An integrated test device for aircraft communication and navigation systems

Abstract

This invention belongs to the field of circuit board testing technology, specifically a test apparatus for integrated testing of an aircraft communication and navigation system. It includes a distributed hardware layer, a real-time test software layer, and a data interaction and control layer. The distributed hardware layer includes a test bench, test components integrated on the test bench, a marking component, a circuit board centering and positioning component, a marking isolation component, and a corner-mounted reinforcement component. This invention utilizes the marking component to automatically mark each detected fault point with a marker. When repairing the circuit board, operators only need to observe the marked positions to accurately locate the fault point, thereby improving repair efficiency.

Description

Technical Field

[0001] This invention belongs to the field of circuit board testing technology, specifically a test device for integrated testing of aircraft communication and navigation systems. Background Technology

[0002] Aircraft communication and navigation systems refer to a series of electronic devices installed on aircraft to enable communication between the air and the ground, determine the aircraft's position, and guide the aircraft for safe flight and landing. During the manufacturing process of aircraft communication and navigation equipment, electrical performance testing of the equipment's circuit boards and functional modules is required.

[0003] Patent CN213364963U discloses a circuit board testing device, which includes a carrier, a testing kit, and a clamping and positioning kit. The testing kit and the clamping and positioning kit are respectively mounted on the carrier. The clamping and positioning kit eliminates the tedious task of visually adjusting the position of the circuit board under test by the tester, eliminates the alignment error between the circuit board under test and the testing device, and enables the test points on the circuit board to be quickly and accurately aligned with the test probes. At the same time, the clamping and positioning kit also prevents the circuit board from sliding on the circuit board testing device, so that the testing equipment in the subsequent testing process can accurately contact the circuit board under test, ensuring testing accuracy. The setting of each reinforcing triangular plate can improve the mechanical strength of the test probe and prevent the test probe from bending, deforming or breaking.

[0004] However, the above technical solutions still have the following shortcomings in practical applications: Testing is performed by contacting multiple test points on the circuit board with probes. The test results are displayed in real time on the screen to determine the performance of each test point. Once a fault is detected, it must be repaired by an operator.

[0005] However, when batch testing of circuit boards is required, followed by unified repair of faulty boards, if the number of faulty boards is large, operators find it difficult to accurately remember the location of the fault on each board, thus affecting repair efficiency. Even with the help of computers or paper to record the fault location, repeated review and verification are necessary during repair, which is not only cumbersome but also prone to confusion.

[0006] Furthermore, existing testing equipment is mostly designed for single functions, with testing, marking, and recording processes being isolated and lacking a unified system architecture. Test data and fault labeling information are difficult to correlate automatically, requiring repeated manual verification during repairs, which can easily lead to confusion. Moreover, most devices have a fixed layout, preventing flexible adjustments to component configurations based on testing needs, resulting in poor scalability and adaptability. Summary of the Invention

[0007] To overcome the shortcomings of the prior art and solve at least one of the technical problems mentioned in the background art, the present invention proposes an integrated testing device for aircraft communication and navigation systems.

[0008] The technical solution adopted by this invention to solve its technical problem is: an integrated testing and experimental device for aircraft communication and navigation systems, comprising: Distributed hardware layer, real-time test software layer, and data interaction and control layer; The distributed hardware layer includes a test bench, a test component integrated on the test bench, a marking component, a circuit board centering positioning component, a marking isolation component, and a corner-type reinforcement component; The testing assembly includes a bracket 1 fixedly connected to one side of the upper surface of the test bench. A crossbeam 1 is slidably arranged on one side of the bracket 1. An adjustment plate is slidably arranged on one side of the crossbeam 1. Two guide rods 2 are slidably connected to one side of the adjustment plate. A probe is fixedly connected to the lower end of the guide rods 2. A flying probe tester is arranged on one side of the upper surface of the adjustment plate. The probe is electrically connected to the flying probe tester. The marking assembly includes a rotating rod rotatably disposed on one side of the probe, and a marker pen is fixedly connected to one end of the rotating rod; The circuit board centering and positioning component includes two positioning blocks, both of which are slidably connected to the upper surface of the test bench. The marking and isolation assembly includes a roller rotatably mounted on one side of the upper end of the test bench, with a film wound on the roller. A support column is fixedly connected to one side of the upper end of the test bench, and a rack is slidably connected to one side of the upper end of the support column. A support plate is fixedly connected to one end of the rack, and two gripper cylinders are fixedly connected to one side of the support plate. A fixing plate is fixedly connected to one side of the upper end of the test bench, and two guide rods are slidably connected to the fixing plate. A blade is fixedly connected to the upper end of each guide rod. The corner-type reinforcement assembly includes two brackets 2 fixedly connected to one side of the upper surface of the test bench. The two brackets 2 are slidably provided with a crossbeam 2. Two threaded blocks are slidably provided on both sides of the crossbeam 2. A cylinder 5 is fixedly connected to one side of the threaded block. A connecting block is fixedly connected to the piston end of the cylinder 5. A flip plate is rotatably provided on one side of the connecting block. Two sliders are slidably connected to one side of the flip plate. A rigid tube is fixedly connected to the lower end face of the slider. A suction cup is fixedly connected to the opening of the rigid tube. A blade 2 is rotatably provided on one side of the flip plate. The real-time test software layer runs on the main control system. The real-time test software layer includes a human-machine interface, a test process management unit, a fault mark management unit, and a variable service unit. It is used to load and execute the circuit board test program. The test program includes a probe path planning module, a test point positioning module, a fault point coordinate recording module, and a mark execution control module. The data interaction and control layer uses a variable service unit to uniformly map test variables in the real-time test software layer to physical execution components in the distributed hardware layer, supporting test signal acquisition, probe displacement control, marker action triggering, and multi-component collaborative scheduling.

[0009] Preferably, one end of the crossbeam is threadedly connected to a threaded rod, both ends of which are rotatably mounted on a bracket. One end of the bracket is fixedly connected to a motor, the output end of which is fixedly connected to one end of the threaded rod. One end of the adjusting plate is threadedly connected to a threaded rod, both ends of which are rotatably mounted on the crossbeam. One side of the crossbeam is fixedly connected to a motor, the output end of which is fixedly connected to one end of the threaded rod. One side of the upper surface of the adjusting plate is fixedly connected to a cylinder, the piston end of which is fixedly connected to one end of a probe. One side of the probe is fixedly connected to a motor, the output end of which is fixedly connected to one end of a rotating rod. One side of the upper surface of the test platform is rotatably mounted with a bidirectional threaded rod, both sides of which are threadedly connected to two positioning blocks. One side of the upper surface of the test platform is fixedly connected to a motor, the output end of which is fixedly connected to one end of the bidirectional threaded rod.

[0010] Preferably, in the marking and isolation assembly, a motor is fixedly connected to one side of the upper end of the test bench, and the output end of the motor is fixedly connected to one end of the roller. A gear is rotatably arranged on one side of the upper end of the support column, and the gear meshes with a rack. A motor is fixedly connected to one side of the upper end of the support column, and the output end of the motor is fixedly connected to the gear. A cylinder is fixedly connected to one side of the fixed plate, and the piston end of the cylinder is fixedly connected to one side of the blade. Two support rods are fixedly connected to one side of the upper surface of the test bench, and a sliding column is fixedly connected to the upper end of each support rod. The two sliding columns are slidably connected to a pressure roller. A support roller is rotatably arranged on one side of each support rod. A spring is sleeved on one side of each sliding column, and one end of the spring is fixedly connected to one end of the pressure roller and the other end is fixedly connected to the end of the sliding column.

[0011] Preferably, a cylinder 2 is fixedly connected to one side of the upper end of the bracket 2, the piston end of the cylinder 2 is fixedly connected to one side of the crossbeam 2, and two bidirectional threaded rods 2 are rotatably provided on both sides of the crossbeam 2. Both ends of the bidirectional threaded rods 2 are rotatably provided on the crossbeam 2, and both sides of the bidirectional threaded rods 2 are threadedly connected to threaded blocks on both sides respectively. Two motors 7 are fixedly connected to both sides of the crossbeam 2, and the output ends of the two motors 7 are fixedly connected to the ends of the bidirectional threaded rods 2 on both sides respectively.

[0012] Preferably, a motor eight is fixedly connected to one end of the connecting block, and the output end of the motor eight is fixedly connected to one end of the flipping plate. A motor nine is fixedly connected to one side of the flipping plate, and the output end of the motor nine is fixedly connected to one end of the blade two. Two bidirectional threaded rods three are rotatably provided at both ends of one side of the flipping plate. The two sides of the bidirectional threaded rods three are respectively threaded to two sliders. A motor three is fixedly connected to one end of the flipping plate, and the output end of the motor three is fixedly connected to one end of the bidirectional threaded rods three. An air pump is fixedly connected to one side of the upper surface of the flipping plate. The air pump inlet is connected to a branch pipe, which is fixedly connected to the flipping plate. Both sides of the branch pipe are connected to flexible hoses, and one end of the flexible hose is connected to one side of the rigid pipe.

[0013] Preferably, the fault marking management unit in the real-time testing software layer supports fault point coordinate recording and storage functions. It can automatically generate fault point location information and map it to the movement trajectory of the probe based on the detection results of the flying probe tester, and control the marker pen to accurately mark the fault point.

[0014] Preferably, the data interaction and control layer realizes the collaborative scheduling of the test process through the variable service unit. When a fault point is detected, the current test process can be interrupted, the marking action can be executed first, and the test can be automatically resumed after the marking is completed, so as to achieve seamless connection between testing and marking.

[0015] Preferably, the real-time testing software layer includes a film marking control module. This module controls the gripper cylinder to pull the film to cover the circuit board according to the recorded fault point coordinates, and adjusts the marker pen to mark the corresponding position on the film to achieve non-contact fault point identification.

[0016] Preferably, the real-time testing software layer includes a thin film reinforcement control module, which controls the corner-mounted reinforcement components to cut, flare, and fix the thin film covering the circuit board surface at the four corners to ensure the relative position of the thin film and the circuit board is stable.

[0017] Preferably, the device supports batch testing mode, which can continuously perform automatic testing, fault point marking, and thin film covering reinforcement on multiple circuit boards, and store the test data and marking location information together to facilitate accurate positioning and traceability of subsequent repair work.

[0018] The beneficial effects of this invention are as follows: 1. The aircraft communication and navigation system integration testing device of this invention utilizes a marking component. Whenever a fault point is detected, it is automatically marked with a marker. When operators repair the circuit board subsequently, they only need to observe the marked location to accurately locate the fault point, thereby improving repair efficiency. Furthermore, compared to recording fault locations using computers or paper, this method eliminates the need for operators to repeatedly review and verify information, making it simple to operate and less prone to confusion.

[0019] 2. The aircraft communication and navigation system integration testing apparatus of this invention utilizes a marking isolation component, which achieves the marking effect while avoiding direct contact between the marker and the circuit board, thus preventing ink from seeping between component pins and solvent corrosion of the circuit board. Similarly, because the thin film surface is relatively flat compared to the circuit board surface, it improves the clarity of the markings and facilitates subsequent observation.

[0020] 3. The aircraft communication and navigation system integration test device of the present invention utilizes a corner-type reinforcement component. When the film is placed on the surface of the circuit board, slits are made at its four corners, and the slits are expanded and fitted onto the four corners of the circuit board. Thus, under the mutual constraint of the four corners of the film, the stability between the film and the circuit board is improved, avoiding film displacement and detachment, which is conducive to the stable progress of subsequent repair work.

[0021] 4. The aircraft communication and navigation system integrated testing device of the present invention, through a three-layer architecture design of distributed hardware layer, real-time test software layer and data interaction and control layer, organically integrates functions such as testing, marking, thin film covering and thin film reinforcement, realizing unified scheduling from hardware execution to software control, and avoiding the problems of functional fragmentation and poor coordination of traditional devices.

[0022] 5. The aircraft communication and navigation system integrated testing device of the present invention features a fault marking management unit in the real-time test software layer that works in conjunction with the data interaction control layer. It can automatically interrupt testing and perform marking when a fault point is detected, and seamlessly resume testing after completion, realizing an integrated automatic process of testing and marking, significantly improving batch testing efficiency. The fault point coordinate information is associated and stored with the test data through a variable service unit, facilitating accurate positioning during subsequent repairs and avoiding the problems of confusion and errors associated with manual recording. The real-time test software layer supports flexible configuration and secondary development of test programs, allowing adjustment of parameters such as probe paths and marking strategies according to the testing requirements of different circuit board models. The modular design of the distributed hardware layer also facilitates future functional expansion and hardware upgrades. The device supports continuous automatic testing, marking, and thin-film covering reinforcement of multiple circuit boards, and associates and stores test data with marking location information to form a complete test record archive, providing data support for quality traceability and process improvement. Attached Figure Description

[0023] The invention will now be further described with reference to the accompanying drawings.

[0024] Figure 1 This is a system architecture block diagram of the present invention; Figure 2 This is a three-dimensional structural schematic diagram of the present invention; Figure 3This is a schematic diagram of the hidden three-dimensional structure of the test bench of the present invention; Figure 4 It is a three-dimensional structural diagram showing the positional relationship between the roller, the fixed plate, the circuit board, and the support column; Figure 5 This is a schematic diagram of the three-dimensional structure at the roller. Figure 6 This is a schematic diagram of the three-dimensional structure at the fixed plate. Figure 7 This is a schematic diagram of the three-dimensional structure at the support column; Figure 8 This is a schematic diagram of a three-dimensional structure of the support frame; Figure 9 This is a schematic diagram of the three-dimensional structure of the two beams; Figure 10 This is a schematic diagram of the three-dimensional structure at the probe location; Figure 11 This is a schematic diagram of the three-dimensional structure at the connecting block; Figure 12 This is a schematic diagram of the three-dimensional structure at another perspective of the connecting block.

[0025] In the diagram: 1. Test bench; 2. Support 1; 3. Roller; 4. Film; 5. Crossbeam 1; 6. Support 2; 7. Crossbeam 2; 8. Threaded block; 9. Support column; 10. Rack; 11. Tilting plate; 12. Cylinder 2; 13. Motor 1; 14. Pressure roller; 15. Support roller; 16. Sliding column; 17. Support rod; 18. Spring; 19. Fixing plate; 20. Positioning block; 21. Cylinder 3; 22. Guide rod 1; 23. Blade 1; 24. Bidirectional threaded rod 1; 25. Motor 2; 26. Rotating rod; 27. Marker pen; 28. Motor 3; 29. ​​Motor 4; 30. Gear; 31. Support plate; 32. Grip cylinder; 33. Motor 5; 34. Threaded rod 1; 35. Flying needle Tester; 36. Threaded rod II; 37. Motor VI; 38. Probe; 39. Cylinder IV; 40. Guide rod II; 41. Adjusting plate; 42. Motor VII; 43. Bidirectional threaded rod II; 44. Connecting block; 45. Cylinder V; 46. Motor VIII; 47. Bidirectional threaded rod III; 48. Slider; 49. Rigid tube; 50. Suction cup; 51. Blade II; 52. Hose; 53. Branch tube; 54. Air pump; 55. Motor IX; 56. Motor X; 100. Distributed hardware layer; 200. Real-time test software layer; 300. Data interaction and control layer; 202. Human-machine interface; 203. Test process management unit; 204. Fault marking management unit; 205. Variable service unit. Detailed Implementation

[0026] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] Please refer to Figures 1-12 This invention provides a technical solution: an integrated testing apparatus for an aircraft communication and navigation system, comprising: Distributed hardware layer 100, real-time test software layer 200 and data interaction and control layer 300; The distributed hardware layer 100 includes a test bench 1, a test component integrated on the test bench 1, a marking component, a circuit board centering positioning component, a marking isolation component, and a corner reinforcement component; The test assembly includes a bracket 2 fixedly connected to one side of the upper surface of the test bench 1. A crossbeam 5 is slidably arranged on one side of the bracket 2. An adjustment plate 41 is slidably arranged on one side of the crossbeam 5. Two guide rods 40 are slidably connected to one side of the adjustment plate 41. A probe 38 is fixedly connected to the lower end of the guide rods 40. A flying probe tester 35 is arranged on one side of the upper surface of the adjustment plate 41. The probe 38 is electrically connected to the flying probe tester 35. The marking assembly includes a rotating rod 26 rotatably disposed on one side of the probe 38, with a marker pen 27 fixedly connected to one end of the rotating rod 26; The circuit board centering and positioning component includes two positioning blocks 20, both of which are slidably connected to the upper surface of the test bench 1. The marking and isolation assembly includes a roller 3 rotatably mounted on one side of the upper end of the test bench 1, a film 4 wound on the roller 3, a support column 9 fixedly connected to one side of the upper end of the test bench 1, a rack 10 slidably connected to one side of the upper end of the support column 9, a support plate 31 fixedly connected to one end of the rack 10, two gripper cylinders 32 fixedly connected to one side of the support plate 31, a fixing plate 19 fixedly connected to one side of the upper end of the test bench 1, two guide rods 22 slidably connected to the fixing plate 19, and a blade 23 fixedly connected to the upper end of the guide rods 22. The corner-type reinforcement assembly includes two brackets 6 fixedly connected to one side of the upper surface of the test bench 1. The two brackets 6 are slidably connected to a crossbeam 7. Two threaded blocks 8 are slidably connected on both sides of the crossbeam 7. A cylinder 45 is fixedly connected to one side of the threaded block 8. A connecting block 44 is fixedly connected to the piston end of the cylinder 45. A flip plate 11 is rotatably connected to one side of the connecting block 44. Two sliders 48 are slidably connected to one side of the flip plate 11. A rigid tube 49 is fixedly connected to the lower end of the slider 48. A suction cup 50 is fixedly connected to the opening of the rigid tube 49. A blade 51 is rotatably connected to one side of the flip plate 11. The real-time test software layer 200 runs on the main control system. The real-time test software layer 200 includes a human-machine interface 202, a test process management unit 203, a fault mark management unit 204, and a variable service unit 205. It is used to load and execute the circuit board test program. The test program includes a probe path planning module, a test point positioning module, a fault point coordinate recording module, and a mark execution control module. The data interaction and control layer 300 uses the variable service unit to uniformly map the test variables in the real-time test software layer to the physical execution components of the distributed hardware layer, supporting test signal acquisition, probe displacement control, marker action triggering, and multi-component collaborative scheduling.

[0028] A threaded rod 34 is threaded to one end of the crossbeam 5. Both ends of the threaded rod 34 are rotatably mounted on the bracket 2. A motor 33 is fixedly connected to one end of the bracket 2. The output end of the motor 33 is fixedly connected to one end of the threaded rod 34. A threaded rod 36 is threaded to one end of the adjusting plate 41. Both ends of the threaded rod 36 are rotatably mounted on the crossbeam 5. A motor 37 is fixedly connected to one side of the crossbeam 5. The output end of the motor 37 is fixedly connected to one end of the threaded rod 36. The upper end of the adjusting plate 41... A cylinder 39 is fixedly connected to one side of the test bench 1. The piston end of the cylinder 39 is fixedly connected to one end of the probe 38. A motor 56 is fixedly connected to one side of the probe 38. The output end of the motor 56 is fixedly connected to one end of the rotating rod 26. A bidirectional threaded rod 24 is rotatably installed on one side of the upper end of the test bench 1. The two sides of the bidirectional threaded rod 24 are threadedly connected to two positioning blocks 20 respectively. A motor 25 is fixedly connected to one side of the upper end of the test bench 1. The output end of the motor 25 is fixedly connected to one end of the bidirectional threaded rod 24.

[0029] In the marking and isolation assembly, a motor 13 is fixedly connected to one side of the upper end of the test bench 1. The output end of the motor 13 is fixedly connected to one end of the roller 3. A gear 30 is rotatably installed on one side of the upper end of the support column 9. The gear 30 meshes with the rack 10. A motor 29 is fixedly connected to one side of the upper end of the support column 9. The output end of the motor 29 is fixedly connected to the gear 30. A cylinder 21 is fixedly connected to one side of the fixed plate 19. The piston end of the cylinder 21 is fixedly connected to one side of the blade 23. Two support rods 17 are fixedly connected to one side of the upper surface of the test bench 1. A sliding column 16 is fixedly connected to the upper end of the support rods 17. The two sliding columns 16 are slidably connected to the pressure roller 14. A support roller 15 is rotatably installed on one side of the two support rods 17. A spring 18 is sleeved on one side of the sliding column 16. One end of the spring 18 is fixedly connected to one end of the pressure roller 14, and the other end is fixedly connected to the end of the sliding column 16.

[0030] A cylinder 12 is fixedly connected to one side of the upper end of bracket 26. The piston end of cylinder 12 is fixedly connected to one side of crossbeam 27. Two bidirectional threaded rods 43 are rotatably installed on both sides of crossbeam 27. Both ends of the bidirectional threaded rods 43 are rotatably installed on crossbeam 27. Both sides of the bidirectional threaded rods 43 are threadedly connected to the threaded blocks 8 on both sides. Two motors 42 are fixedly connected to both sides of crossbeam 27. The output ends of the two motors 42 are fixedly connected to the ends of the bidirectional threaded rods 43 on both sides.

[0031] One end of the connecting block 44 is fixedly connected to a motor 8 46. The output end of the motor 8 46 is fixedly connected to one end of the flip plate 11. One side of the flip plate 11 is fixedly connected to a motor 9 55. The output end of the motor 9 55 is fixedly connected to one end of the blade 2 51. Two bidirectional threaded rods 3 47 are rotatably set at both ends of one side of the flip plate 11. The two sides of the bidirectional threaded rods 3 47 are threadedly connected to two sliders 48 respectively. One end of the flip plate 11 is fixedly connected to a motor 3 28. The output end of the motor 3 28 is fixedly connected to one end of the bidirectional threaded rod 3 47. One side of the upper surface of the flip plate 11 is fixedly connected to an air pump 54. The air inlet of the air pump 54 is connected to a branch pipe 53. The branch pipe 53 is fixedly connected to the flip plate 11. Both sides of the branch pipe 53 are connected to hoses 52. One end of the hose 52 is connected to one side of the rigid pipe 49.

[0032] The fault marking management unit in the real-time test software layer 200 supports the function of recording and storing fault point coordinates. It can automatically generate fault point location information and map it to the motion trajectory of the probe 38 based on the detection results of the flying probe tester 35, and control the marker pen 27 to accurately mark the fault point.

[0033] The data interaction and control layer 300 achieves collaborative scheduling of the test process through the variable service unit. When a fault point is detected, the current test process can be interrupted, the marking action can be executed first, and the test can be automatically resumed after the marking is completed, thus achieving seamless connection between testing and marking.

[0034] The real-time test software layer 200 includes a film marking control module. This module controls the gripper cylinder 32 to pull the film 4 to cover the circuit board according to the recorded fault point coordinates, and adjusts the marker pen 27 to mark the corresponding position on the film 4 to achieve non-contact fault point identification.

[0035] The real-time test software layer 200 includes a thin film reinforcement control module, which controls the corner-mounted reinforcement components to cut, flare, and fix the thin film 4 covering the circuit board surface at the four corners, ensuring that the relative position of the thin film 4 and the circuit board is stable.

[0036] The device supports batch testing mode, enabling continuous automatic testing, fault point marking, and thin-film reinforcement of multiple circuit boards. It also associates and stores test data with the marked location information, facilitating accurate positioning and traceability in subsequent repair work.

[0037] Specifically, the distributed hardware layer 100 serves as the physical foundation of the entire device, integrating testing components, marking components, circuit board centering and positioning components, marking isolation components, and corner-mounted reinforcement components. Each component is equipped with an independent drive execution unit (motor, cylinder, etc.), which is integrated onto the test bench 1 through standardized mechanical and electrical interfaces, forming a modular and scalable hardware platform.

[0038] The real-time test software layer 200 runs on the main control system and is the core of human-computer interaction and test logic. The human-computer interface provides functions such as test parameter setting, status monitoring, and data display; the test process management unit is responsible for loading test programs and scheduling test tasks; the fault marking management unit records the coordinates of fault points detected by the flying probe tester 35 in real time and generates marking instructions; the variable service unit acts as a data bridge between the software layer and the hardware layer, converting test variables (such as probe target positions, marker trigger signals, etc.) into standardized control instructions.

[0039] The data interaction and control layer 300 achieves precise mapping between software variables and hardware physical interfaces through the variable service unit. When the real-time test software layer 200 generates test instructions, the data interaction and control layer 300 converts them into specific action sequences of actuators such as motors and cylinders. After the hardware components complete their actions, their status information is fed back to the real-time test software layer 200 via the data interaction and control layer 300, thus achieving closed-loop control.

[0040] The circuit board to be tested is placed between two positioning blocks 20. Then, the motor 25 drives the bidirectional threaded rod 24 to rotate, so that the two positioning blocks 20 move closer to each other and clamp the circuit board.

[0041] Subsequently, motor 533 drives threaded rod 134 to rotate, causing crossbeam 15 to slide on bracket 12. Motor 637 drives threaded rod 236 to rotate, causing adjustment plate 41 to slide on crossbeam 15. Cylinder 439 drives probe 38 to rise and fall, thereby adjusting the position of probe 38 in the x, y, and z axes, so that probe 38 contacts each test point on the circuit board. The test results are displayed on the screen in real time.

[0042] When the flying probe tester (35) detects a fault point, the fault marking management unit of the real-time test software layer (200) immediately records the coordinates of the point and sends a coordinated command to the probe (38) and the marker pen (27) through the data interaction and control layer (300): First, the probe (38) is controlled to move upward away from the circuit board. Then, the motor (56) drives the rotating rod (26) to rotate the marker pen (27) to vertical downward. Then, according to the recorded coordinates, the probe (38) is controlled to move above the fault point, and the cylinder (39) pushes the marker pen (27) downward to complete the marking. Throughout the process, the test process management unit of the real-time test software layer (200) is responsible for coordinating the timing of testing and marking, ensuring that the test process is automatically restored after marking is completed, and achieving seamless connection between testing and marking. After completing one marking operation, the marker pen 27 is reset, without affecting the subsequent testing work of the probe 38. Then, the above operation is repeated. Whenever a fault point is detected, it is automatically marked with marker 27. When the operator repairs the circuit board later, they only need to observe the marked position to accurately locate the fault point, thereby improving repair efficiency. In addition, compared with recording the fault location using a computer or paper, this method saves the operator from repeatedly flipping through and checking the records, making it simple to operate and less prone to confusion.

[0043] In the initial state, the end of the film 4 is located between the pressure roller 14 and the support roller 15, and the pressure roller 14 presses the film 4 down under the action of the spring 18.

[0044] When a fault point is detected, the system first records its coordinates. After all test points on the circuit board have been tested, motor 29 drives gear 30 to rotate, which in turn drives rack 10 to slide laterally on support 9, causing gripper cylinder 32 to move to the edge of film 4. Then, gripper cylinder 32 clamps the end of film 4. Subsequently, gripper cylinder 32 pulls the end of film 4 to the right, while motor 13 drives roller 3 to rotate, unwinding film 4 until it covers the top of the circuit board. At this point, the system readjusts the position of marker pen 27 based on the recorded fault point coordinates and marks the film 4 with the marked points corresponding to the fault points on the circuit board below. After marking is completed... Then, cylinder 321 drives blade 23 to rise, cutting the film 4. At this point, gripper cylinder 32 releases the film 4, and the cut film 4 falls onto the circuit board surface. The operator can then remove the film 4 and the circuit board together. During subsequent repair work, the operator can observe the markings on the film 4 to locate the circuit fault. This achieves the marking effect while avoiding direct contact between the marker pen 27 and the circuit board, preventing ink from seeping between component leads and solvent corrosion of the circuit board. Similarly, since the surface of the film 4 is relatively flat compared to the circuit board surface, it improves the clarity of the markings and facilitates subsequent observation.

[0045] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. An integrated testing apparatus for an aircraft communication and navigation system, characterized in that, include: Distributed hardware layer (100), real-time test software layer (200), and data interaction and control layer (300). The distributed hardware layer (100) includes a test bench (1), a test component, a marking component, a circuit board centering positioning component, a marking isolation component, and a corner reinforcement component integrated on the test bench (1); The test assembly includes a bracket (2) fixedly connected to one side of the upper surface of the test bench (1), a crossbeam (5) slidably arranged on one side of the bracket (2), an adjustment plate (41) slidably arranged on one side of the crossbeam (5), two guide rods (40) slidably connected on one side of the adjustment plate (41), a probe (38) fixedly connected to the lower end of the guide rods (40), a flying needle tester (35) arranged on one side of the upper surface of the adjustment plate (41), and the probe (38) electrically connected to the flying needle tester (35). The marking assembly includes a rotating rod (26) rotatably disposed on one side of the probe (38), and a marker pen (27) is fixedly connected to one end of the rotating rod (26). The circuit board centering positioning component includes two positioning blocks (20), both of which are slidably connected to the upper surface of the test bench (1); The marking and isolation assembly includes a roller (3) rotatably mounted on one side of the upper end of the test bench (1), a film (4) wound on the roller (3), a support column (9) fixedly connected to one side of the upper end of the test bench (1), a rack (10) slidably connected to one side of the upper end of the support column (9), a support plate (31) fixedly connected to one end of the rack (10), two gripper cylinders (32) fixedly connected to one side of the support plate (31), a fixing plate (19) fixedly connected to one side of the upper end of the test bench (1), two guide rods (22) slidably connected to the fixing plate (19), and a blade (23) fixedly connected to the upper end of the guide rods (22). The corner-type reinforcement assembly includes two brackets (6) fixedly connected to one side of the upper surface of the test bench (1). The two brackets (6) are slidably provided with a crossbeam (7). Two threaded blocks (8) are slidably provided on both sides of the crossbeam (7). A cylinder (45) is fixedly connected to one side of the threaded block (8). A connecting block (44) is fixedly connected to the piston end of the cylinder (45). A flip plate (11) is rotatably provided on one side of the connecting block (44). Two sliders (48) are slidably connected to one side of the flip plate (11). A rigid tube (49) is fixedly connected to the lower end of the slider (48). A suction cup (50) is fixedly connected to the opening of the rigid tube (49). A blade (51) is rotatably provided on one side of the flip plate (11). The real-time test software layer (200) runs on the main control system. The real-time test software layer (200) includes a human-machine interface (202), a test process management unit (203), a fault mark management unit (204), and a variable service unit (205), which are used to load and execute the circuit board test program. The test program includes a probe path planning module, a test point positioning module, a fault point coordinate recording module, and a mark execution control module. The data interaction and control layer (300) uses a variable service unit to uniformly map the test variables in the real-time test software layer to the physical execution components of the distributed hardware layer, supporting test signal acquisition, probe displacement control, marker action triggering, and multi-component collaborative scheduling.

2. The aircraft communication and navigation system integration test apparatus according to claim 1, characterized in that: One end of the crossbeam (5) is threadedly connected to a threaded rod (34), both ends of which are rotatably mounted on the bracket (2). One end of the bracket (2) is fixedly connected to a motor (33), the output end of which is fixedly connected to one end of the threaded rod (34). One end of the adjusting plate (41) is threadedly connected to a threaded rod (36), both ends of which are rotatably mounted on the crossbeam (5). One side of the crossbeam (5) is fixedly connected to a motor (37), the output end of which is fixedly connected to one end of the threaded rod (36). The adjusting plate (41) is threadedly connected to a threaded rod (36), both ends of which are rotatably mounted on the crossbeam (5). One side of the crossbeam (5) is fixedly connected to a motor (37), the output end of which is fixedly connected to one end of the threaded rod (36). 1) A cylinder four (39) is fixedly connected to one side of the upper end face. The piston end of the cylinder four (39) is fixedly connected to one end of the probe (38). A motor ten (56) is fixedly connected to one side of the probe (38). The output end of the motor ten (56) is fixedly connected to one end of the rotating rod (26). A bidirectional threaded rod one (24) is rotatably set on one side of the upper end of the test bench (1). The two sides of the bidirectional threaded rod one (24) are threadedly connected to two positioning blocks (20) respectively. A motor two (25) is fixedly connected to one side of the upper end of the test bench (1). The output end of the motor two (25) is fixedly connected to one end of the bidirectional threaded rod one (24).

3. The aircraft communication and navigation system integration test apparatus according to claim 1, characterized in that: In the marking and isolation assembly, a motor (13) is fixedly connected to one side of the upper end of the test bench (1), and the output end of the motor (13) is fixedly connected to one end of the roller (3). A gear (30) is rotatably installed on one side of the upper end of the support column (9), and the gear (30) meshes with the rack (10). A motor (29) is fixedly connected to one side of the upper end of the support column (9), and the output end of the motor (29) is fixedly connected to the gear (30). A cylinder (21) is fixedly connected to one side of the fixing plate (19). The piston end is fixedly connected to one side of the blade (23); two support rods (17) are fixedly connected to one side of the upper surface of the test bench (1), and a sliding column (16) is fixedly connected to the upper end of the support rod (17). The two sliding columns (16) are slidably connected to the pressure roller (14). The two support rods (17) are rotatably connected to one side of the support roller (15). A spring (18) is sleeved on one side of the sliding column (16). One end of the spring (18) is fixedly connected to one end of the pressure roller (14), and the other end is fixedly connected to the end of the sliding column (16).

4. The aircraft communication and navigation system integration test apparatus according to claim 1, characterized in that: A cylinder 2 (12) is fixedly connected to one side of the upper end of the bracket 2 (6). The piston end of the cylinder 2 (12) is fixedly connected to one side of the crossbeam 2 (7). Two bidirectional threaded rods 2 (43) are rotatably arranged on both sides of the crossbeam 2 (7). Both ends of the bidirectional threaded rods 2 (43) are rotatably arranged on the crossbeam 2 (7). Both sides of the bidirectional threaded rods 2 (43) are threadedly connected to the threaded blocks (8) on both sides. Motors 7 (42) are fixedly connected to both sides of the crossbeam 2 (7). The output ends of the two motors 7 (42) are fixedly connected to the ends of the two bidirectional threaded rods 2 (43) on both sides.

5. The aircraft communication and navigation system integration test apparatus according to claim 1, characterized in that: One end of the connecting block (44) is fixedly connected to a motor eight (46), the output end of the motor eight (46) is fixedly connected to one end of the flip plate (11), one side of the flip plate (11) is fixedly connected to a motor nine (55), the output end of the motor nine (55) is fixedly connected to one end of the blade two (51), and two ends of one side of the flip plate (11) are rotatably provided with a bidirectional threaded rod three (47), the two sides of the bidirectional threaded rod three (47) are respectively threadedly connected to two sliders (48), the... A motor (28) is fixedly connected to one end of the flip plate (11). The output end of the motor (28) is fixedly connected to one end of the bidirectional threaded rod (47). An air pump (54) is fixedly connected to one side of the upper surface of the flip plate (11). The air inlet of the air pump (54) is connected to a branch pipe (53). The branch pipe (53) is fixedly connected to the flip plate (11). Both sides of the branch pipe (53) are connected to flexible hoses (52). One end of the flexible hose (52) is connected to one side of the rigid pipe (49).

6. The aircraft communication and navigation system integration test apparatus according to claim 5, characterized in that: The fault marking management unit in the real-time test software layer (200) supports fault point coordinate recording and storage functions. It can automatically generate fault point location information and map it to the motion trajectory of the probe (38) based on the detection results of the flying probe tester (35), and control the marker pen (27) to accurately mark the fault point.

7. The aircraft communication and navigation system integration test apparatus according to claim 5, characterized in that: The data interaction and control layer (300) realizes the collaborative scheduling of the test process through the variable service unit. When a fault point is detected, the current test process can be interrupted, the marking action can be executed first, and the test can be automatically resumed after the marking is completed, so as to achieve seamless connection between testing and marking.

8. The aircraft communication and navigation system integration test apparatus according to claim 1, characterized in that: The real-time test software layer (200) includes a film marking control module. This module controls the gripper cylinder (32) to pull the film (4) to cover the circuit board according to the recorded fault point coordinates, and adjusts the marker pen (27) to mark the corresponding position of the film (4) to realize non-contact fault point identification.

9. The aircraft communication and navigation system integration test apparatus according to claim 8, characterized in that: The real-time test software layer (200) includes a thin film reinforcement control module, which controls the corner-mounted reinforcement component to cut, flare, and fix the thin film (4) covering the surface of the circuit board at four corners to ensure that the relative position of the thin film (4) and the circuit board is stable.

10. The aircraft communication and navigation system integration test apparatus according to claim 8, characterized in that: The device supports batch testing mode, which can continuously perform automatic testing, fault point marking, and thin film covering reinforcement on multiple circuit boards, and store the test data and marking location information together to facilitate accurate positioning and traceability of subsequent repair work.

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