High-precision automatic detection method for aircraft brake system

Abstract

The application provides a high-precision automatic detection method for an airplane brake system, and belongs to the technical field of airplane brake system debugging. A brake system comprehensive debugging detection device and a digitalized footrest brake force measuring device are designed, and the brake system comprehensive debugging detection device and the digitalized footrest brake force measuring device are responsible for brake electrical system debugging monitoring and footrest mechanical system transmission operating force measurement respectively. The built-in brake monitoring soft module of the brake system comprehensive debugging detection device acquires bus data, and displays brake system data visually, so as to achieve the purpose of brake electrical system debugging monitoring; the digitalized footrest brake force measuring device is provided with a force sensor, the force sensor is installed on a clamp designed to be matched with the footrest, and a digitalized display is matched, so that the brake force value applied by an operator can be read in real time.

Description

Technical Field

[0001] This invention is applied in the field of aircraft brake system debugging technology. By studying the transmission logic of brake system technical parameters, terminal brake data is obtained and displayed using a visualization platform. This enables high-precision automated and digital inspection, measurement, monitoring, and fault diagnosis of the electrical modules and hydraulic accessories of the brake system, improving work efficiency and the accuracy of parameter detection. Background Technology

[0002] The aircraft's wheel braking system plays a crucial role during takeoff and landing. During takeoff, the system uses takeoff brakes to bring the aircraft to a stop, maximizing initial acceleration and reducing takeoff distance. During landing, the system generates braking force during the taxiing process to bring the aircraft to a complete stop. In aircraft manufacturing, checking the functionality of the braking system is a top priority in the commissioning process.

[0003] Most braking system parameters cannot be displayed on the aircraft's control system. The majority of data requires manual measurement by personnel based on external observations of the aircraft, using common tools such as stopwatches, rulers, and pointer-type force gauges. However, due to limitations in the reaction time of some technical parameters, making precise stopwatch measurements impossible, and the limited space required for measuring with rulers and force gauges due to the external shape of components, some braking system parameters can only be roughly estimated. Multiple measurements are then taken and averaged to eliminate measurement errors, resulting in low efficiency and accuracy.

[0004] Furthermore, the braking system involves numerous finished components, primarily including command sensors, an electromechanical management computer (including the brake module), hydraulic solenoid valves, servo valves, shuttle valves, pressure sensors, wheel speed sensors, etc. The interconnections between these components are intricate, and the internal workings of the braking system are highly complex. Therefore, troubleshooting a brake malfunction is extremely difficult. Traditional troubleshooting methods rely on the brake system's self-test function to detect top-level fault information and codes, identifying the approximate faulty component and wiring. Troubleshooting is then performed using traditional methods such as component replacement, wiring continuity testing, and wiring harness adjustments. However, this self-test function can only perform self-tests on the brake module within the electromechanical management computer and cannot self-test the hydraulic brake accessories. Therefore, this traditional troubleshooting method has certain limitations.

[0005] Based on the limitations of traditional testing and troubleshooting methods, this study researched high-precision automated testing technology for aircraft braking systems, and invented a comprehensive testing and debugging device for braking systems and a digital foot brake force measuring device. This further optimized the process flow of braking system debugging, avoided measurement errors caused by human operation, and displayed all test data through a visual interface. It not only has a high degree of automation, but also improves accuracy and operability, and solves the difficult problems in the debugging, testing, and troubleshooting of braking systems to the greatest extent. Summary of the Invention

[0006] The present invention aims to provide a comprehensive debugging and testing equipment for braking systems and a digital foot pedal brake force measuring device, which can realize high-precision automated testing of braking systems.

[0007] The technical solution of the present invention:

[0008] The high-precision automated testing method for aircraft braking systems is as follows:

[0009] A comprehensive braking system testing and debugging device and a digital pedal brake force measurement device were designed separately. These two devices are responsible for monitoring and debugging the brake electrical system and measuring the transmission force of the pedal mechanical system, respectively. The comprehensive braking system testing and debugging device has built-in brake monitoring software that acquires bus data and displays it visually, thus monitoring and debugging the brake electrical system. The digital pedal brake force measurement device is equipped with a force sensor. A clamp adapted to the pedal is designed to mount the force sensor on the clamp, and a digital display is used to read the brake force applied by the operator in real time.

[0010] Furthermore, the core control component of the wheel braking system is the brake module within the electromechanical management computer. The brake module adjusts the input current of the electro-hydraulic pressure servo valve according to a predetermined braking control rate, thereby causing the servo valve to output braking pressure corresponding to the current, thus applying the braking function to the aircraft. Simultaneously, the brake module uploads all braking information to the electromechanical management computer. After processing, the data is uploaded to the aircraft's bus recording data and finally to the flight parameter system. The integrated braking system testing and debugging equipment uses a testing cable inserted into the electromechanical management computer's testing socket to acquire the bus recording data. This data is then analyzed and processed using the brake monitoring software within the equipment, enabling automated testing and debugging. See the schematic diagram for details. Figure 1 .

[0011] Furthermore, the comprehensive braking system testing and debugging equipment includes a testing cable 03, an adapter 02, and a ground inspection device 01 with built-in monitoring software. One end of the testing cable 03 is connected to the testing socket of the aircraft's electromechanical management computer 04, and the other end is connected to the adapter 02. The adapter 02 then connects to the ground inspection device 01 with built-in braking monitoring software via a USB port. See the schematic diagram for details. Figure 2 .

[0012] Furthermore, the packet decomposition algorithm in the brake monitoring software is as follows:

[0013] Firstly, the electromechanical management computer uploads data to the aircraft bus in the form of data packets, which are a large sequence of data. The data model is as follows:

[0014] S = {(a1, a2, a3, ..., a...} n )}

[0015] Where S represents the determinant of the transmitted data packets, a1—a n It represents a sequence of n data sets.

[0016] After the aforementioned data packets are acquired via the detection cable, they are transmitted to the brake monitoring software. The brake monitoring software then uses parsing algorithms K1, K2, K3…K… n The data packet determinant S is filtered and decomposed into n sets of sequences b1, b2...b representing different technical parameters. n Upload the data to the display and control system for display, where k1, k2…k n The solution coefficients are represented by the following analytical model:

[0017] b1={(a1, a2, a3, ...., a n )}×K1=k1×a1 T

[0018] b2={(a1, a2, a3, ...., a n )}×K2=k2×a2 T

[0019] …

[0020] b n ={(a1, a2, a3, ..., a n )}×K n =k n ×a n T

[0021] in:

[0022]

[0023] Note: a n T Representing sequence a n The inversion of .

[0024] pass Figure 1 It is known that the integrated testing and debugging equipment for the braking system can be connected to the testing socket of the electromechanical management computer through testing cables and adapters to obtain braking system parameters that are the same as those of the aircraft bus system. Then, the data is analyzed and processed using VB programming software, and all braking system data and fault status are visualized through the display interface. In addition, the connection cable at the testing socket will not affect the normal operation of the onboard system. The equipment only receives information and does not send it outward, so it will not interfere with the operation of the onboard system.

[0025] Furthermore, the digital pedal braking force measurement device is as follows:

[0026] The foot pedals deflect up and down along their own rotation axis and control the brake pressure reducer through a linkage to achieve the main brake pressure output. Among these parameters, the brake operating force is the most important control parameter that determines the brake pressure and the pilot's control quality.

[0027] The digital pedal braking force measuring device includes a fixed plate 1, a side plate 2, a limiting pin 3, a pedal 4, a connecting screw 5, a pin 6, a tongue 7, a handheld digital push-pull force gauge 8, short connecting bolts 9, and long connecting bolts 10. The fixed plate 1 and side plate 2 are fixed together by four short connecting bolts 9 and mounted on the pedal, secured by two pins 6 and two limiting pins 3. The tongue 7 is rotated 90 degrees and positioned horizontally at the insertion port to prevent the fixed plate 1 from slipping off the pedal. The handheld digital push-pull force gauge 8 is mounted and fixed to the fixed plate 1 by eight long connecting bolts 10. The pedal 4 is mounted on the handheld digital push-pull force gauge 8 via the connecting screw 5. See the schematic diagram for details. Figure 3 .

[0028] The beneficial effects of this invention are:

[0029] (1) The high-precision automated testing technology of the brake system is used for debugging. No manual operation is required throughout the process. The operator only needs to step on the foot pedal and operate the rotating wheel mechanism to drive the main wheel to rotate. All technical parameters can be displayed. The traditional method of debugging the brake process requires at least 8 working hours, while the debugging using the testing technology of this invention can be completed in only 2 working hours, which increases the work efficiency by more than 75%, greatly improves the work efficiency, and shortens the debugging cycle.

[0030] (2) The high-precision automated testing technology of the braking system can directly obtain aircraft bus data, especially for some braking data that are difficult to test, such as the brake pressure rise time and the working stroke of the command sensor. This avoids a lot of manual measurement and reading, and directly reduces the measurement error to 0, which greatly improves the accuracy of the aircraft wheel brake system debugging.

[0031] (3) The digital foot pedal braking force measuring device adopts integrated data display technology. The operator can measure and read the debugging data by simply operating the handheld display. This overcomes the problem of the small cockpit operating space making it difficult to measure the braking force, greatly improving operability. Moreover, the foot pedals of each model have only minor differences. The measurement of the foot pedals of each model can be met by adjusting the limit pin. The applicability is extremely wide.

[0032] (4) When using the digital foot pedal brake force measuring device to measure the brake operating force, the operator does not need to manually draw lines to determine the force measuring point. The force sensor is placed in the pre-designed measuring hole. The distance between the measuring hole and the foot pedal rotation axis is the measuring lever arm. No manual determination is required, which reduces human error and makes the measurement data more accurate. In addition, the measurement data are all displayed digitally for the operator to view, avoiding visual errors. Therefore, the convenience of aircraft debugging is greatly improved.

[0033] (5) Although the aircraft has a built-in brake self-test function, it can only detect electrical circuit faults such as brake module and does not have the function to test other hydraulic components of the brake system. However, this invention can perform real-time visual monitoring of brake system parameters without affecting the normal operation of the brake system and other products, and can accurately locate faults in the first time, saving a lot of troubleshooting and inspection time. Attached Figure Description

[0034] Figure 1 Brake data transmission logic flowchart.

[0035] Figure 2 Braking system comprehensive debugging and testing equipment.

[0036] Figure 3 Digital pedal braking force measurement device.

[0037] In the diagram: 01 Ground inspection book with built-in monitoring software, 02 Adapter, 03 Detection cable, 04 Electromechanical management computer, 1 Fixing plate, 2 Side plate, 3 Limiting pin, 4 Pedal, Connecting screw, 6 Pin, 7 Tongue, 8 Handheld digital push-pull force gauge, 9 Short connecting bolt, 10 Long connecting bolt. Detailed Implementation

[0038] The specific implementation methods and steps of this invention are as follows:

[0039] (1) First, connect the test cable 03, the adapter 02, and the ground test book 01 with built-in monitoring software to form a comprehensive test and debugging device for the brake system, and connect the test cable 03 to the test port of the aircraft electromechanical management computer 04.

[0040] (2) Install the digital foot pedal brake force measuring device on the left foot pedal of the aircraft and adjust the limiting pin 3 to reliably fix the device on the foot pedal.

[0041] (3) After adjusting the position of the digital foot pedal brake force measuring device, fix it with two pins 6, and rotate the tongue 7 90° and place it horizontally at the socket.

[0042] (4) Power on the aircraft and connect the hydraulic power source;

[0043] (5) Open the monitoring software in the ground inspection book 3 with built-in monitoring software and the display on the handheld digital push-pull force gauge 8 respectively;

[0044] (6) When the operator steps on pedal 4 to deflect the pedal to the limit, the braking force value can be displayed on the handheld digital push-pull force gauge 8 and the reading can be recorded. At the same time, the maximum braking pressure and pressure rise time can be displayed on the screen of the ground inspection book 03 with built-in monitoring software.

[0045] (7) Remove the digital pedal brake force measuring device from the left pedal and install it on the right pedal. Repeat the above operation to check, adjust and record the right pedal brake force, maximum brake pressure and rise time.

[0046] (8) Remove the digital pedal brake force measuring device and store it properly;

[0047] (9) Then, the anti-skid, ground protection, wheel-to-wheel protection and brake self-test of the brake system are debugged respectively. The main wheel is driven to rotate at high speed by the rotating wheel mechanism. The display screen of the ground test machine 03 with built-in monitoring software can show the wheel speed and brake pressure changes at this time.

[0048] (10) If the brake system malfunctions during the brake commissioning process, the brake system integrated commissioning and testing equipment can decompose the data packet and display the fault information and fault point in real time without manual troubleshooting.

[0049] (11) After the above work is completed, remove the test cable 01 from the electromechanical management computer and properly store the brake system integrated debugging and testing equipment.

Claims

1. A high-precision automated testing method for aircraft braking systems, characterized in that, Specifically, the design includes a comprehensive debugging and testing device for the brake system and a digital pedal brake force measuring device. The comprehensive debugging and testing device for the brake system and the digital pedal brake force measuring device are respectively responsible for the debugging and monitoring of the brake electrical system and the measurement of the transmission and operating force of the pedal mechanical system. The brake monitoring software built into the integrated debugging and testing equipment for the brake system acquires bus data and displays the brake system data in a visual manner, thereby achieving the purpose of debugging and monitoring the brake electrical system. The digital pedal braking force measurement device is equipped with a force sensor. By designing a clamp that is compatible with the pedal, the force sensor is installed on the clamp and paired with a digital display, so that the braking force applied by the operator can be read in real time. The core control component of the wheel braking system is the brake module in the electromechanical management computer. The brake module adjusts the input current of the electro-hydraulic pressure servo valve according to the predetermined brake control rate, and then the servo valve outputs the brake pressure corresponding to the current to implement the braking function of the aircraft. At the same time, the brake module uploads all braking information to the electromechanical management computer, which processes it and then uploads it to the aircraft's bus recording data, and finally uploads it to the flight parameter system. The brake system integrated debugging and testing equipment uses a testing cable inserted into the testing socket of the electromechanical management computer to acquire bus recorded data. The data is then analyzed and processed using the brake monitoring software inside the equipment, thereby achieving automated testing and debugging functions.

2. The high-precision automated testing method for aircraft braking systems according to claim 1, characterized in that, The comprehensive testing and debugging equipment for the braking system includes a testing cable (03), an adapter (02), and a ground tester (01) with built-in monitoring software. One end of the testing cable (03) is connected to the testing socket of the aircraft's electromechanical management computer (04), and the other end is connected to the adapter (02). The cable is then connected to the ground tester (01) with built-in braking monitoring software via the USB port on the adapter (02).

3. The high-precision automated testing method for aircraft braking systems according to claim 1, characterized in that, The packet decomposition algorithm in the brake monitoring software is as follows: Firstly, the electromechanical management computer uploads data to the aircraft bus in the form of data packets, which are a large sequence of data. The data model is as follows: where S represents the determinant of the transmitted data packet, a1— a n representing n sets of data series; When the above data packet is obtained by detecting cable and transmitted to brake monitoring software, brake monitoring software uses analysis algorithm K1, K2, K3…K n The data packet determinant S is screened and processed, and is decomposed into n groups of numerical series b1, b2…b n Upload the display control system for display, wherein k1, k2…k n Represent the solving coefficient, and the specific analysis model is as follows: … in: 、 、…… Note: Representative sequence The inversion of .

4. The high-precision automated testing method for aircraft braking systems according to claim 1, characterized in that, The digital pedal braking force measuring device includes a fixed plate (1), a side plate (2), a limiting pin (3), a pedal (4), a connecting screw (5), a pin (6), a tongue (7), a handheld digital push-pull force gauge (8), short connecting bolts (9), and long connecting bolts (10). The fixed plate (1) and the side plate (2) are fixed together by four short connecting bolts (9) and installed on the pedal. They are fixed with two pins (6) and two limiting pins (3). The tongue (7) is rotated 90 degrees and placed horizontally at the socket to prevent the fixed plate (1) from slipping off the pedal. The handheld digital push-pull force gauge (8) is installed and fixed on the fixed plate (1) by eight long connecting bolts (10). The pedal (4) is installed on the handheld digital push-pull force gauge (8) by the connecting screw (5).

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