Aircraft Braking Control Method, System and Aircraft

Abstract

The present invention provides an aircraft braking control method, system and aircraft. The method includes: obtaining a braking control command value according to the obtained aircraft speed, wheel speed and a preset target slip ratio; obtaining a correction command value according to the obtained actual braking pressure value; judging whether there is a pressure jam according to the actual braking pressure value and the braking control command value, and outputting a pressure jam command value when there is a pressure jam; and outputting a target braking control command value based on the braking control command value, the correction command value and the pressure jam command value. The present invention can achieve a good anti-skid braking control effect, avoid releasing too much pressure at the same time, obtain a high braking efficiency, and effectively improve the braking performance of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft brake control, and particularly to an aircraft brake control method, system and aircraft capable of coping with pressure jamming. Background Art

[0002] The core of aircraft brake control is anti-skid brake control, which can play important roles such as regulating brake pressure to prevent wheel skidding, locking and reducing braking distance, ensuring safe, reliable and efficient aircraft braking deceleration. And the aircraft anti-skid brake system is a complex non-linear system with uncertainty, and there are many non-linear factors in the system, which directly affect the performance of anti-skid braking.

[0003] In brake anti-skid control, pressure jamming will occur. Regardless of the control command, the actual output of brake pressure is jammed within a certain range. The reason may be a control valve failure or pollutants in the pipeline. For an aircraft, due to the high failure rate of brake equipment, long pressure pipelines and large actuators, if the pressure jamming cannot be handled in time, it will cause safety consequences such as tire skidding or even locking. Summary of the Invention

[0004] The present invention provides an aircraft brake control method, system and aircraft, which are used to solve the safety problem that tire skidding or even locking will occur due to the failure to handle pressure jamming in time in the prior art.

[0005] In a first aspect, the present invention provides an aircraft brake control method, and the method includes:

[0006] Obtaining a brake control command value according to the obtained aircraft speed, wheel speed and a preset target slip ratio;

[0007] Obtaining a correction command value according to the obtained actual brake pressure value;

[0008] Judging whether there is pressure jamming according to the actual brake pressure value and the brake control command value, and outputting a pressure jamming command value when there is pressure jamming;

[0009] Outputting a target brake control command value based on the brake control command value, the correction command value and the pressure jamming command value.

[0010] In an embodiment of the present invention, the step of obtaining a brake control command value according to the obtained aircraft speed, wheel speed and a preset target slip ratio includes:

[0011] Obtaining the reference speed of the previous cycle;

[0012] Comparing the magnitudes of the aircraft speed and the reference speed of the previous cycle, and taking the one with the larger speed value as the reference speed of the current cycle;

[0013] Subtract the wheel speed from the reference speed of the current cycle, take the absolute value, and divide by the reference speed of the current cycle to obtain the actual slip ratio;

[0014] Calculate the brake control command value according to the difference between the preset target slip ratio and the actual slip ratio, where the brake control command value is equal to the sum of the deviation term and the integral term of the difference.

[0015] In an embodiment of the present invention, the step of obtaining the correction command value according to the obtained actual brake pressure value includes:

[0016] Obtain the target brake control command value of the previous cycle;

[0017] Multiply the difference between the target brake control command value of the previous cycle and the actual brake pressure value by a preset proportionality coefficient to obtain the correction command value.

[0018] In an embodiment of the present invention, the step of judging whether there is pressure jamming according to the actual brake pressure value and the brake control command value, and outputting a pressure jamming command value when there is pressure jamming includes:

[0019] Subtract the actual brake pressure value from the brake control command value, take the absolute value, and divide by the brake control command value to obtain the offset ratio;

[0020] If the offset ratio is greater than a first preset threshold and exceeds a preset duration, it is determined that there is pressure jamming and the pressure jamming command value is output.

[0021] In an embodiment of the present invention, the step of outputting a target brake control command value based on the brake control command value, the correction command value, and the pressure jamming command value includes:

[0022] If there is no pressure jamming, the target brake control command value is equal to the sum of the brake control command value and the correction command value;

[0023] If there is pressure jamming, the target brake control command value is equal to the pressure jamming command value.

[0024] In an embodiment of the present invention, the step of outputting a target brake control command value based on the brake control command value, the correction command value, and the pressure jamming command value further includes:

[0025] Record the number of times or the duration of outputting the pressure jamming command value;

[0026] Judge whether the number of times or the duration exceeds a second preset threshold;

[0027] If it exceeds, the pressure jamming command value is no longer output, and the target brake control command value is updated to be equal to the sum of the brake control command value and the correction command value.

[0028] In an embodiment of the present invention, the pressure jamming command value is a set of command values, which includes a maximum command value and a minimum command value. The step of outputting the pressure jamming command value when there is pressure jamming includes:

[0029] Cyclically output the maximum command value and the minimum command value and repeat a preset number of times.

[0030] In a second aspect, the present invention further provides an aircraft brake control system, which includes:

[0031] A brake control command value calculation module, configured to obtain a brake control command value according to the acquired aircraft speed, wheel speed, and a preset target slip ratio;

[0032] A correction command value calculation module, configured to obtain a correction command value according to the acquired actual brake pressure value;

[0033] A pressure jamming judgment module, configured to judge whether there is pressure jamming according to the actual brake pressure value and the brake control command value, and output a pressure jamming command value when there is pressure jamming;

[0034] A target brake command value calculation module, configured to output a target brake control command value based on the brake control command value, the correction command value, and the pressure jamming command value.

[0035] In a third aspect, the present invention further provides an aircraft, which is used to execute the aircraft brake control method according to any item in the first aspect.

[0036] In an embodiment of the present invention, the aircraft includes a wheel speed sensor, an aircraft speed measurement module, a brake control module, a brake control device, a brake actuator, and a brake pressure sensor;

[0037] Among them, the wheel speed sensor is used to measure the wheel speed of the aircraft, the aircraft speed measurement module is used to measure the aircraft speed, the brake pressure sensor is used to measure the actual brake pressure value output by the brake control device to the brake actuator, the brake control module is used to execute the aircraft brake control method according to the received aircraft speed, wheel speed, and actual brake pressure value and output a brake control command; the brake control device is used to output a brake pressure according to the brake control command; the brake actuator is used to receive the brake pressure and act on the aircraft wheels.

[0038] The aircraft braking control method, system and aircraft provided by the present invention correct the braking control command value by introducing the actual braking pressure. At the same time, it also judges whether there is pressure jamming during the braking process, and outputs the target braking control command value according to the presence or absence of pressure jamming and the corrected command value, which can achieve a good anti-skid braking control effect, avoid releasing too much pressure, obtain a high braking efficiency, and effectively improve the braking performance of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0040] Figure 1 is a block diagram of the aircraft provided by the present invention;

[0041] Figure 2 is a schematic flow chart of the aircraft braking control method provided by the present invention;

[0042] Figure 3 is a schematic flow chart of the calculation of the braking control command value provided by the present invention;

[0043] Figure 4 is a schematic flow chart of the calculation of the corrected command value provided by the present invention;

[0044] Figure 5 is a schematic flow chart of judging pressure jamming provided by the present invention;

[0045] Figure 6 is a schematic flow chart of the calculation of the target braking command value provided by the present invention;

[0046] Figure 7 is a block diagram of the aircraft braking control system provided by the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0047] In order to make the objectives, technical solutions and advantages of the present invention clearer, the following will clearly and completely describe the technical solutions in the present invention with reference to the drawings in the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art without creative efforts based on the embodiments in the present invention belong to the scope of protection of the present invention.

[0048] In the description and claims of the present invention and in the above-mentioned drawings, terms such as "first", "second", etc. are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged under appropriate circumstances so that the embodiments described herein can be implemented in an order different from that shown or described herein.

[0049] The aircraft anti-skid brake control algorithm is the core of brake control and plays an important role in regulating the brake pressure to prevent tire skidding, locking, and reducing the braking distance, ensuring safe, reliable, and efficient braking deceleration of the aircraft.

[0050] To solve the safety problem in the prior art that pressure jamming cannot be processed in time, which may cause tire skidding or even locking, the present invention provides an aircraft brake control method, system, and aircraft. By introducing the actual brake pressure to correct the brake control command value, and at the same time determining whether there is pressure jamming during the braking process, and outputting the target brake control command value according to the presence or absence of pressure jamming and the corrected command value, a better anti-skid brake control effect can be achieved, while avoiding excessive pressure release, obtaining a higher braking efficiency, and effectively improving the braking performance of the aircraft.

[0051] The following Figure 1-7 describes the aircraft brake control method, system, and aircraft of the present invention.

[0052] Please refer to Figure 1 , Figure 1 which is a block diagram of the modules of the aircraft provided by the present invention. An aircraft includes a wheel speed sensor 101, an aircraft speed measurement module 102, a brake control module 103, a brake pressure sensor 104, a brake control device 105, and a brake actuator 106.

[0053] Exemplarily, the wheel speed sensor 101 is connected to the brake control module 103 and is installed at the wheel axle of the landing gear to measure the rolling speed of the aircraft wheels, i.e., the wheel speed.

[0054] Exemplarily, the aircraft speed measurement module 102 is connected to the brake control module 103 and is used to measure the aircraft speed. The aircraft speed measurement module 102 can adopt an aircraft inertial navigation system.

[0055] Exemplarily, the brake control module 103 is respectively connected to the wheel speed sensor 101, the aircraft speed measurement module 102, the brake pressure sensor 104, and the brake control device 105, and is used to execute the aircraft brake control method of the present invention to output a brake control command according to the aircraft speed measured by the aircraft speed measurement module 102, the wheel speed measured by the wheel speed sensor 101, and the actual brake pressure value measured by the brake pressure sensor 104.

[0056] Exemplarily, the brake pressure sensor 104 is located at the output end of the brake control device 105 and is used to measure the actual brake pressure value output from the brake control device 15 to the brake actuator 106.

[0057] Exemplarily, the brake control device 105 is configured to output a brake pressure to the brake actuator 106 according to the brake control instruction output by the brake control module 103.

[0058] Exemplarily, the brake actuator 106 is configured to receive the brake pressure output by the brake control device 105, generate a braking torque, and then apply it to the aircraft wheels to decelerate the aircraft wheels, thereby playing a role in decelerating the aircraft.

[0059] Based on the above aircraft architecture, the aircraft brake control method and system provided by the present invention will be specifically described below.

[0060] Please refer to Figure 2 , Figure 2 which is a schematic flow chart of the aircraft brake control method provided by the present invention. An aircraft brake control method, the method comprising:

[0061] Step 210, obtaining a brake control instruction value according to the acquired aircraft speed, wheel speed, and a preset target slip ratio.

[0062] Step 220, obtaining a correction instruction value according to the acquired actual brake pressure value.

[0063] Step 230, judging whether there is pressure jamming according to the actual brake pressure value and the brake control instruction value, and outputting a pressure jamming instruction value when there is pressure jamming.

[0064] Step 240, outputting a target brake control instruction value based on the brake control instruction value, the correction instruction value, and the pressure jamming instruction 5 value.

[0065] It should be noted that the aircraft brake control method of the present invention can be executed periodically, that is, the above steps 210 to 240 are executed once in each period, completing the entire calculation process from input to output, and finally outputting a target brake control instruction value. The time of each period can be set according to actual needs, for example, each period is set to 5 ms.

[0066] The following takes a certain period as an example to specifically describe the above steps 210 to 240.

[0067] Please refer to Figure 3 , Figure 3 which is a schematic flow chart of the calculation of the brake control instruction value provided by the present invention. In the above step 210, the step of obtaining a brake control instruction value according to the acquired aircraft speed, wheel speed, and a preset target slip ratio includes:

[0068] Step 2101: Obtain the reference speed of the previous cycle.

[0069] Step 2102: Compare the aircraft speed with the reference speed of the previous cycle, and take the larger speed value as the reference speed of the current cycle.

[0070] Among them, the aircraft speed can be measured by the Figure 1 aircraft speed measurement module 102 therein. The reference speed is a reference speed for anti-skid braking control of the aircraft and can be calculated based on aircraft motion parameters. The aircraft motion parameters are, for example, the aircraft pitch angle, wheel speed, etc.

[0071] Step 2103: Subtract the wheel speed from the reference speed of the current cycle, take the absolute value, and then divide by the reference speed of the current cycle to obtain the actual slip ratio.

[0072] Exemplarily, the actual slip ratio H1 = |V 0- - V1| / V0, where V0 represents the reference speed of the current cycle and V1 represents the wheel speed.

[0073] Step 2104: Calculate the brake control command value according to the difference between the preset target slip ratio and the actual slip ratio, where the brake control command value is equal to the sum of the deviation term

[0074] and the integral term of the difference.

[0075] Exemplarily, assume that the preset target slip ratio is H0. For example, the preset target slip ratio is 0.15, and the difference E = H0 - H1. Then the brake control command value Ca is equal to the sum of the deviation term and the integral term of the difference E, that is

[0076] Ca = K p *E + K i *∫E;

[0077] Among them, K p and K i are preset parameters and can be constants.

[0078] Please refer to Figure 4 , Figure 4 which is a schematic flowchart of the calculation of the correction command value provided by the present invention. In the above step 220, the steps of obtaining the correction command value according to the obtained actual brake pressure value include:

[0079] Step 2201: Obtain the target brake control command value of the previous cycle.

[0080] It should be noted that the target brake control command value in the previous cycle refers to the target brake control command value finally output when the aircraft brake control method of the present invention was last run. If there is no target brake control command value in the previous cycle, for example, if the current cycle is the first time to run the aircraft brake control method of the present invention, the target brake control command value in the previous cycle is defaulted to 0.

[0081] Step 2202: Multiply the difference between the target brake control command value in the previous cycle and the actual brake pressure value by a preset proportionality coefficient to obtain the correction command value.

[0082] Exemplarily, through Figure 1 the shown brake pressure sensor 104, the actual brake pressure value P in the current cycle can be measured i , the target brake control command value in the previous cycle is C i-1 , then the difference S is expressed as:

[0083] S = (C i-1 - P i ).

[0084] Then, the correction command value Cb = S * k, where k represents the preset proportionality coefficient.

[0085] Please refer to Figure 5 , Figure 5 which is a schematic flow diagram of judging pressure jamming provided by the present invention. In the above step 230, the step of judging whether there is pressure jamming according to the actual brake pressure value and the brake control command value and outputting a pressure jamming command value when there is pressure jamming includes:

[0086] Step 2301: Subtract the actual brake pressure value from the brake control command value, take the absolute value, and then divide by the brake control command value to obtain an offset ratio.

[0087] Exemplarily, the offset ratio M = S / Ca, where S = |C i-1 - P i |, P i represents the actual brake pressure value in the current cycle, and Ca represents the brake pressure command value.

[0088] Step 2302: If the offset ratio is greater than a first preset threshold and exceeds a preset duration, it is determined that there is pressure jamming and a pressure jamming command value is output.

[0089] For example, if the offset ratio M is greater than 40% and exceeds 0.2S, it is determined that there is pressure jamming and a pressure jamming command value Cd is output.

[0090] Step 2303: If the offset ratio is less than or greater than the first preset threshold and exceeds the preset duration, it is determined that there is no pressure jamming.

[0091] Exemplarily, the pressure jamming command value Cd is a set of command values, which includes a maximum command value Cd1 and a minimum command value Cd2. In the step 2302, the step of outputting the punching pressure command value 0 includes: circularly outputting the maximum command value and the minimum command value and repeating a preset number of times.

[0092] For example, Cd1 represents the maximum command value, Cd2 represents the minimum command value 0, and Cd1 and Cd2 are circularly output and repeated 5 times. The purpose of outputting the pressure jamming command value Cd is to open the pressure output element such as the brake control valve to the maximum and release it to the minimum to remove the pressure jamming.

[0093] 5 Please refer to Figure 6 , Figure 6 is the flow diagram of the target brake command value calculation provided by the present invention

[0094] In the above step 240, the step of outputting the target brake control command value based on the brake control command value, the correction command value, and the pressure jamming command value includes:

[0095] Step 2401, calculate the target brake command value.

[0096] Step 2402, if there is no pressure jamming, the target brake control command value is equal to the sum of the brake control command value and the correction command value.

[0097] Exemplarily, if it is determined through the above Figure 5 that there is no pressure jamming, the final target brake control command value C i = Ca + Cb, where Ca represents the brake control command value and Cb represents the correction command value.

[0098] Step 2403, if there is pressure jamming, the target brake control command value is equal to the pressure jamming command value.

[0099] Exemplarily, if it is determined through the above Figure 5 that there is pressure jamming, the target brake control command value C of the current cycle i = Cd, where Cd represents the pressure jamming command value.

[0100] Step 2404, record the number of times or the duration of outputting the pressure jamming command value.

[0101] Step 2405, judge whether the number of times or the duration exceeds a second preset threshold.

[0102] Step 2406, if it exceeds, no longer output the pressure jamming command value and update the target brake control command value to be equal to the sum of the brake control command value and the correction command value.

[0103] Exemplarily, if the number of times or the duration of the output pressure jamming command value exceeds a second preset threshold, for example, if the number of times of outputting the pressure jamming command value exceeds 5 times, then the above step 2302 no longer outputs the pressure jamming command value Cd and updates the target brake control command value C of the current cycle to: C i is updated to: C i = Ca + Cb.

[0104] If it does not exceed, return to the above step 2403.

[0105] In summary, the aircraft brake control method of the present invention corrects the brake control command value by introducing the actual brake pressure, and at the same time judges whether there is pressure jamming during the braking process, and outputs the target brake control command value according to the presence or absence of pressure jamming and the corrected command value, which can achieve a good anti-skid brake control effect, avoid releasing too much pressure at the same time, obtain a high braking efficiency, and effectively improve the braking performance of the aircraft.

[0106] Next, the aircraft brake control system provided by the present invention will be described. The aircraft brake control system described below can be mutually corresponding and referred to the aircraft brake control method described above.

[0107] Please refer to Figure 7 , Figure 7 which is a block diagram of the aircraft brake control system provided by the present invention. An aircraft brake control system 700 includes a brake control command value calculation module 710, a correction command value calculation module 720, a pressure jamming judgment module 730, and a target brake command value calculation module 740.

[0108] Exemplarily, the brake control command value calculation module 710 is used to:

[0109] Obtain the brake control command value according to the obtained aircraft speed, wheel speed, and a preset target slip ratio.

[0110] Exemplarily, the correction command value calculation module 720 is used to:

[0111] Obtain the correction command value according to the obtained actual brake pressure value.

[0112] Exemplarily, the pressure jamming judgment module 730 is used to:

[0113] Judge whether there is pressure jamming according to the actual brake pressure value and the brake control command value, and output a pressure jamming command value when there is pressure jamming.

[0114] Exemplarily, the target brake command value calculation module 740 is used to:

[0115] Output a target brake control command value based on the brake control command value, the correction command value, and the pressure jam command value.

[0116] Exemplarily, the brake control command value calculation module 710 is further configured to:

[0117] Obtain the reference speed of the previous cycle;

[0118] Compare the magnitudes of the aircraft speed and the reference speed of the previous cycle, and use the one with the larger speed value as the reference speed of the current cycle;

[0119] Subtract the wheel speed from the reference speed of the current cycle, take the absolute value, and divide by the reference speed of the current cycle to obtain the actual slip ratio;

[0120] Calculate the brake control command value according to the difference between the preset target slip ratio and the actual slip ratio, where the brake control command value is equal to the sum of the deviation term and the integral term of the difference.

[0121] Exemplarily, the correction command value calculation module 720 is further configured to:

[0122] Obtain the target brake control command value of the previous cycle;

[0123] Multiply the difference between the target brake control command value of the previous cycle and the actual brake pressure value by a preset proportionality coefficient to obtain the correction command value.

[0124] Exemplarily, the pressure jam determination module 730 is further configured to:

[0125] Subtract the actual brake pressure value from the brake control command value, take the absolute value, and divide by the brake control command value to obtain the offset ratio;

[0126] If the offset ratio is greater than the first preset threshold and exceeds the preset duration, determine that there is a pressure jam and output the pressure jam command value.

[0127] Exemplarily, the target brake command value calculation module 740 is further configured to:

[0128] If there is no pressure jam, the target brake control command value is equal to the sum of the brake control command value and the correction command value;

[0129] If there is a pressure jam, the target brake control command value is equal to the pressure jam command value.

[0130] Exemplarily, the target brake command value calculation module 740 is further configured to:

[0131] Record the number of times or the duration of outputting the pressure jam command value;

[0132] Determine whether the number of times or the duration exceeds a second preset threshold;

[0133] If it exceeds, stop outputting the pressure jam instruction value and update the target brake control instruction value to be equal to the sum of the brake control instruction value and the correction instruction value.

[0134] Exemplarily, the target brake instruction value calculation module 740 is further configured to:

[0135] Circularly output the maximum instruction value and the minimum instruction value and repeat a preset number of times, where the pressure jam instruction value is a set of instruction values, which includes the maximum instruction value and the minimum instruction value.

[0136] It should be noted here that the above aircraft brake control system provided by the embodiments of the present invention can implement all the method steps implemented by the above method embodiments, and can achieve the same technical effects. The same parts and beneficial effects as those in the method embodiments will not be specifically described in this embodiment.

[0137] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aircraft brake control method, characterized in that, The method includes: Obtaining a brake control command value based on the acquired aircraft speed, wheel speed, and a preset target slip ratio; Obtaining a correction command value based on the acquired actual brake pressure value; Judging whether there is pressure jamming according to the actual brake pressure value and the brake control command value, and outputting a pressure jamming command value when there is pressure jamming. Specifically, it includes: subtracting the actual brake pressure value from the brake control command value, taking the absolute value, and then dividing by the brake control command value to obtain an offset ratio; if the offset ratio is greater than a first preset threshold and exceeds a preset duration, it is determined that there is pressure jamming and the pressure jamming command value is output; Outputting a target brake control command value based on the brake control command value, the correction command value, and the pressure jamming command value.

2. The aircraft braking control method according to claim 1, characterized in that The step of obtaining the brake control command value based on the acquired aircraft speed, wheel speed, and preset target slip ratio includes: Obtaining the reference speed of the previous cycle; Comparing the magnitudes of the aircraft speed and the reference speed of the previous cycle, and taking the larger speed value as the reference speed of the current cycle; Subtracting the wheel speed from the reference speed of the current cycle, taking the absolute value, and then dividing by the reference speed of the current cycle to obtain the actual slip ratio; Calculating the brake control command value according to the difference between the preset target slip ratio and the actual slip ratio, where the brake control command value is equal to the sum of the deviation term and the integral term of the difference.

3. The aircraft braking control method according to claim 2, characterized in that The step of obtaining the correction command value based on the acquired actual brake pressure value includes: Obtaining the target brake control command value of the previous cycle; Multiplying the difference between the target brake control command value of the previous cycle and the actual brake pressure value by a preset proportional coefficient to obtain the correction command value.

4. The aircraft brake control method according to claim 1, wherein The step of outputting the target brake control command value based on the brake control command value, the correction command value, and the pressure jamming command value includes: If there is no pressure jamming, the target brake control command value is equal to the sum of the brake control command value and the correction command value; If there is pressure jamming, the target brake control command value is equal to the pressure jamming command value.

5. The aircraft brake control method according to claim 4, characterized in that The step of outputting the target brake control command value based on the brake control command value, the correction command value, and the pressure jamming command value further includes: Recording the number of times or the duration of outputting the pressure jamming command value; Judging whether the number of times or the duration exceeds a second preset threshold; If it exceeds, the pressure jamming command value is no longer output, and the target brake control command value is updated to be equal to the sum of the brake control command value and the correction command value.

6. The aircraft braking control method according to claim 1, wherein The pressure jamming command value is a set of command values, which includes a maximum command value and a minimum command value. The step of outputting the pressure jamming command value when there is pressure jamming includes: Cyclically outputting the maximum command value and the minimum command value and repeating a preset number of times.

7. An aircraft brake control system, characterized in that, The system includes: A brake control command value calculation module, configured to obtain a brake control command value according to the acquired aircraft speed, wheel speed, and a preset target slip ratio; A correction command value calculation module, configured to obtain a correction command value according to the acquired actual brake pressure value; A pressure jamming judgment module, configured to judge whether there is pressure jamming according to the actual brake pressure value and the brake control command value, and output a pressure jamming command value when there is pressure jamming. Specifically, it includes: subtracting the actual brake pressure value from the brake control command value, taking the absolute value, and then dividing by the brake control command value to obtain an offset ratio; if the offset ratio is greater than a first preset threshold and exceeds a preset duration, it is determined that there is pressure jamming and the pressure jamming command value is output; A target brake command value calculation module, configured to output a target brake control command value based on the brake control command value, the correction command value, and the pressure jamming command value.

8. An aircraft, characterized in that, The aircraft is used to execute the aircraft brake control method according to any one of claims 1 to 6.

9. The aircraft according to claim 8, characterized in that, The aircraft includes a wheel speed sensor, an aircraft speed measurement module, a brake control module, a brake control device, a brake actuator, and a brake pressure sensor; Wherein, the wheel speed sensor is used to measure the wheel speed of the aircraft, the aircraft speed measurement module is used to measure the aircraft speed, the brake pressure sensor is used to measure the actual brake pressure value output by the brake control device to the brake actuator, and the brake control module is used to execute the aircraft brake control method according to the received aircraft speed, wheel speed, and actual brake pressure value and output a brake control command; the brake control device is used to output a brake pressure according to the brake control command; the brake actuator is used to receive the brake pressure and act on the aircraft wheels.

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