Indication control method and system for airplane wheel brake system without antiskid brake

Abstract

The invention belongs to the technical field of aircraft brake systems, and discloses an indication control method for an aircraft wheel brake system without an anti-skid brake, which is used when an anti-skid system of an aircraft fails, and is used for prompting a pilot according to the ground speed of the aircraft and the brake pressure of all aircraft wheels, if the ground speed of the aircraft does not exceed the speed threshold value, a non-warning prompt is output to a pilot; meanwhile, brake pressure collection is carried out on all airplane wheels of the airplane, and when the brake pressure of any airplane wheel exceeds a threshold value, a warning prompt or a serious warning prompt is output to a pilot. Through the design, the operation safety and the system reliability of the aircraft brake system in a non-antiskid state can be effectively protected, and misjudgment and operation risks of a pilot caused by antiskid function failure or brake faults are avoided.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aircraft brake systems, and relates to a method for indicating pilots when an anti-skid brake system of an aircraft fails, in particular to a method and system for indicating and controlling aircraft wheel brake systems without anti-skid braking. BACKGROUND

[0002] Aircraft wheel brake systems are usually equipped with anti-skid braking functions to provide effective braking during ground taxiing, landing, and the like. However, when the anti-skid braking function fails or the system enters an anti-skid-free mode, some aircraft wheel brake systems usually lack clear and intuitive state indications, and the visualization of key data is not obvious, which makes it difficult for pilots to timely perceive changes in brake states, causing key data to exceed threshold ranges, and leading pilots to make incorrect judgments or misoperations, thereby seriously affecting flight safety. In addition, even if some aircraft wheel brake systems have fault indication functions, they still have problems such as response delays and ambiguous information, which cannot meet the high requirements of modern aircraft for flight safety and reliability. SUMMARY

[0003] To this end, the present application provides a method and system for indicating and controlling aircraft wheel brake systems without anti-skid braking, to solve the problem that pilots cannot timely learn the state of the brake system due to the failure of the anti-skid braking function of the wheel brake system or the failure of the normal braking function.

[0004] The technical solution of the present application is as follows: A method for indicating and controlling aircraft wheel brake systems without anti-skid braking is used when the anti-skid system of an aircraft fails, and pilots are prompted according to the ground speed of the aircraft and the brake pressure of all wheels, wherein the ground speed of the aircraft is judged, and if the ground speed of the aircraft does not exceed the speed threshold, no warning prompt is output to the pilot; at the same time, the brake pressure of all wheels of the aircraft is collected, and when the brake pressure of any wheel exceeds the threshold, a warning prompt or a serious warning prompt is output to the pilot.

[0005] Further, the method specifically includes an indication and control method for normal braking conditions, including the following steps: S1, collecting the brake pressure of all wheels of the aircraft, and when the brake pressure of any wheel is greater than a first pressure threshold, outputting a serious warning prompt to the pilot; otherwise, proceeding to S2; S2, when the anti-skid system fails, detecting whether the failure time exceeds a time threshold, and if so, outputting an anti-skid failure warning prompt to the pilot and proceeding to S3; otherwise, no warning is issued; S3, collecting the ground speed of the aircraft, and when the ground speed exceeds a speed threshold, proceeding to S4; otherwise, no warning prompt is issued; S4, simultaneously, the second collection of the brake pressure of all the wheels of the aircraft is carried out, when the brake pressure of any wheel is greater than the second pressure threshold, the pilot is outputted a warning prompt; otherwise, no warning prompt is outputted.

[0006] Further, the method specifically comprises the indication control method of the emergency braking working condition, comprising the following steps: S01, the brake pressure of the inner pair of wheels and the outer pair of wheels of the aircraft and the ground speed are collected; S02, when the brake pressure of the inner pair of wheels and the outer pair of wheels is less than the second pressure threshold, or the brake pressure of the inner pair of wheels and the outer pair of wheels is greater than the second pressure threshold but the ground speed is less than the speed threshold, no warning prompt is outputted; otherwise, the pilot is outputted a warning prompt.

[0007] Further, all the prompts are outputted to the pilot through visual transmission by color and text on the reference display interface, the reference display interface displays all the wheels of the aircraft by graphical and textual array arrangement, and sets brake pressure display boxes beside the wheel graphics.

[0008] Further, when no warning is outputted, the brake pressure values of each wheel are displayed in green on the reference display interface.

[0009] Further, when a warning prompt is outputted, the brake pressure values of the wheels exceeding the pressure threshold are displayed in amber on the reference display interface; when a serious warning prompt is outputted, the brake pressure values of the wheels exceeding the pressure threshold are displayed in red on the reference display interface; when a warning prompt or a serious warning prompt is outputted, the corresponding wheel graphics and text also display the brake pressure values in the same color.

[0010] Further, when the ground speed or the brake pressure of the wheel of the aircraft is compared with any threshold value, the real-time ground speed or brake pressure is greater than the corresponding threshold value for at least 0.5 seconds to complete the determination of being greater than the corresponding threshold value.

[0011] Further, when the pilot receives a warning prompt or a serious warning prompt, the brake duty cycle is immediately reduced.

[0012] The application discloses an indication control system for an airplane wheel brake system in a non-slip braking state, and an indication control method for the airplane wheel brake system in the non-slip braking state.

[0013] Technical effects: 1. The application can effectively protect the operation safety and system reliability of the airplane brake system in the non-slip state, and avoid the pilot misjudgment and operation risk caused by the failure of the anti-slip function or brake failure.

[0014] 2. The traditional brake system lacks an indication method for brake pressure abnormalities and system states in the non-slip working condition, and is prone to cause problems such as wheel locking and sliding out of control due to the lag of indication alarm or information loss. The application mainly designs an indication logic for the airplane wheel brake system in the non-slip braking state, displays the current brake pressure state on a reference display interface in three colors according to different states in two working conditions, so that the pilot can quickly identify the abnormal condition of the brake pressure in the non-slip state, make effective operation, and ensure flight safety. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 FIG. 1 is a structural diagram of the indication logic system for the non-slip braking state of the application.

[0016] Figure 2 FIG. 5 is a working flow chart of the color display logic for the non-slip braking state of the application.

[0017] Figure 3 FIG. 6 is a flow chart of the indication logic for the normal braking condition of the non-slip braking state of the application.

[0018] Figure 4 FIG. 7 is a flow chart of the indication logic for the emergency braking condition of the non-slip braking state of the application. DETAILED DESCRIPTION

[0019] The features and exemplary embodiments of the various aspects of the present application will be described in detail below. In the following detailed description, numerous specific design details are set forth in order to provide a more thorough understanding of the present application. However, it will be apparent to one of ordinary skill in the art that the present application can be practiced without some or all of these specific details. The description of the embodiments is merely intended to provide a more detailed understanding of the present application. The present application is not limited to any particular setting or method described below, but covers any modifications, equivalents, and alternatives falling within the spirit and scope of the present application. In the drawings and the following description, well-known functions or constructions are not described in detail because they would obscure the application. Embodiments of the present application will be described with reference to the accompanying drawings, in which:

[0020] It should be noted that the embodiments of the present application and the features in the embodiments can be combined with each other, and each embodiment can be referred to and cited by each other, without conflict. The present application will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0021] Embodiment 1: An indication control method for an aircraft wheel brake system without anti-skid braking is used when the anti-skid system of the aircraft fails, which prompts the pilot according to the ground speed of the aircraft and the brake pressure of all the wheels, wherein the ground speed of the aircraft is judged, and if the ground speed of the aircraft does not exceed the speed threshold, no warning prompt is output to the pilot; at the same time, the brake pressure of all the wheels of the aircraft is collected, and when the brake pressure of any wheel exceeds the threshold, a warning prompt or a serious warning prompt is output to the pilot.

[0022] Specifically, the indication control method includes a normal braking working condition, including the following steps: S1, collecting the brake pressure of all the wheels of the aircraft, and when the brake pressure of any wheel is greater than a first pressure threshold, outputting a serious warning prompt to the pilot; otherwise, entering S2; S2, when the anti-skid system is detected to fail, detecting whether the failure time exceeds a time threshold, and if so, outputting an anti-skid failure warning prompt to the pilot and entering S3; otherwise, no warning is issued; S3, collecting the ground speed of the aircraft, and when the ground speed exceeds a speed threshold, entering S4; otherwise, no warning prompt is issued; S4, collecting the brake pressure of all the wheels of the aircraft for the second time, and when the brake pressure of any wheel is greater than a second pressure threshold, outputting a warning prompt to the pilot; otherwise, no warning prompt is issued.

[0023] Specifically, the indication control method includes an emergency braking working condition, including the following steps: S01, collecting the brake pressure of the inner pair of wheels and the brake pressure of the outer pair of wheels of the aircraft, as well as the ground speed; S02: When the braking pressure of the inner and outer wheels is less than the second pressure threshold, or when the braking pressure of the inner and outer wheels is greater than the second pressure threshold but the ground speed is less than the speed threshold, no warning is issued; otherwise, a warning is issued to the pilot.

[0024] All prompts are visually transmitted to the pilot using color and text on the reference display interface. The reference display interface displays all the aircraft's wheels in an array of graphics and text, and a brake pressure display box is placed next to the wheel graphics.

[0025] When no warning is issued, the brake pressure value of each wheel is displayed in green on the reference display interface.

[0026] When a warning is issued, the brake pressure value of the wheel exceeding the pressure threshold is displayed in amber on the reference display interface; when a serious warning is issued, the brake pressure value of the wheel exceeding the pressure threshold is displayed in red on the reference display interface; when a warning or serious warning is issued, the corresponding wheel graphic and text also display the same color as the brake pressure value.

[0027] When comparing the aircraft's ground speed or wheel braking pressure with any threshold, the real-time ground speed or braking pressure must be continuously greater than the corresponding threshold for at least 0.5 seconds to complete the determination that it is greater than the corresponding threshold.

[0028] When a pilot receives a warning or serious warning, they should immediately reduce the duty cycle of braking.

[0029] An indication and control system for an aircraft wheel braking system without anti-skid braking, comprising the aforementioned method for indicating and controlling an aircraft wheel braking system without anti-skid braking, includes a brake control unit, a combined servo valve, a speed sensor, a pressure sensor, a remote data collection unit, and a reference display interface. The brake control unit and the reference display interface are connected via communication. The speed sensor is mounted on the wheel, and the pressure sensor includes a voltage-type pressure sensor located around the wheel. Data collected by the speed sensor and the pressure sensor are aggregated in the remote data collection unit and then sent to the reference display interface and the brake control unit. The brake control unit connects to and controls the combined servo valve, which provides braking pressure to the wheel.

[0030] Example 2: According to a first aspect of the present invention, an indication logic for an aircraft wheel braking system without anti-skid braking is provided, characterized in that the brake pressure color display logic without anti-skid braking includes the following steps: S1: Real-time data collection of ground speed and determination of whether ground speed exceeds the threshold range; S2: When the local speed exceeds the threshold range, the corresponding brake pressure value will be displayed in green on the reference display interface; S3: Simultaneously perform a brake pressure acquisition step on i wheels (i=1,2,3……n, where n is the total number of wheels actually in use) and determine whether the brake pressure exceeds the threshold range; S4: When the brake pressure exceeds the threshold range, the corresponding brake pressure value will be displayed in amber color on the reference display interface. Braking without anti-slip measures operates under two conditions. Under normal braking conditions, the following steps are included: S1: The brake pressure collection process for all turbine wheels. When the brake pressure exceeds the threshold range, the corresponding brake pressure value will be displayed in red on the reference display interface to issue an alarm; reminding the unit to use normal braking gently and appropriately reduce the brake duty cycle. S2: When the anti-slip function fails, the unit alarm system will report an amber text "Anti-slip failure" alarm and determine whether the duration exceeds the threshold range. S3: Real-time data collection of ground speed and determination of whether ground speed exceeds the threshold range; S4: When the local speed exceeds the threshold range, the corresponding brake pressure value color will be displayed on the reference display interface. S5: Simultaneously perform a brake pressure acquisition step on i wheels (i=1,2,3……n, where n is the total number of wheels actually in use) and determine whether the brake pressure exceeds the threshold range; S6: When the braking pressure exceeds the threshold range, the corresponding braking pressure value color will be displayed on the reference display interface. When the speed is greater than 9 and the pressure is greater than 6.5, the unit will be reminded to use normal braking gently and appropriately reduce the braking duty cycle.

[0031] The emergency braking procedure includes the following steps: S1: The steps of collecting the braking pressure of the inner wheel and the braking pressure of the outer wheel, as well as the ground speed, are used to determine whether the braking pressure and ground speed exceed the threshold range. S2: When the braking pressure and ground speed exceed the threshold range, the corresponding braking pressure value color will be displayed on the reference display interface to issue an alarm.

[0032] According to a second aspect of the present invention, an indication logic system for an aircraft wheel braking system when there is no anti-skid braking is provided, comprising: The brake command sensor is used to collect brake commands from the driver and passenger and transmit the dual-redundant brake command voltage signal to the brake control unit. The combined servo valve is used to output the corresponding braking pressure to the normal brake piston of the corresponding wheel brake device to apply the brakes; Speed ​​sensors are used to detect wheel speed; The brake control unit receives brake command signals and controls the output brake current to achieve the fly-by-wire braking function. Simultaneously, it receives speed sensor signals, detects wheel slippage, calculates anti-slip amount, and adjusts the current output by the combined servo valve to release wheel slippage in a timely manner. It also provides corresponding equipment alarms to indicate equipment malfunctions and facilitates system maintenance. Pressure sensor (current type) is used to collect the braking pressure of the inner wheel and the outer wheel; Shutdown / emergency brake valve, used for variable pressure gain; The stop / emergency brake handle is used to drive the stop / emergency brake cable to operate the stop / emergency brake valve and output braking pressure. The stop / emergency brake cable is used to transmit the force and displacement of the stop / emergency brake handle to the rocker arm of the stop / emergency brake valve, thereby controlling the stop / emergency brake valve to output braking pressure. Pressure sensors (voltage type) are used to collect the emergency braking pressure of the inner wheel and the outer wheel; A remote data collection unit is used to acquire the output of a pressure sensor (voltage type); The remote data interface unit is used to receive signals from the brake control unit and the remote data centralization unit to enable communication with the avionics system.

[0033] In one possible embodiment, the real-time braking pressure of each wheel can be collected independently.

[0034] In one possible embodiment, the wheel braking system employs dual-redundant power supply, meaning that the inner and outer power supplies are completely independent, and the inner and outer wheel control channels are independent.

[0035] The wheel braking system is equipped with two types of pressure sensors. The current-type pressure sensor is installed on the normal brake line and outputs a corresponding current signal based on the collected brake pressure. This current-type pressure sensor is connected to the combined servo valve via a brake cable. The combined servo valve adjusts the system's brake pressure, outputting a brake pressure proportional to the current, which is then transmitted to the brake control unit. The brake control unit, remote data interface unit, and reference display interface are connected via a bus for information exchange. The voltage-type pressure sensor is installed on the emergency brake line and outputs a corresponding voltage signal based on the collected brake pressure, which is transmitted to the remote data centralization unit. The remote data centralization unit, remote data interface unit, and reference display interface are also connected via a bus for information exchange.

[0036] Example 3: See Figure 1 This is a structural diagram of the indication logic system of the aircraft wheel braking system provided by the present invention when there is no anti-skid braking.

[0037] Under normal braking conditions: The brake control unit collects and processes the signals output by the brake command sensor and outputs corresponding voltage / current control signals to drive the combined servo valve to output the predetermined brake pressure. At the same time, the speed sensor feeds back the wheel speed signal to the brake control unit. After determining whether the brake pressure meets the anti-skid failure condition, the brake control unit transmits a signal to the avionics system via the remote data interface unit and bus to report an "anti-skid failure" alarm. It further determines whether the ground speed and brake pressure exceed the threshold and displays the brake pressure value in color on the reference interface so that the crew can identify the current braking status.

[0038] Under emergency braking conditions: The unit operates the stop / emergency brake handle to apply brake pressure through the stop / emergency brake valve to the braking device for braking. When the hydraulic power source fails or stops working, the brake accumulator supplies pressure to the emergency braking system. The corresponding emergency braking pressure is collected by the pressure sensor and then transmitted through the remote data central unit and the remote data interface unit. The brake pressure value is displayed in color on the reference interface so that the unit can identify the current braking status.

[0039] See Figure 2 This is a flowchart illustrating the color display logic of the aircraft wheel braking system when there is no anti-skid braking, as provided by the present invention, including the following steps: Step 1: Collect data on wheel speed, brake pressure, and ground speed, and then proceed to Step 2; Step 2: Determine whether the ground speed exceeds the threshold range according to the first instruction logic statement. If the judgment statement is satisfied, the brake pressure value on the reference display interface will be displayed in green; if the judgment statement is not satisfied, proceed to Step 3. Step 3: Determine whether the brake pressure exceeds the threshold range according to the second instruction logic statement. If the judgment statement is satisfied, the brake pressure value on the reference display interface will be displayed in green; if the judgment statement is not satisfied, the brake pressure value on the reference display interface will be displayed in amber.

[0040] See Figure 3 This is a flowchart of the normal braking condition indicating the aircraft wheel braking system without anti-skid braking, provided by the present invention, including the following steps: Step 1: Collect the braking pressure of the wheel and proceed to Step 2; Step 2: Determine whether the anti-skid function is malfunctioning based on the first instruction logic statement; if the statement is met, it means the brake pressure exceeds the threshold range, and the brake pressure value on the reference display interface will be displayed in red; if the statement is not met, it means the anti-skid function is malfunctioning, and then proceed to Step 3. Step 3: The unit alarm system reports an amber text alarm "Anti-slip failure" accompanied by audible and visual alarms, and then proceeds to Step 4.

[0041] Step 4: Determine whether the alarm meets the conditions according to the second instruction logic statement. If the condition is met, proceed to step 5; if the condition is not met, the "anti-skid failure" alarm is cleared, and the brake pressure value on the reference display interface will be displayed in green. Step 5: Collect ground velocity. According to the logical judgment statement in instruction 3, determine whether the ground velocity exceeds the threshold. If the judgment statement is satisfied, it means that the ground velocity meets the requirements, and the pressure value on the reference display interface will be displayed in green; if the judgment statement is not satisfied, proceed to step 6. Step Six: Collect the brake pressure of the left inner wheel, left outer wheel, right inner wheel, and right outer wheel. Based on the logic statement in instruction number 4, determine if the brake pressure exceeds the threshold. If the statement is satisfied, the brake pressure meets the requirements, and the brake pressure value on the reference display interface will be displayed in green. If the statement is not satisfied, the brake pressure is abnormal, and the brake pressure value on the reference display interface will be displayed in amber. Remind the unit to use normal braking gently and appropriately reduce the brake duty cycle.

[0042] See Figure 4 This is a flowchart of the emergency braking condition indication logic for an aircraft wheel braking system without anti-skid braking, provided by the present invention, including the following steps: Step 1: Collect the emergency braking pressure of the inner wheel, the emergency braking pressure of the outer wheel, and the ground speed, and then proceed to Step 2; Step 2: Determine the current emergency braking status. If the condition is met, it means both emergency braking pressure and ground speed meet the requirements, and the pressure value on the reference display interface will be displayed in green. If the condition is not met, it means the emergency braking pressure is abnormal, and the pressure value on the reference display interface will be displayed in amber. Remind the crew to use normal braking gently and appropriately reduce the braking duty cycle.

[0043] The above description is only a preferred embodiment of the present invention. It should be noted that those skilled in the art can make several improvements without departing from the principle of the present invention, and these improvements should also be considered within the scope of protection of the present invention.

Claims

1. An indicating control method for an aircraft wheel brake system when the wheel brakes are not being applied, characterized in that, The application is used when the anti-skid system of the airplane fails, and the pilot is prompted according to the ground speed of the airplane and the brake pressure of all the wheels, wherein the ground speed of the airplane is judged, and if the ground speed of the airplane does not exceed the speed threshold, no warning prompt is output to the pilot; meanwhile, the brake pressure of all the wheels of the airplane is collected, and when the brake pressure of any wheel exceeds the threshold, a warning prompt or a serious warning prompt is output to the pilot.

2. The method of claim 1, wherein, Specifically, the indication control method in the normal brake working condition comprises the following steps: S1, the brake pressure of all the wheels of the airplane is collected, and when the brake pressure of any wheel is greater than the first pressure threshold, a serious warning prompt is output to the pilot; otherwise, S2 is entered; S2, when the anti-skid system is detected to fail, it is detected whether the failure time exceeds the time threshold, and if yes, an anti-skid failure warning prompt is output to the pilot and S3 is entered; otherwise, no warning is issued; S3, the ground speed of the airplane is collected, and when the ground speed exceeds the speed threshold, S4 is entered; otherwise, no warning prompt is issued; S4, the brake pressure of all the wheels of the airplane is collected again, and when the brake pressure of any wheel is greater than the second pressure threshold, a warning prompt is output to the pilot; otherwise, no warning prompt is issued.

3. The method of claim 1, wherein the method further comprises: Specifically, the indication control method in the emergency brake working condition comprises the following steps: S01, the brake pressure of the inner pair of wheels and the brake pressure of the outer pair of wheels and the ground speed of the airplane are collected; S02, when the brake pressure of the inner pair of wheels and the brake pressure of the outer pair of wheels are less than the second pressure threshold, or the brake pressure of the inner pair of wheels and the brake pressure of the outer pair of wheels are greater than the second pressure threshold but the ground speed is less than the speed threshold, no warning prompt is issued; otherwise, a warning prompt is output to the pilot.

4. The method of claim 1, wherein, All the prompts are output to the pilot in the form of visual transmission by color and text on the reference display interface, and the reference display interface displays all the wheels of the airplane in the form of graphic and text array respectively.

5. The method of claim 4, wherein the method further comprises: When no warning is issued, the brake pressure values of each wheel are displayed in green on the reference display interface.

6. The method of claim 5, wherein the method further comprises: When a warning prompt is issued, the brake pressure values of the wheels exceeding the pressure threshold are displayed in amber on the reference display interface; when a serious warning prompt is issued, the brake pressure values of the wheels exceeding the pressure threshold are displayed in red on the reference display interface; when a warning prompt or a serious warning prompt is issued, the graphic and text of the corresponding wheel also display the brake pressure values in the same color.

7. A method of indicating the absence of wheel skid in an aircraft wheel brake system according to claim 2 or 3, characterised in that, When the ground speed or the brake pressure of the wheel is compared with any threshold, the real-time ground speed or brake pressure is greater than the corresponding threshold for at least 0.5 seconds to complete the determination of being greater than the corresponding threshold.

8. The method of claim 1, wherein, When the pilot receives a warning prompt or a serious warning prompt, the duty ratio of the brake is immediately reduced.

9. An aircraft wheel brake system non-slip braking time indication control system for implementing an aircraft wheel brake system non-slip braking time indication control method as claimed in any one of claims 1 to 9, characterized in that The brake control unit, the combined servo valve, the speed sensor, the pressure sensor, the remote data collection unit and the reference display interface are connected by communication, the speed sensor is installed on the wheel, the pressure sensor is a voltage type pressure sensor arranged around the wheel, the data collected by the speed sensor and the pressure sensor is sent to the reference display interface and the brake control unit after being collected in the remote data collection unit; the brake control unit is connected with and controls the combined servo valve, and the combined servo valve provides brake pressure for the wheel brake.

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