheel deceleration;

[0031] When the first hydraulic source is normal, and the braking function and the anti-skid function of the first brake control module are both normal, the first brake control module is normal and no switching is performed;

[0032] Under the premise of failure of the first brake control module, if the second hydraulic source fails and the third shut-off valve fails, the first brake control module controls the wheel deceleration of the brake system;

[0033] If the second hydraulic source is normal, and both the braking function and the anti-skid function of the second brake control module are normal, the second brake control module is normal and no switching is performed.

[0034] Preferably, after switching from the first brake control module to the second brake control module, the method further includes:

[0035] When the current state of the anti-skid switch changes compared to the initial state, the first brake control module only has a brake function failure, and in the brake function of the second brake control module: the second command signals of the driver's and co-driver's left pedal command sensors are normal; at the same time, in the brake function of the first brake control module: the first command signals of the driver's and co-driver's right pedal command sensors are normal;

[0036] Alternatively, in the braking function of the first brake control module: the first command signals of the left pedal command sensors of the driver and the co-driver are normal; and at the same time, in the braking function of the second brake control module: the second command signals of the right pedal command sensors of the driver and the co-driver are both normal;

[0037] At this time, the braking functions of the first brake control module and the second brake control module work simultaneously to control the deceleration of the wheels.

[0038] Preferably, when the state of the anti-skid switch has not changed and is still in the ON position determined initially, the second brake control module stops determining and controls the wheel to decelerate;

[0039] When the current state of the anti-skid switch does not change compared to the initial state and is still in the AUTO gear or fault state determined initially, it is determined whether the second brake control module is faulty. If the second brake control module is faulty, the third brake control module is switched from the second brake control module to control wheel deceleration;

[0040] If the state of the anti-skid switch has not changed and is still in the OFF position determined initially, the third brake control module controls the wheel to decelerate.

[0041] Preferably, if the third shut-off valve fails, the third brake control module switches to the first brake control module to control wheel deceleration; if the third shut-off valve is normal and the braking function of the third brake control module fails, the third brake control module switches to the first brake control module to control wheel deceleration; if the third shut-off valve is normal and the braking function of the third brake control module is normal, no switching is performed.

[0042] The beneficial effects of the present invention are:

[0043] 1. By setting an anti-skid switch and judging the working status of the three brake control modules after the system is powered on, and combining the hydraulic source, braking function and anti-skid function of each brake control module to determine whether the switching conditions are met, free switching between redundant brake control systems is achieved, thereby saving the time required for the pilot to manually switch to the third brake control module, reducing the aircraft's braking time, and ensuring the safety and reliability of the wheel brake system.

[0044] 2. Secondly, each brake control module of the present invention is provided with a controller, that is, when the brake control module only has a brake function failure, since in the brake function of the second brake control module: the second command signal of the left pedal command sensor of the main driver and the co-pilot is normal: at the same time, in the brake function of the first brake control module: the first command signal of the right pedal command sensor of the main driver and the co-pilot is normal, or, in the brake function of the first brake control module: the first command signal of the left pedal command sensor of the main driver and the co-pilot is normal: at the same time, in the brake function of the second brake control module: the second command signal of the right pedal command sensor of the main driver and the co-pilot is normal, the controller of the first brake control module controls the deceleration of the wheels on one side, and the controller of the second brake control module controls the deceleration of the wheels on the other side, thereby increasing the redundancy of the wheel brake system and further improving the safety and reliability of the wheel brake system. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0046] Figure 1 This is a structural block diagram of an aircraft redundant wheel brake control system according to the present invention;

[0047] Figure 2 This is a control block diagram of an aircraft redundant wheel brake control system according to the present invention;

[0048] Figure 3 This is a hydraulic control block diagram of an aircraft redundant wheel brake control system according to the present invention;

[0049] Figure 4 This is a flow chart of a switching method for an aircraft redundant wheel brake control system according to the present invention;

[0050] In the figure: 1. Anti-skid switch; 2. Command input module; 3. Second brake controller; 4. Second shut-off valve; 5. Second control valve; 6. Conversion valve; 7. Second hydraulic fuse; 8. Second hydraulic source; 9. Second one-way valve; 10. Third brake controller; 11. Third shut-off valve; 12. Third control valve; 13. First hydraulic source; 14. First one-way valve; 15. Third hydraulic source; 16. Wheel; 17. First hydraulic fuse; 18. First control valve; 19. First shut-off valve; 20. First brake controller. DETAILED DESCRIPTION

[0051] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0052] An embodiment of the present invention of a redundant aircraft wheel 16 brake control system is as follows Figure 1As shown, it includes: a first brake control module, a second brake control module, a third brake control module, a hydraulic source module, a command input module 2, an anti-skid switch 1 and a fault detection module; the first brake control module, the second brake control module and the third brake control module all include a brake controller and a hydraulic control module, wherein a hydraulic control module is connected to the brake device of each wheel 16; the output end of the hydraulic source module is connected to the three hydraulic control modules respectively through an output pipe; wherein the hydraulic control modules of the first brake control module and the second brake control module include: a plurality of hydraulic control channels are connected to each output pipe of the hydraulic source module, a cut-off valve is provided on each output pipe, and a control valve and a hydraulic fuse are provided in sequence on each hydraulic control channel, and the outlet of the hydraulic control channel is connected to the inlet of the piston of the brake device on the wheel. The oil port is connected, and a conversion valve 6 is also provided on the output pipeline between the control valve and the hydraulic fuse of one of the hydraulic control modules in the first brake control module and the second brake control module; the hydraulic control module of the third brake control module includes: a third control valve 12 and a third cut-off valve 11 arranged in sequence on the third output pipeline of the hydraulic source module, and the third control valve 12 is connected to the conversion valve 6; the instruction input module 2 is used to send instruction signals corresponding to the brake instructions to the first brake module, the second brake module and the third vehicle module; the anti-skid switch 1 is used to input control instructions to prevent the wheels 16 from locking when each brake control module is working; the second brake control module is used to control the deceleration of the wheels 16 when the first brake control module fails, and the third brake control module is used to control the deceleration of the wheels 16 when both the first brake control module and the second brake control module fail.

[0053] Among them, the fault detection module includes: a first detection unit and a second detection unit. The first detection unit is used to detect whether the hydraulic source, braking function, anti-skid function and anti-skid switch 1 of the first brake control module are faulty when they are working. If one of the hydraulic source, braking function, anti-skid function and anti-skid switch 1 of the first brake control module is faulty when they are working, the first brake control module is faulty; the second detection unit is used to detect whether the hydraulic source, braking function, anti-skid function and anti-skid switch 1 of the second brake control module are faulty when they are working. If one of the hydraulic source, braking function, anti-skid function and anti-skid switch 1 of the second brake control module is faulty when they are working, the second brake control module is faulty.

[0054] Specifically, the anti-skid switch 1 includes: an anti-skid switch 1 and four wheel speed sensors. The anti-skid switch 1 includes three gears, namely ON gear, OFF gear and AUTO gear. The anti-skid switch 1 includes a first redundancy and a second redundancy. The first redundancy of the anti-skid switch 1 is used to input a control instruction to prevent the wheel 16 from locking when the first brake control module is working. The second redundancy of the anti-skid switch 1 is used to input a control instruction to prevent the wheel 16 from locking when the second brake control module is working.

[0055] Specifically, such as Figure 2 As shown, since the aircraft has four wheels 16, the command input module 2 of this embodiment includes: four command sensors, the four command sensors are the main pilot left pedal command sensor, the main pilot right pedal command sensor, the co-pilot left pedal command sensor, and the co-pilot right pedal command sensor, each command sensor is correspondingly arranged on each wheel 16, and each command sensor is three command signals; among which the three command signals are: a first command signal, a second command signal and a third command signal, the first command signal is used to control the first brake control module, the second command signal is used to control the second brake control module, and the third command signal is used to control the third brake control module.

[0056] Specifically, such as Figure 1 As shown, the hydraulic source module of this embodiment includes: a first hydraulic source 13, a second hydraulic source 8 and a third hydraulic source 15; the input end of the third hydraulic source 15 is connected to the first hydraulic source 13 and the second hydraulic source 8 respectively, and a one-way valve is provided between the third hydraulic source 15 and the first hydraulic source 13, and between the third hydraulic source 15 and the second hydraulic source 8. The one-way valve is only used for the oil from the first hydraulic source 13 or the second hydraulic source 8 to flow to the third hydraulic source 15; wherein, the first hydraulic source 13 is connected to the control valve of the first brake control module, the second hydraulic source 8 is connected to the control valve of the second brake control module, the output end of the third hydraulic source 15 is connected to the third cut-off valve 11, and the output end of the first hydraulic source 13 is connected to the cut-off valve of the first brake control module, and the output end of the second hydraulic source 8 is connected to the cut-off valve of the second brake control module.

[0057] In the embodiment, the hydraulic control module of the first brake control module includes two first output pipes and four first hydraulic control channels, each first output pipe is connected to two first hydraulic control channels, and each first hydraulic control channel controls one wheel 16; the second brake control module includes one second output pipe and two second hydraulic control channels, each second output pipe is connected to two second hydraulic control channels, and each second hydraulic control channel controls two wheels 16; specifically, Figure 3As shown, taking the control of the two left wheels 16 of the aircraft as an example, the control of the two left wheels 16 of the first brake control module is controlled through two first hydraulic control channels. That is, the first hydraulic control module is energized by the first hydraulic source 13, and then the first shut-off valve 19 of the first output pipeline on the first hydraulic source 13 is opened, and the first control valve 18 on the first hydraulic control channel connected to the first left wheel 16 is controlled to open. Finally, the first hydraulic control channel outputs the oil to the piston in the brake device of the first left wheel 16 through the first hydraulic fuse 17. When the hydraulic control channel behind the first hydraulic fuse 17 ruptures, the first hydraulic fuse 17 is closed to prevent the oil from the hydraulic source from flowing out, and the brake device controls one left wheel 16 to decelerate and brake. Each second hydraulic control module of the second brake control module controls two hydraulic channels, that is, Figure 3 As shown, the second control pipeline of one of the second hydraulic control modules is connected to the first left wheel 16 and the second left wheel 16, thereby achieving simultaneous deceleration and braking control of the wheels 16 on the same side. When the third brake control module is working, as shown in FIG. Figure 3 As shown, this embodiment takes the conversion valve being arranged between the second control valve 5 and the second hydraulic fuse 7 of the second brake control module as an example. At this time, the output end of the hydraulic control module of the third brake control module and the first one-way valve 14 connecting the first hydraulic source 13 and the second one-way valve 9 connected to the second hydraulic source 8 are opened, that is, the first hydraulic source 13 and the second hydraulic source 8 supply oil to the third hydraulic source 15, and then the third shut-off valve 11 is opened, and the third control valve 12 is opened. The oil flows through the third shut-off valve 11, the third control valve 12, the conversion valve 6 in sequence, into the hydraulic output pipeline of the second hydraulic control module, and is output to the wheel 16 on the same side, so as to simultaneously control the deceleration braking of the wheel 16 on the same side.

[0058] The present invention also discloses a switching method of a redundant wheel 16 brake control system for an aircraft, specifically, switching the brake system of a redundant wheel 16 brake control system for an aircraft of the present invention; Figure 4As shown, this embodiment includes: obtaining the initial state of the anti-skid switch 1; the initial state is in the four states of ON gear, OFF gear, AUTO gear and fault; when the initial state of the anti-skid switch 1 is in the OFF gear, the brake system switches from the first brake control module to the third brake control module to control the deceleration of the wheel 16; when the initial state of the anti-skid switch 1 is in the ON gear, the initial state of the anti-skid switch 1 is in the AUTO gear or the initial state of the anti-skid switch 1 is in a fault, the first brake control module works (it should be noted that the present invention also assumes that the first brake control module works when the system is powered on): when the first brake control module works, when the first hydraulic source 13. If one of the braking function of the first brake control module or the anti-skid function of the first brake control module fails, the first brake control module fails, and when the second hydraulic source 8 is normal, the brake system switches from the first brake control module to the second brake control module to control the deceleration of the wheel 16; if the first brake control module fails, and one of the second hydraulic source 8, the braking function of the second brake control module or the anti-skid function of the second brake control module fails, the first brake control module and the second brake control module fail at the same time, and when the third cut-off valve 11 is normal, the brake system switches from the first brake control module to the third brake control module to control the deceleration of the wheel 16.

[0059] Among them, when the first hydraulic source 13 fails and the second hydraulic source 8 fails, the brake system is switched from the first brake control module to the third brake control module to control the deceleration of the wheel 16; when the first hydraulic source 13 is normal, and the braking function of the first brake control module and the anti-skid function of the first brake control module are both normal, the first brake control module is normal and no switching is performed; under the premise of the failure of the first brake control module, if the second hydraulic source 8 fails and the third cut-off valve 11 fails, the brake system is switched from the first brake control module to the third brake control module to control the deceleration of the wheel 16; if the second hydraulic source 8 is normal, and the braking function of the second brake control module and the anti-skid function of the second brake control module are both normal, the second brake control module is normal and no switching is performed.

[0060] Specifically, when the second brake control module starts to work, it also includes: when the current state of the anti-skid switch 1 changes compared to the initial state, the first brake control module only has a brake function failure, and in the brake function of the second brake control module: the second command signal of the left foot pedal command sensor of the main pilot and the co-pilot is normal: at the same time, in the brake function of the first brake control module: the first command signal of the right foot pedal command sensor of the main pilot and the co-pilot is normal; or, in the brake function of the first brake control module: the first command signal of the left foot pedal command sensor of the main pilot and the co-pilot is normal: at the same time, in the brake function of the second brake control module: the second command signal of the right foot pedal command sensor of the main pilot and the co-pilot is normal; at this time, the brake functions of the first brake control module and the second brake control module work simultaneously to control the deceleration of the wheel 16.

[0061] Among them, when the state of the anti-skid switch 1 has not changed and is still in the ON gear position initially judged, the second brake control module stops judging and the second brake control module controls the deceleration of the wheel 16; when the current state of the anti-skid switch 1 has not changed compared with the initial state and is still in the AUTO gear position or fault state initially judged, it is judged whether the second brake control module is faulty. If the second brake control module is faulty, the second brake control module switches to the third brake control module to control the deceleration of the wheel 16; if the state of the anti-skid switch 1 has not changed and is still in the OFF gear position initially judged.

[0062] Specifically, if the third shut-off valve 11 fails, the third brake control module switches to the first brake control module to control the deceleration of the wheel 16; if the third shut-off valve 11 is normal and the braking function of the third brake control module fails, the third brake control module switches to the first brake control module to control the deceleration of the wheel 16; if the third shut-off valve 11 is normal and the braking function of the third brake control module is normal, no switching is performed.

[0063] Specific working principle

[0064] When in use, the system is powered on, the initial state of the anti-skid switch 1 is the ON position, and the state of the anti-skid switch 1 is determined by the first brake controller 20 of the first brake control module. When the initial state of the anti-skid switch 1 is in the ON position, the first brake controller 20 works, and the second brake controller 3 is in a standby state, waiting for the instruction of the first brake controller 20, while the third brake controller 10 does not work; when the first brake controller 20 determines that the initial state of the anti-skid switch 1 is in the AUTO position, the first brake controller 20 of the first brake control module works, the second brake controller 3 and the third brake controller 10 are in a standby state, waiting for the instruction of the first brake controller 20; when the first brake controller 20 determines that the anti-skid switch 1 is faulty, the first brake controller 20 works, the second brake controller 3 and the third brake controller 10 are in a standby state, waiting for the instruction of the first brake controller 20, that is, when the initial state of the anti-skid switch 1 is in the ON gear, the initial state of the anti-skid switch 1 is in the AUTO gear or the initial state of the anti-skid switch 1 is faulty, the first brake control module works (it should be noted that the present invention also defaults to the system being powered on, the first Brake control module operation): When the first brake control module is operating, if one of the first hydraulic source 13, the braking function of the first brake control module, or the anti-skid function of the first brake control module fails, the first brake control module fails, and when the second hydraulic source 8 is normal, the brake system is switched from the first brake control module to the second brake control module to control the deceleration of the wheels 16; if the first brake control module fails and one of the second hydraulic source 8, the braking function of the second brake control module, or the anti-skid function of the second brake control module fails, the first brake control module and the second brake control module fail at the same time, and when the third shut-off valve 11 is normal, the brake system is switched from the first brake control module to the third brake control module to control the deceleration of the wheels 16; and when the first brake controller 20 of the first brake control module determines that the initial state of the anti-skid switch 1 is in the OFF position, the first brake controller 20 of the first brake control module and the second brake controller 3 of the second brake control module are both inoperative. At this time, the third brake controller 10 of the third brake control module is operative, and the control system of the third brake control module decelerates the aircraft wheels 16.

[0065] It should be noted that if the current state of the anti-skid switch 1 changes relative to the initial state during the switching process of a certain brake control module, the switching of the control module is re-judged; that is, when the first brake control module is working, until the aircraft stops: if the first brake controller 20 determines not to switch to the second brake controller 3, and the state of the anti-skid switch 1 has not changed, the first brake control module continues to work; if the first brake controller 20 determines not to switch to the second brake controller 3, and the state of the anti-skid switch 1 is switched to the OFF position, the first brake controller 20 switches to the third controller, and the third brake control module works; if the first brake controller 20 determines to switch to the second brake controller 3, and when the anti If the current state of the sliding switch 1 changes compared to the initial state, then the first brake control module only has a brake function failure, and in the brake function of the second brake control module: the second command signal of the left pedal command sensor of the main driver and the co-pilot is normal: at the same time, in the brake function of the first brake control module: the first command signal of the right pedal command sensor of the main driver and the co-pilot is normal; or, in the brake function of the first brake control module: the first command signal of the left pedal command sensor of the main driver and the co-pilot is normal: at the same time, in the brake function of the second brake control module: the second command signal of the right pedal command sensor of the main driver and the co-pilot is normal; at this time, the brake functions of the first brake control module and the second brake control module work simultaneously. , to control the deceleration of the wheel 16; if the first brake controller 20 determines to switch to the second brake controller 3, and the state of the anti-skid switch 1 has not changed and is still in the ON gear position initially determined, the second brake control module stops judging, and the second brake control module controls the deceleration of the wheel 16; if the first brake controller 20 determines to switch to the second brake controller 3, and the current state of the anti-skid switch 1 has not changed compared with the initial state and is still in the AUTO gear position or fault state initially determined, it is determined whether the second brake control module is faulty. If the second brake control module is faulty, the second brake control module switches to the third brake control module to control the deceleration of the wheel 16; if the anti-skid switch 1 is in the ON gear or When the AUTO position is switched to the OFF position, the third brake controller 10 is switched to regardless of the brake controller in use, and the third brake control module operates until the aircraft stops or the anti-skid switch 1 is detected to be switched again; if the anti-skid switch 1 is switched from the OFF position to the ON position or the AUTO position, the third brake controller 10 switches to the first brake controller 20, and the first brake control module operates, and the first brake controller 20 determines whether to switch to the second brake controller 3; if the anti-skid switch 1 is switched from the ON position to the AUTO position, the brake controller in use continues to switch between the first brake controller 20, the second brake controller 3, and the third brake controller 10 according to the above-mentioned fault state.If the anti-skid switch 1 is switched from the AUTO position to the ON position, the brake controller continues to switch between the first brake controller 20 and the second brake controller 3 according to the above-mentioned fault state judgment.

[0066] In summary, the embodiments of the present invention provide an aircraft redundant wheel brake control system and a switching method thereof.

[0067] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An aircraft redundant wheel brake control system, characterized in that: include: a first brake control module, a second brake control module, a third brake control module, and a hydraulic source module; The first brake control module, the second brake control module and the third brake control module each include a brake controller and a hydraulic control module, wherein a hydraulic control module is connected to the brake device of each wheel; A hydraulic source module, the output end of which is connected to the three hydraulic control modules through output pipelines; The hydraulic control modules of the first brake control module and the second brake control module include: a plurality of hydraulic control channels are connected to each output pipeline of the hydraulic source module, a cut-off valve is provided on each output pipeline, a control valve and a hydraulic fuse are provided in sequence on each hydraulic control channel, the outlet of the hydraulic control channel is communicated with the oil inlet of the piston of the brake device on the wheel, and a conversion valve is further provided on the output pipeline between the control valve and the hydraulic fuse of one of the hydraulic control modules in the first brake control module and the second brake control module; the hydraulic control module of the first brake control module includes two first output pipelines and four first hydraulic control channels, each first output pipeline is connected to two first hydraulic control channels, and each first hydraulic control channel controls one wheel correspondingly; the second brake control module includes one second output pipeline and two second hydraulic control channels, each second output pipeline is connected to two second hydraulic control channels, and each second hydraulic control channel controls two wheels correspondingly; The hydraulic control module of the third brake control module includes: a third control valve and a third shut-off valve sequentially provided on the third output pipeline of the hydraulic source module, wherein the third control valve is in communication with the switching valve; The command input module is used to send a command signal corresponding to the braking command to the first brake module, the second brake module and the third vehicle module; an anti-skid switch for inputting a control instruction for preventing wheel lock when each brake control module is operating; the anti-skid switch includes three positions: an ON position, an OFF position, and an AUTO position; the anti-skid switch includes a first margin and a second margin, the first margin of the anti-skid switch being used to input a control instruction for preventing wheel lock when the first brake control module is operating, and the second margin of the anti-skid switch being used to input a control instruction for preventing wheel lock when the second brake control module is operating; A fault detection module, used to detect whether the first brake control module and the second brake control module are faulty; The second brake control module is used to control the deceleration of the aircraft wheel when the first brake control module fails, and the third brake control module is used to control the deceleration of the aircraft wheel when both the first brake control module and the second brake control module fail. The hydraulic source module includes: a first hydraulic source, a second hydraulic source, and a third hydraulic source; The input end of the third hydraulic source is connected to the first hydraulic source and the second hydraulic source respectively, and a one-way valve is provided between the third hydraulic source and the first hydraulic source, and between the third hydraulic source and the second hydraulic source. The one-way valve is only used for the oil of the first hydraulic source or the second hydraulic source to flow to the third hydraulic source; Among them, the first hydraulic source is connected to the control valve of the first brake control module, the second hydraulic source is connected to the control valve of the second brake control module, the output end of the third hydraulic source is connected to the third cut-off valve, and the output end of the first hydraulic source is connected to the cut-off valve of the first brake control module, and the output end of the second hydraulic source is connected to the cut-off valve of the second brake control module.

2. The aircraft redundant wheel brake control system according to claim 1, characterized in that: The command input module includes: four command sensors, the four command sensors are the main driver's left foot pedal command sensor, the main driver's right foot pedal command sensor, the co-pilot's left foot pedal command sensor, and the co-pilot's right foot pedal command sensor, each command sensor has three command signals; among them, the three command signals are: a first command signal, a second command signal and a third command signal, the first command signal is the input of the brake command of the first brake control module, the second command signal is the input of the brake command of the second brake control module, and the third command signal is the input of the brake command of the third brake control module.

3. A method for switching an aircraft redundant wheel brake control system, characterized in that: Switching the brake system of the aircraft redundant wheel brake control system according to any one of claims 1-2; Get the initial state of the anti-skid switch, which includes four states: ON gear, OFF gear, AUTO gear and fault; When the anti-skid switch is initially in the OFF position, the braking system switches from the first brake control module to the third brake control module to control wheel deceleration; When the initial state of the anti-skid switch is in the ON position, the initial state of the anti-skid switch is in the AUTO position, or the initial state of the anti-skid switch is faulty, the first brake control module operates: When one of the first hydraulic source, the braking function of the first brake control module, and the anti-skid function of the first brake control module fails, the first brake control module fails, and when the second hydraulic source is normal, the braking system switches from the first brake control module to the second brake control module to control wheel deceleration; When the first brake control module fails and one of the second hydraulic source, the braking function of the second brake control module or the anti-skid function of the second brake control module fails, the first brake control module and the second brake control module fail at the same time. When the third cut-off valve is normal, the brake system is switched from the first brake control module to the third brake control module to control wheel deceleration.

4. The switching method of an aircraft redundant wheel brake control system according to claim 3, characterized in that: When the first hydraulic source fails and the second hydraulic source fails, the braking system switches from the first brake control module to the third brake control module to control wheel deceleration; When the first hydraulic source is normal, and the braking function and the anti-skid function of the first brake control module are both normal, the first brake control module is normal and no switching is performed; Under the premise of failure of the first brake control module, if the second hydraulic source fails and the third shut-off valve fails, the first brake control module controls the wheel deceleration of the brake system; If the second hydraulic source is normal, and both the braking function and the anti-skid function of the second brake control module are normal, the second brake control module is normal and no switching is performed.

5. The switching method of an aircraft redundant wheel brake control system according to claim 3, characterized in that: After switching from the first brake control module to the second brake control module, the method further includes: When the current state of the anti-skid switch changes compared to the initial state, the first brake control module only has a brake function failure, and in the brake function of the second brake control module: the second command signals of the driver's and co-driver's left pedal command sensors are normal; at the same time, in the brake function of the first brake control module: the first command signals of the driver's and co-driver's right pedal command sensors are normal; Alternatively, in the braking function of the first brake control module: the first command signals of the left pedal command sensors of the driver and the co-driver are normal; and at the same time, in the braking function of the second brake control module: the second command signals of the right pedal command sensors of the driver and the co-driver are both normal; At this time, the braking functions of the first brake control module and the second brake control module work simultaneously to control the deceleration of the wheels.

6. The switching method of an aircraft redundant wheel brake control system according to claim 5, characterized in that: When the state of the anti-skid switch does not change and is still in the ON position determined initially, the second brake control module stops determining and controls the wheel to decelerate. When the current state of the anti-skid switch does not change compared to the initial state and is still in the AUTO gear or fault state determined initially, it is determined whether the second brake control module is faulty. If the second brake control module is faulty, the third brake control module is switched from the second brake control module to control wheel deceleration; If the state of the anti-skid switch has not changed and is still in the OFF position determined initially, the third brake control module controls the wheel to decelerate.

7. The switching method of an aircraft redundant wheel brake control system according to claim 3, characterized in that: If the third shut-off valve fails, the third brake control module switches to the first brake control module to control wheel deceleration; If the third cut-off valve is normal and the brake function of the third brake control module fails, the third brake control module switches to the first brake control module to control the wheel deceleration; If the third shut-off valve is normal and the braking function of the third brake control module is normal, no switching is performed.

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