A method and system for indicating control of an aircraft wheel brake system when non-slip braking is not engaged

Abstract

The present application belongs to the technical field of aircraft brake system, and discloses a kind of aircraft wheel brake system no anti-skid brake time indicating control method, when the anti-skid system of aircraft fails, according to the ground speed of aircraft and the brake pressure of all wheels, the pilot is prompted, wherein the ground speed of aircraft is judged, if the ground speed of 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, the pilot is output warning prompt or serious warning prompt. Through the design of the present application, the operation safety and system reliability of the aircraft brake system in the non-anti-skid state can be effectively protected, and the pilot's misjudgment and operation risk caused by the failure of anti-skid function or brake failure can be avoided.

Description

Technical Field

[0001] This invention belongs to the field of aircraft braking system technology, and relates to a method for instructing the pilot when the anti-skid braking system of an aircraft fails. Specifically, it relates to an instruction and control method and system for aircraft wheel braking system without anti-skid braking. Background Technology

[0002] Aircraft wheel braking systems are typically equipped with anti-skid braking to provide effective braking during taxiing and landing. However, when the anti-skid braking function fails or the system enters a non-anti-skid mode, some aircraft wheel braking systems often lack clear and intuitive status indicators, and the visual cues for critical data are not obvious. This makes it difficult for pilots to perceive changes in braking status in a timely manner, causing critical data to exceed threshold ranges. Consequently, pilots are prone to making incorrect judgments or misoperations, which seriously affects flight safety. In addition, even some aircraft wheel braking systems with fault indication functions suffer from response delays and ambiguous information, failing to meet the high requirements of modern aircraft for flight safety and reliability. Summary of the Invention

[0003] To address this issue, the present invention provides a method and system for indicating and controlling the aircraft wheel braking system when the anti-skid braking function is not working, in order to solve the problem that pilots cannot promptly obtain the status of the braking system due to the failure of the anti-skid braking function or the malfunction of the normal braking function, thus leading to misoperation.

[0004] The technical solution of the present invention is as follows: A method for indicating and controlling the aircraft wheel braking system when anti-skid braking fails is disclosed. This method provides prompts to the pilot based on the aircraft's ground speed and the braking pressure of all wheels. Specifically, the ground speed is assessed, and if it does not exceed a speed threshold, no warning is issued to the pilot. Simultaneously, the braking pressure of all aircraft wheels is collected, and if the braking pressure of any wheel exceeds the threshold, a warning or serious warning is issued to the pilot.

[0005] Furthermore, specifically including the indication and control method for normal braking conditions, comprising the following steps: S1: Collect the braking pressure of all wheels of the aircraft. If the braking pressure of any wheel exceeds the first pressure threshold, output a serious warning to the pilot; otherwise, proceed to S2. S2, when the anti-skid system failure is detected, check whether the failure time exceeds the time threshold. If it does, output an anti-skid failure warning to the pilot and proceed to S3; if it does not exceed the time threshold, no warning is issued. S3 collects the aircraft's ground speed. If the ground speed exceeds the speed threshold, it enters S4. If it does not exceed the threshold, no warning is issued. S4 simultaneously collects the braking pressure of all aircraft wheels for the second time. If the braking pressure of any wheel exceeds the second pressure threshold, a warning is issued to the pilot; otherwise, no warning is issued.

[0006] Furthermore, specifically including the indication and control method for emergency braking conditions, comprising the following steps: S01 collects the braking pressure of the inner and outer 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.

[0007] Furthermore, 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.

[0008] Furthermore, when no warning is issued, the brake pressure value of each wheel is displayed in green on the reference display interface.

[0009] Furthermore, 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.

[0010] Furthermore, 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 in order to complete the determination that it is greater than the corresponding threshold.

[0011] Furthermore, when the pilot receives a warning or serious warning, he should immediately reduce the duty cycle of braking.

[0012] An indication and control system for an aircraft wheel braking system without anti-skid braking, comprising a brake control unit, a combined servo valve, a speed sensor, a pressure sensor, a remote data collection unit, and a reference display interface, wherein 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 is a voltage-type pressure sensor located around the wheel; the 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 is connected to and controls the combined servo valve, which provides braking pressure to the wheel.

[0013] Technical effects: 1. The design of this invention can effectively protect the operational safety and system reliability of the aircraft braking system in the absence of anti-skid conditions, and avoid pilot misjudgment and operational risks caused by anti-skid failure or brake malfunction.

[0014] 2. Traditional braking systems lack methods to indicate abnormal brake pressure and system status when there is no anti-skid. This can easily lead to problems such as wheel lock-up and loss of control during taxiing due to delayed warnings or missing information. This invention primarily addresses this by designing an indication logic for the aircraft wheel braking system when braking without anti-skid. Under two different operating conditions, the current brake pressure status is displayed in three colors on the reference display interface, enabling pilots to quickly identify abnormal brake pressure conditions when there is no anti-skid and take effective action to ensure flight safety. Attached Figure Description

[0015] Figure 1 This is a structural diagram of the non-anti-slip braking indication logic system of the present invention.

[0016] Figure 2 This is a flowchart of the color display logic for the present invention when there is no anti-slip braking.

[0017] Figure 3 This is a flowchart of the normal braking condition indicating the logic when there is no anti-slip braking according to the present invention.

[0018] Figure 4 This is a flowchart of the emergency braking condition indication logic when there is no anti-skid braking according to the present invention. Detailed Implementation

[0019] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific design details are set forth in the following detailed description to provide a more complete understanding of the invention. However, it will be apparent to those skilled in the art that the invention can be practiced without some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setup and method set forth below, but covers any improvements, substitutions, and modifications to the structures, methods, and devices without departing from the spirit of the invention. In the drawings and the following description, any parts not exhaustively described are considered to be common knowledge or conventional practices in the art.

[0020] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0021] Example 1: A method for indicating and controlling the aircraft wheel braking system when anti-skid braking fails is disclosed. This method provides prompts to the pilot based on the aircraft's ground speed and the braking pressure of all wheels. Specifically, the ground speed is assessed, and if it does not exceed a speed threshold, no warning is issued to the pilot. Simultaneously, the braking pressure of all aircraft wheels is collected, and if the braking pressure of any wheel exceeds the threshold, a warning or serious warning is issued to the pilot.

[0022] Specifically, this includes a method for indicating and controlling normal braking conditions, comprising the following steps: S1: Collect the braking pressure of all wheels of the aircraft. If the braking pressure of any wheel exceeds the first pressure threshold, output a serious warning to the pilot; otherwise, proceed to S2. S2, when the anti-skid system failure is detected, check whether the failure time exceeds the time threshold. If it does, output an anti-skid failure warning to the pilot and proceed to S3; if it does not exceed the time threshold, no warning is issued. S3 collects the aircraft's ground speed. If the ground speed exceeds the speed threshold, it enters S4. If it does not exceed the threshold, no warning is issued. S4 simultaneously collects the braking pressure of all aircraft wheels for the second time. If the braking pressure of any wheel exceeds the second pressure threshold, a warning is issued to the pilot; otherwise, no warning is issued.

[0023] Specifically, this includes the indication and control method for emergency braking conditions, comprising the following steps: S01 collects the braking pressure of the inner and outer 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 in order 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 of the aircraft wheel braking system when there is no 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. A method for indicating and controlling an aircraft wheel braking system when there is no anti-skid braking, characterized in that, Used when the aircraft's anti-skid system fails, it alerts the pilot based on the aircraft's ground speed and the braking pressure of all wheels. The aircraft's ground speed is assessed; if it does not exceed the speed threshold, no warning is issued to the pilot. At the same time, the braking pressure of all aircraft wheels is collected; if the braking pressure of any wheel exceeds the threshold, a warning or serious warning is issued to the pilot. The method for indicating and controlling normal braking conditions includes the following steps: S1: Collect the braking pressure of all wheels of the aircraft. If the braking pressure of any wheel exceeds the first pressure threshold, output a serious warning to the pilot; otherwise, proceed to S2. S2, when the anti-skid system failure is detected, check whether the failure time exceeds the time threshold. If it does, output an anti-skid failure warning to the pilot and proceed to S3; if it does not exceed the time threshold, no warning is issued. S3 collects the aircraft's ground speed. If the ground speed exceeds the speed threshold, it enters S4. If it does not exceed the threshold, no warning is issued. S4 simultaneously collects the braking pressure of all aircraft wheels for the second time. When the braking pressure of any wheel exceeds the second pressure threshold, a warning is issued to the pilot; otherwise, no warning is issued. 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. When no warning is issued, the brake pressure value of each wheel is displayed in green on the reference display interface; 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 are also displayed in the same color as the brake pressure value.

2. The method for indicating and controlling an aircraft wheel braking system without anti-skid braking as described in claim 1, characterized in that, The method for indicating and controlling emergency braking conditions includes the following steps: S01 collects the braking pressure of the inner and outer 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.

3. A method for indicating and controlling an aircraft wheel braking system without anti-skid braking, as described in claim 1 or 2, characterized in that, 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 in order to complete the determination that it is greater than the corresponding threshold.

4. The method for indicating and controlling an aircraft wheel braking system without anti-skid braking as described in claim 1, characterized in that, When a pilot receives a warning or serious warning, they should immediately reduce the duty cycle of braking.

5. A control system for indicating when an aircraft wheel braking system is not braking with anti-skid features, comprising the method for indicating when an aircraft wheel braking system is not braking with anti-skid features as described in any one of claims 1-4, characterized in that, It 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 is communicatively connected to the reference display interface. The speed sensor is mounted on the wheel, and the pressure sensor is a voltage-type pressure sensor located around the wheel. The 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.

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