CN117465687A - High-precision automatic detection method for aircraft brake system - Google Patents
High-precision automatic detection method for aircraft brake system Download PDFInfo
- Publication number
- CN117465687A CN117465687A CN202311444265.6A CN202311444265A CN117465687A CN 117465687 A CN117465687 A CN 117465687A CN 202311444265 A CN202311444265 A CN 202311444265A CN 117465687 A CN117465687 A CN 117465687A
- Authority
- CN
- China
- Prior art keywords
- brake
- pedal
- debugging
- brake system
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000001514 detection method Methods 0.000 title claims abstract description 40
- 238000012544 monitoring process Methods 0.000 claims abstract description 9
- 230000005540 biological transmission Effects 0.000 claims abstract description 8
- 238000007726 management method Methods 0.000 claims description 18
- 238000000034 method Methods 0.000 claims description 13
- 238000012360 testing method Methods 0.000 claims description 6
- 238000004458 analytical method Methods 0.000 claims description 4
- 238000003491 array Methods 0.000 claims description 4
- 238000007689 inspection Methods 0.000 claims description 3
- 238000013499 data model Methods 0.000 claims description 2
- 238000000354 decomposition reaction Methods 0.000 claims description 2
- 238000012545 processing Methods 0.000 claims description 2
- 238000012216 screening Methods 0.000 claims description 2
- 238000005259 measurement Methods 0.000 description 7
- 238000013024 troubleshooting Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 230000000007 visual effect Effects 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 238000012935 Averaging Methods 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 238000004132 cross linking Methods 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000035484 reaction time Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Regulating Braking Force (AREA)
Abstract
The invention provides a high-precision automatic detection method for an aircraft brake system, and belongs to the technical field of debugging of aircraft brake systems. The invention designs a comprehensive debugging and detecting device and a digital pedal braking force measuring device of a braking system respectively, wherein the comprehensive debugging and detecting device and the digital pedal braking force measuring device of the braking system are respectively responsible for debugging and monitoring a braking electric system and measuring transmission operating force of a pedal mechanical system. The built-in brake monitoring soft module of the brake system comprehensive debugging and detecting equipment achieves the purpose of debugging and monitoring the brake electrical system by acquiring bus data and visually displaying the brake system data; the digital pedal braking force measuring device is provided with a force sensor, and the force sensor is arranged on the clamp through designing the clamp matched with the pedal, and the braking force value applied by an operator can be read in real time by matching with a digital display.
Description
Technical Field
The invention is applied to the technical field of debugging of an aircraft brake system. The technical parameter transmission logic of the brake system is researched, so that the terminal brake data is obtained and displayed by a visual platform, high-precision automatic and digital inspection, measurement, monitoring and fault diagnosis of an electric module and a hydraulic accessory of the brake system are realized, and the working efficiency and the accuracy of parameter detection are improved.
Background
The wheel brake system of the aircraft plays a very important role in the take-off and landing phases of the aircraft. In the take-off stage, the system has the functions of braking the aircraft by using a take-off brake to obtain the maximum initial acceleration and reducing the take-off distance; during the landing phase, the system can generate braking force during the running process of the aircraft to stop the aircraft. In the aircraft manufacturing process, checking the functionality of the brake system of an aircraft is a major issue in debugging.
Most of the parameters of the braking system cannot be displayed one by one through an aircraft display control system, most of the data are required to be manually measured by personnel through external appearance of the aircraft, and the used tools are all general tools such as stopwatches, steel plates, pointer type pulling-pressing force measuring meters and the like. However, because some technical parameters are detected to break through the limit of the reaction time of detection personnel, the accurate measurement by a stopwatch cannot be realized, and the problems of no measurement operation space and the like caused by the external shape of a part are solved by using a steel plate ruler and a pointer type pulling-pressing force measuring meter, the technical parameters of a part of brake system can only be roughly estimated and read, the measurement error is eliminated by adopting a mode of measuring for averaging for a plurality of times, the working efficiency is low, and the accuracy is low.
In addition, the brake system mainly comprises an instruction sensor, an electromechanical management computer (comprising a brake module), a hydraulic electromagnetic valve, a servo valve, a spindle valve, a pressure sensor, a wheel speed sensor and the like, the crosslinking relation among the components is complicated, the internal principle of the brake system is complicated, and the process of eliminating the faults is difficult once a certain brake fault occurs. The traditional troubleshooting method is to detect top fault information and fault codes according to the self-checking function of the brake system, determine the parts and circuits which are approximately faulty, and troubleshoot the faults by the traditional modes of switching the parts, measuring the conductivity of the circuits, switching the wire harnesses and the like; however, the self-checking function can only perform self-checking on the brake module in the electromechanical management computer, and cannot perform self-checking on the brake hydraulic accessory, so that the traditional troubleshooting mode has certain limitation.
Based on the limitations of the traditional detection and troubleshooting method, the invention provides the comprehensive debugging and detection equipment of the brake system and the digital pedal braking force measuring device for the brake system, further optimizes the technological process of the debugging work of the brake system, avoids measurement errors caused by manual operation, displays all detection data through a visual display interface, has high automation degree, improves accuracy and operability, and furthest solves the problems in the debugging and detection and troubleshooting processes of the brake system.
Disclosure of Invention
The invention aims to provide comprehensive debugging and detecting equipment for a braking system and a digital pedal braking force measuring device, so that high-precision automatic detection of the braking system can be realized.
The technical scheme of the invention is as follows:
the high-precision automatic detection method of the aircraft brake system specifically comprises the following steps:
the comprehensive debugging and detecting equipment and the digital pedal braking force measuring device of the braking system are respectively designed and respectively responsible for debugging and monitoring the braking electric system and measuring the transmission operating force of the pedal mechanical system. Brake monitoring software arranged in the brake system comprehensive debugging and detecting equipment plays a role in debugging and monitoring the brake electrical system by acquiring bus data and visually displaying the brake system data; the digital pedal braking force measuring device is provided with a force sensor, and the force sensor is arranged on the clamp through designing the clamp matched with the pedal, and the braking force value applied by an operator can be read in real time by matching with a digital display.
Further, the core control component of the wheel braking system is a braking module in the electromechanical management computer. The brake module adjusts the input current of the electrohydraulic pressure servo valve according to a preset brake control rate, and then the servo valve outputs the brake pressure corresponding to the current, so as to implement the brake function for the aircraft. Meanwhile, the braking module uploads all braking information to the electromechanical management computer, and the braking information is uploaded to bus record data of the aircraft after being processed by the electromechanical management computer and finally uploaded to the flight parameter system. The brake system comprehensive debugging and detecting equipment is inserted into an electromechanical management computer detection socket by using a detection cable, bus record data is obtained, and analysis processing is performed by using brake monitoring software in the brake system comprehensive debugging and detecting equipment, so that automatic detection and debugging functions are realized. The schematic diagram is shown in detail in fig. 1.
Further, the brake system comprehensive debugging and detecting device comprises a detecting cable 03, an adapter 02 and a ground test book 01 with built-in monitoring software. One end of the detection cable 03 is connected to a detection socket of the electromechanical management computer 04 of the airplane, and the other end of the detection cable 03 is connected to the adapter 02 and then connected to the ground sample 01 with the built-in brake monitoring software through a USB socket on the adapter 02. The schematic diagram is shown in detail in fig. 2.
Further, the data packet decomposition algorithm in the brake monitoring software specifically comprises the following steps:
firstly, the data of the aircraft bus uploaded by the electromechanical management computer are data packets in the form of a series and collection of a large amount of data for transmission, and the data model is as follows:
S＝{(a 1 、a 2 、a 3 、…、a n )}
wherein S represents the transmitted packet determinant, a 1 —a n Representing n sets of data arrays.
When the data packet is acquired through the detection cable and then transmitted to brake monitoring software, the brake monitoring software utilizes an analysis algorithm K 1 、K 2 、K 3 …K n Screening the determinant S of the data packet, decomposing it into n groups of arrays b representing different technical parameters 1 、b 2 …b n Uploading and displaying by a display control system, wherein k is 1 、k 2 …k n Representing the resolution coefficients, the specific analytical model is as follows:
b 1 ＝{(a 1 、a 2 、a 3 、....、a n )}×K 1 ＝k 1 ×a 1 T
b 2 ＝{(a 1 、a 2 、a 3 、....、a n )}×K 2 ＝k 2 ×a 2 T
…
b n ＝{(a 1 、a 2 、a 3 、....、a n )}×K n ＝k n ×a n T
wherein:
note that: a, a n T Representing the array a n Is inverted.
As can be seen from FIG. 1, the brake system comprehensive debugging and detecting device can be connected to the detecting socket of the electromechanical management computer through the detecting cable and the adapter, acquire brake system parameters homologous to the aircraft bus system, analyze and process the data by utilizing VB programming software, and visually present all brake system data and fault states through the display interface.
Further, the digital pedal braking force measuring device is specifically as follows:
the pedal deflects up and down along the rotating shaft of the pedal and controls the brake pressure reducer to realize main brake pressure output through a rod system transmission, wherein the brake operating force is the most important control parameter for determining the brake pressure and the pilot operating quality.
The digital pedal braking force measuring device comprises a fixed plate 1, a side plate 2, a limiting pin 3, a pedal 4, a connecting screw 5, a bolt 6, a tongue piece 7, a hand-held digital display push-pull force meter 8, a short connecting bolt 9 and a long connecting bolt 10. The fixed plate 1 and the side plate 2 are fixed together through 4 short connecting bolts 9 and are arranged on the pedal, the two bolts 6 and the two limiting pins 3 are used for fixing, the tongue piece 7 is rotated for 90 degrees and horizontally arranged at the socket, so that the fixed plate 1 is prevented from sliding off the pedal; the hand-held digital push-pull gauge 8 is fixedly arranged on the fixed plate 1 through 8 long connecting bolts 10, and the pedal 4 is arranged on the hand-held digital push-pull gauge 8 through the connecting screw 5. The schematic diagram is shown in detail in fig. 3.
The invention has the beneficial effects that:
(1) The high-precision automatic detection technology of the brake system is utilized for debugging, manual operation is not needed in the whole process, an operator only needs to tread a pedal and operate a rotating wheel mechanism to drive a host wheel to rotate, technical parameters can be displayed one by one, at least 8 working hours are needed for debugging a brake process by using a traditional method, the detection technology is utilized for debugging, the debugging can be completed by only 2 working hours, the working efficiency is improved by more than 75%, the working efficiency is greatly improved, and the debugging period is shortened.
(2) The high-precision automatic detection technology of the braking system can be used for directly acquiring the bus data of the airplane, particularly, parameters such as the working stroke of an instruction sensor and the like are prevented from being measured manually and read, the measurement error is directly 0, and the debugging accuracy of the braking system of the airplane wheel is greatly improved.
(3) The digital pedal braking force measuring device adopts an integrated data display technology, an operator can measure and read debugging data only by controlling the handheld display, the problem that the braking force is difficult to measure due to the small operation space of the cabin is solved, the operability is greatly improved, each model pedal has small difference, the measurement of each model pedal can be met through adjustment of the limiting pin, and the application range is extremely wide;
(4) When the digital pedal braking force measuring device is used for measuring braking operating force, an operator does not need to manually mark a force measuring point, a force sensor is placed in a pre-designed measuring hole, the distance between the measuring hole and a pedal rotating shaft is a measuring force arm, manual determination is not needed, human errors are reduced, the measuring data are more accurate, in addition, the measuring data are all displayed by numbers for the operator to check, visual errors are avoided, and therefore convenience in debugging of an airplane is greatly improved;
(5) Although the aircraft is provided with a brake self-checking function, only the faults of electric circuits such as a brake module and the like can be detected, and the function detection of other hydraulic components of the brake system is not provided, the invention can perform real-time visual monitoring on parameters of the brake system on the premise that the normal operation of the brake system and other products is not influenced, and the fault can be accurately positioned at the first time, so that a large amount of troubleshooting and checking working time is saved.
Drawings
FIG. 1 is a logic flow diagram for brake data transmission.
FIG. 2 brake system integrated debugging and detecting device.
FIG. 3 shows a digital pedal braking force measuring device.
In the figure: the ground test book with the built-in monitoring software, the 02 adapter, the 03 detection cable, the 04 electromechanical management computer, the 1 fixing plate, the 2 side plates, the 3 limit pin, the 4 pedal, the connecting screw, the 6 bolt, the 7 tongue piece, the 8 hand-held digital display push-pull meter, the 9 short connecting bolt and the 10 long connecting bolt.
Detailed Description
The specific implementation mode and the steps of the invention are as follows:
(1) Firstly, connecting a detection cable 03, an adapter 02 and a ground test book 01 with built-in monitoring software to form brake system comprehensive debugging detection equipment, and connecting the detection cable 03 to a detection socket of an aircraft electromechanical management computer 04;
(2) The digital pedal braking force measuring device is arranged on the left pedal of the aircraft, and the limiting pin 3 is adjusted to ensure that the device is reliably fixed on the pedal;
(3) After the position of the digital pedal braking force measuring device is adjusted, the digital pedal braking force measuring device is fixed by two bolts 6, and the tongue piece 7 is rotated by 90 degrees and horizontally arranged at the socket;
(4) Powering on the aircraft, and switching on a hydraulic source;
(5) Respectively opening the monitor software in the ground test book 3 with the built-in monitor software and the display on the hand-held digital display type push-pull tension meter 8;
(6) The operator pedaling plate 4 is operated to deflect the pedaling plate to the limit, the hand-held digital push-pull meter 8 can display the braking force value, the reading record is carried out, and meanwhile, the display screen of the ground sample 03 with the built-in monitoring software can display the maximum braking pressure and the pressure rising time at the moment;
(7) The digital pedal braking force measuring device is detached from the left pedal and is arranged on the right pedal, the operation is repeated, and the right pedal braking force, the maximum braking pressure and the rising time are checked, adjusted and recorded;
(8) Removing the digital pedal braking force measuring device and properly storing;
(9) Then debugging works such as skid resistance, grounding protection, inter-wheel protection, brake self-checking and the like of the brake system are respectively carried out, a rotating wheel mechanism is used for driving a host wheel to rotate at a high speed, the display screen of the ground test book 03 with the built-in monitoring software can be displayed, and at the moment, the rotating speed of the wheel and the brake pressure are changed;
(10) If the brake system reports the fault in the brake debugging working process, the brake system comprehensive debugging detection equipment can display fault information and fault points in real time by decomposing the data packet without manual investigation.
(11) After the above work is completed, the detection cable 01 is removed from the electromechanical management computer, and the comprehensive debugging and detecting equipment of the brake system is properly stored.
Claims (5)
1. The high-precision automatic detection method for the aircraft brake system is characterized by comprising the following steps of: the comprehensive debugging and detecting equipment of the braking system and the digital pedal braking force measuring device are respectively designed and respectively responsible for debugging and monitoring the braking electric system and measuring the transmission operating force of the pedal mechanical system; brake monitoring software arranged in the brake system comprehensive debugging and detecting equipment plays a role in debugging and monitoring the brake electrical system by acquiring bus data and visually displaying the brake system data; the digital pedal braking force measuring device is provided with a force sensor, and the force sensor is arranged on the clamp through designing the clamp matched with the pedal, and the braking force value applied by an operator can be read in real time by matching with a digital display.
2. The method of high-precision automated inspection of an aircraft brake system according to claim 1, wherein the core control component of the aircraft brake system is a brake module in an electromechanical management computer; the brake module adjusts the input current of the electrohydraulic pressure servo valve according to a preset brake control rate, and then the servo valve outputs the brake pressure corresponding to the current, so as to implement a brake function for the aircraft; meanwhile, the braking module uploads all braking information to the electromechanical management computer, and the braking information is uploaded to bus record data of the aircraft after being processed by the electromechanical management computer and finally uploaded to the flight parameter system; the brake system comprehensive debugging and detecting equipment is inserted into an electromechanical management computer detection socket by using a detection cable, bus record data is obtained, and analysis processing is performed by using brake monitoring software in the brake system comprehensive debugging and detecting equipment, so that automatic detection and debugging functions are realized.
3. The high-precision automatic detection method for the aircraft brake system according to claim 1, wherein the comprehensive debugging and detecting equipment for the aircraft brake system comprises a detection cable (03), an adapter (02) and a ground test book (01) with built-in monitoring software; one end of the detection cable (03) is connected to a detection socket of an electromechanical management computer (04) of the airplane, and the other end of the detection cable is connected to the adapter (02) and then connected to the ground sample (01) with the built-in brake monitoring software through a USB socket on the adapter (02).
4. The method for high-precision automated inspection of an aircraft brake system according to claim 1, wherein the data packet decomposition algorithm in the brake monitoring software is specifically as follows:
firstly, the data of the aircraft bus uploaded by the electromechanical management computer are data packets in the form of a series and collection of a large amount of data for transmission, and the data model is as follows:
S＝{(a 1 、a 2 、a 3 、…、a n )}
wherein S represents the transmitted packet determinant, a 1 —a n Representing n sets of data arrays;
when the data packet is acquired through the detection cable and then transmitted to brake monitoring software, the brake monitoring software utilizes an analysis algorithm K 1 、K 2 、K 3 …K n Screening the determinant S of the data packet, decomposing it into n groups of arrays b representing different technical parameters 1 、b 2 …b n Uploading and displaying by a display control system, wherein k is 1 、k 2 …k n Representing the resolution coefficients, the specific analytical model is as follows:
b 1 ＝{(a 1 、a 2 、a 3 、…、a n )}×K 1 ＝k 1 ×a 1 T
b 2 ＝{(a 1 、a 2 、a 3 、…、a n )}×K 2 ＝k 2 ×a 2 T
…
b n ＝{(a 1 、a 2 、a 3 、…、a n )}×K n ＝k n ×a n T
wherein:
note that: a, a n T Representing the array a n Is inverted.
5. The high-precision automatic detection method for the aircraft brake system according to claim 1, wherein the digital pedal brake force measuring device comprises a fixed plate (1), a side plate (2), a limiting pin (3), a pedal (4), a connecting screw (5), a bolt (6), a tongue piece (7), a hand-held digital display push-pull gauge (8), a short connecting bolt (9) and a long connecting bolt (10); the fixed plate (1) and the side plate (2) are fixed together through 4 short connecting bolts (9), are arranged on the pedal, are fixed by two bolts (6) and two limiting pins (3), rotate the tongue piece (7) by 90 degrees, and are transversely arranged at the socket to prevent the fixed plate (1) from sliding off the pedal; the hand-held digital push-pull meter (8) is fixedly arranged on the fixed plate (1) through 8 long connecting bolts (10), and the pedal (4) is arranged on the hand-held digital push-pull meter (8) through the connecting screw (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311444265.6A CN117465687A (en) | 2023-11-01 | 2023-11-01 | High-precision automatic detection method for aircraft brake system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311444265.6A CN117465687A (en) | 2023-11-01 | 2023-11-01 | High-precision automatic detection method for aircraft brake system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117465687A true CN117465687A (en) | 2024-01-30 |
Family
ID=89628822
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311444265.6A Pending CN117465687A (en) | 2023-11-01 | 2023-11-01 | High-precision automatic detection method for aircraft brake system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117465687A (en) |
-
2023
- 2023-11-01 CN CN202311444265.6A patent/CN117465687A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101672663B (en) | Auto meter visual detecting system based on computer and detecting method thereof | |
| CN110614539B (en) | Online real-time monitoring and analyzing method for state of spindle of numerical control machine tool | |
| CN206223464U (en) | Steering wheel integrated test system for performance | |
| CN103698701B (en) | Comprehensive automatic testing system and method for stepping motor | |
| CN103196480B (en) | Automobile instrument automatic detection device and detection method | |
| CN103019940A (en) | Electric energy meter embedded software semi-simulation test device | |
| CN107907057B (en) | A grating ruler reliability test bench and a reliability test method based on load spectrum | |
| CN105526959A (en) | Encoder reliability test device and method | |
| CN116481805B (en) | A reducer precision measuring device and a measuring method thereof | |
| CN102954894A (en) | Steering engine testing device for intelligent ships | |
| CN107727029A (en) | A kind of magnetic bearing is demarcated with displacement transducer and detection means | |
| CN117465687A (en) | High-precision automatic detection method for aircraft brake system | |
| CN205384042U (en) | Encoder reliability test device | |
| CN204439109U (en) | Pressure unit electronic response speed testing system | |
| CN118191576A (en) | Calibrating device and method for testing speed characteristics of circuit breaker | |
| CN109029537A (en) | A kind of pointer-type sync bit indicator test device and its application method | |
| CN116908648A (en) | Nuclear power plant nuclear instrument system electronic board card detection device and method | |
| CN118036236A (en) | Digital twin method for matching detection display model of motor for vehicle | |
| CN102072990A (en) | Ageing detection device for laser | |
| CN211262461U (en) | Weighing sensor performance testing device | |
| CN201653544U (en) | Laser ageing detection device | |
| CN114563033A (en) | Motor encoder installation precision detection method | |
| CN114834647A (en) | System for real-time supervision aircraft body structural strength | |
| CN107179155B (en) | Automatic calibration system and calibration method for bridge mode strain stress measurement system | |
| CN104215863A (en) | Testing method of AD port of 1U controller of grinding machine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |