Aircraft cabin air intake duct endurance test device and method

Abstract

The application discloses a kind of aircraft cabin air inlet duct endurance test device and test method, including rack, rack is equipped with installation box, installation box is installed main switch, power supply, stop / reset switch, counter display screen, ECU controller, rack is installed with linear slide table unit, rotating execution unit, pneumatic clamping unit, position detection unit, counting unit;Linear slide table unit carries rotating execution unit and moves on slide table support by linear slide table;The output end of rotating execution unit is installed pneumatic clamping unit, and the pull line end of aircraft cabin air inlet duct to be tested is clamped by pneumatic clamping unit through air clamp;Slide table support is provided with fixed position detection unit, and position detection unit monitors the position of linear slide table;ECU controller controls and executes work action and collects relevant test information.The application realizes the full-process automation of pull line type component endurance test, can continuously complete tens of thousands of cycle tests, does not need artificial continuous on duty, and greatly reduces artificial cost and operation intensity.

Description

Technical Field

[0001] This invention relates to the field of air intake duct testing, specifically to a durability testing device and method for aircraft cockpit air intake ducts. Background Technology

[0002] In the field of aircraft manufacturing and maintenance, the cockpit air intake duct is a crucial component of the environmental control system, and its mechanical durability directly impacts flight safety. During takeoff, landing, and maneuvering, the cockpit air intake duct is frequently subjected to combined tensile and torsional loads, which can easily lead to fatigue damage or fracture failure after prolonged repeated stress. Therefore, conducting durability tests on the manufactured or repaired cockpit air intake duct is a critical step in ensuring the safe operation of aircraft.

[0003] Currently, durability testing of aircraft cockpit air intake ducts primarily relies on manual operation. Testers must repeatedly pull the duct connection cable while simultaneously performing a rotational motion, with a single test typically requiring tens of thousands of cycles. However, manual operation is labor-intensive, making it difficult to maintain a stable frequency and amplitude of movements over extended periods, resulting in inconsistent test results. Furthermore, manual testing is time-consuming and inefficient, failing to meet the efficiency requirements of mass production and maintenance cycles. While there are existing solutions using general-purpose robotic arms for automated testing, these robotic arms are expensive, and programming specific motion sequences for the air intake duct is complex, lacking specialization and hindering widespread adoption.

[0004] In summary, existing durability testing equipment for similar air ducts, pipelines, and components suffers from problems such as simple motion simulation, lack of push-pull-rotation combined linkage, lack of precise position detection and limit switches, excessive manual intervention, and insufficient counting accuracy. These issues prevent the equipment from meeting the requirements for standardized durability testing of tens of thousands of cycles for the air intake duct cables in aircraft cockpits. Summary of the Invention

[0005] To overcome the shortcomings of the prior art, this invention provides a durability testing device and method for aircraft cockpit air intake ducts, which can simulate manual "pulling-rotating" compound actions, automatically perform cyclic testing, and has automatic counting and position detection functions, so as to solve the problems existing in the prior art.

[0006] To address the problems of the existing technology, the technical solution of this invention patent is as follows: A durability testing device for an aircraft cockpit air intake duct includes a frame, a mounting box on the frame, and a main switch, a power supply, a stop / reset switch, a counter display screen, and an ECU controller mounted on the mounting box. The frame is equipped with a linear slide unit, a rotary execution unit, a pneumatic clamping unit, a position detection unit, and a counting unit; The frame is equipped with an adjustment support, on which a slide bracket is hinged and an angle adjuster is rotatably installed. The angle adjuster adjusts the angle of the slide bracket. The linear slide unit includes a slide support, and the linear slide of the linear slide unit carries a rotary actuator that moves on the slide support. A pneumatic clamping unit is installed at the output end of the rotary actuator. The pneumatic clamping unit clamps the cable end of the cockpit air intake duct of the aircraft to be tested using pneumatic clamps. The slide support is equipped with a fixed position detection unit, which monitors the position of the linear slide. The ECU controller controls and executes the working actions of the linear slide unit, rotary actuator, pneumatic clamping unit, position detection unit, and counting unit, and collects relevant test information.

[0007] Furthermore, a slide block is slidably mounted on the adjusting support, and the slide block is connected to the slide table bracket via connecting rods hinged at both ends; an adjusting screw is rotatably mounted on the adjusting support, and the outer end of the adjusting screw is connected to the angle adjuster, passes through the slide block, and is screwed into it.

[0008] Furthermore, the two ends of the slide bracket are rotatably mounted with a drive screw and a slide rod via two uprights. A linear slide is slidably mounted on the slide rod. The drive screw passes through the linear slide and engages with it. The drive screw is driven by a drive motor fixedly mounted on the uprights to adjust the position of the linear slide on the slide bracket.

[0009] Furthermore, the rotary actuator is fixedly mounted on the linear slide, and includes a fixedly mounted servo motor. The output end of the servo motor is mounted on the pneumatic clamping unit via a pneumatic clamp bracket.

[0010] Furthermore, the pneumatic clamping unit includes a set of fixedly installed air clamp brackets, on which air clamps are installed. The air clamps are powered by an external air pump and controlled by a relay.

[0011] Furthermore, the position detection unit includes a front limit switch and a rear limit switch fixedly mounted on the slide bracket; when the linear slide triggers the front limit switch or the rear limit switch, it sends a trigger signal to the ECU controller, and the ECU controller controls the rotary actuator to perform rotation.

[0012] Furthermore, when the linear slide triggers the front limit switch, the trigger signal sent by the front limit switch is linked to the counting unit of the ECU controller for counting.

[0013] Furthermore, the position detection unit includes a distance-type photoelectric switch fixedly mounted on the slide bracket, and the distance-type photoelectric switch is electrically connected to the ECU controller.

[0014] A testing method based on a testing device, characterized in that: Includes the following steps: The first step is to fix the main body of the aircraft cockpit air intake duct in the tooling position, control the relay to turn on, and put the end of the cable to be tested into the pneumatic clamping unit and clamp it tightly. The second step is that the ECU controller controls the linear slide unit to move backward. When the linear slide moves into the detection range of the distance photoelectric switch, the distance photoelectric switch sends a trigger signal to the ECU controller, and the ECU controller controls the rotary actuator to perform a rotation action at a set angle. Third, after the rotary actuator completes its rotation, the ECU controller controls the linear slide unit to continue moving backward until it touches the rear limit switch and immediately stops moving backward; the rear limit switch sends a signal to the ECU controller, and the ECU controller controls the rotary actuator to perform a rotational action of a set angle and then performs a reverse rotation reset. Fourth, after the rotary actuator is reset, the ECU controller controls the linear slide unit to start moving forward. When it passes the distance-type photoelectric switch again, it is triggered a second time. The ECU controller then controls the rotary actuator to perform the rotation action of the set angle again. After the rotation action is completed, the linear slide continues to move forward until it touches the front limit switch. Fifth, after the front limit switch is triggered, the counting unit completes one count, which means that a complete set of endurance cycle actions has been completed; the ECU controller automatically resets all mechanisms, and the equipment immediately enters the next cycle.

[0015] Furthermore, the counting unit is a pulse counter, with its input end connected to the front limit switch and its output end connected to the counter display screen; Each time the front limit switch is triggered and closed, the durability cycle action in step five is recorded as one test count, and the corresponding counter display automatically increments by one.

[0016] Compared with existing technologies, the advantages of this invention patent are as follows: This invention automates the entire process of durability testing for wire-type components, enabling continuous testing of tens of thousands of cycles without the need for continuous human supervision, thus significantly reducing labor costs and workload. The equipment is controlled by a controller that uniformly manages the timing of actions, translation speed, rotation angle, and travel distance. All test conditions are kept highly consistent, effectively improving the repeatability and accuracy of test data.

[0017] The system uses a front limit switch linked to a counter for automatic counting, completely eliminating errors caused by manual counting and ensuring precise control over the number of tests. The combination of photoelectric switch mid-travel triggering action and mechanical micro-motion limit protection not only realizes the automatic switching of translation and rotation actions, but also prevents overtravel movement, effectively protecting various test components and pull wires; The pneumatic grippers are easy to use, and the equipment parameters can be flexibly adjusted. They can adapt to the testing needs of different specifications of pull wires, pipeline fittings and different test standards, making them highly versatile. The various actions are automatically linked by the program, and the process is coherent and orderly, which significantly improves the overall work efficiency of durability testing. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of the present invention. Figure 2 This is a partial structural schematic diagram of the testing device of this invention. Figure 3 This is a schematic diagram illustrating the working principle of the control method of the present invention. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0020] The aircraft cockpit air intake duct durability testing device provided in this embodiment has all electrical and mechanical components mounted on the frame 1, including the mounting box 2. The mounting box 2 is equipped with a main switch 3, a power supply 4, a stop / reset switch 5, and an ECU controller 9. An adjustment support 6 is provided on the frame 1. A slide bracket 7 is hinged to the adjustment support 6, and an angle adjuster 8 is rotatably installed on the adjustment support 6. A slide block 61 is slidably installed on the adjustment support 6, and the slide block 61 is connected to the slide bracket 7 through a connecting rod 62 hinged at both ends. An adjustment screw 63 is rotatably installed on the adjustment support 6. The outer end of the adjustment screw 63 is connected to the angle adjuster 8, passes through the slide block 61 and is screwed into it. The angle adjuster 8 adjusts the angle of the slide bracket 7 through the adjustment screw 63, the slide block 61 and the connecting rod 62. The linear slide unit includes a slide bracket 7. The two ends of the slide bracket 7 are rotatably mounted with a drive screw 72 and a slide rod 73 via two uprights 71. The linear slide 14 is slidably mounted on the slide rod 73. The drive screw 72 passes through the linear slide 14 and is screwed into it. The drive screw 72 is driven by a drive motor 16 fixedly mounted on the upright 71 to adjust the position of the linear slide 14 on the slide bracket 7 and achieve smooth forward and backward linear movement. The rotary actuator is fixedly mounted on the linear slide 14. It includes a servo motor 17 fixedly mounted on the linear slide 14 via a servo motor bracket 25. The output end of the servo motor 17 is mounted on a pneumatic clamping unit via a pneumatic clamp bracket 18. The pneumatic clamping unit clamps the end 13 of the cable 12 of the cockpit air intake duct 11 of the aircraft to be tested via a pneumatic clamp 10. The pneumatic clamping unit consists of a pneumatic clamp 10 and a cylinder-controlled relay 15. The pneumatic clamp 10 uses a standard pneumatic gripper, and the relay 15 controls the air circuit to clamp and release the end 13 of the pull wire 12. Servo motor 17 is fixed above linear slide table 14 by mounting plate, and air clamp 10 is fixed on output shaft of servo motor 17 by air clamp bracket 17. Servo motor 17 can drive air clamp 10 and cable 12 to rotate synchronously.

[0021] The slide bracket 7 is equipped with a fixed position detection unit, which includes a front limit switch 19 and a rear limit switch 20 fixedly installed on the slide bracket 7. When the linear slide 14 moves back and forth, the servo bracket 25 triggers the front limit switch 19 or the rear limit switch 20, and sends a trigger signal to the ECU controller 9. The ECU controller 9 controls the servo 17 of the rotary actuator to perform rotation. In the position detection unit, the distance-type photoelectric switch 21 is fixed on the slide bracket 7 by the photoelectric switch bracket 24. The detection distance is used as the basis for judging whether the rotary actuator rotates. When the linear slide 14 moves into the sensing range of the distance-type photoelectric switch 21, the distance-type photoelectric switch 21 immediately outputs an electrical signal to the ECU controller 9.

[0022] The testing method of the testing device in this embodiment includes the following steps: The first step is to fix the main body of the aircraft cockpit air intake duct 11 in the tooling position, and the ECU controller 9 controls the relay 15 to conduct. Then, the end 13 of the pull wire 12 to be tested is placed into the pneumatic clamping unit and clamped and secured. In the second step, the ECU controller 9 controls the linear slide unit to move backward. When the linear slide 14 moves into the detection range of the distance photoelectric switch 21, the distance photoelectric switch 21 sends a trigger signal to the ECU controller 9, and the ECU controller 9 controls the rotary actuator to perform a rotational action at a set angle. Third, after the rotary actuator completes its rotation, the ECU controller 9 controls the linear slide unit to continue moving backward until it touches the rear limit switch 20 and immediately stops moving backward; the rear limit switch 20 sends a signal to the ECU controller 9, and the ECU controller 9 controls the rotary actuator to perform a rotation action of a set angle and then performs a reverse rotation reset. Fourth step: After the rotary actuator is reset, the ECU controller 9 controls the linear slide unit to start moving forward. When it passes the distance photoelectric switch 21 again, it is triggered a second time. The ECU controller 9 controls the rotary actuator to perform the rotation action of the set angle again. After the rotation action is completed, the linear slide 14 continues to move forward until it touches the front limit switch 20. Fifth, after the front limit switch 20 is triggered, the counting unit completes one count, which means that a complete set of endurance cycle actions has been completed; the ECU controller 9 automatically resets all mechanisms, and the equipment immediately enters the next cycle.

[0023] The counting unit uses a pulse counter 22, whose input is connected to the front limit switch 19 and whose output is connected to the counter display screen 23. Each time the front limit switch 19 is triggered and closed, the durability cycle action in step five is recorded as one test count. At this time, it represents that a complete set of durability cycle actions has been completed, and the corresponding counter display screen 23 automatically increments the displayed number. The ECU controller 9 automatically resets all mechanisms, and the equipment immediately enters the next cycle.

[0024] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention.

Claims

1. A durability testing device for an aircraft cockpit air intake duct, comprising a frame, a mounting box mounted on the frame, and a master switch, a power supply, a stop / reset switch, a counter display screen, and an ECU controller mounted on the mounting box, characterized in that: The frame is equipped with a linear slide unit, a rotary execution unit, a pneumatic clamping unit, a position detection unit, and a counting unit; The frame is equipped with an adjustment support, on which a slide bracket is hinged and an angle adjuster is rotatably installed. The angle adjuster adjusts the angle of the slide bracket. The linear slide unit includes a slide support, and the linear slide of the linear slide unit carries a rotary actuator that moves on the slide support. A pneumatic clamping unit is installed at the output end of the rotary actuator. The pneumatic clamping unit clamps the cable end of the cockpit air intake duct of the aircraft to be tested using pneumatic clamps. The slide support is equipped with a fixed position detection unit, which monitors the position of the linear slide. The ECU controller controls and executes the working actions of the linear slide unit, rotary actuator, pneumatic clamping unit, position detection unit, and counting unit, and collects relevant test information.

2. The aircraft cockpit air intake duct durability testing device according to claim 1, characterized in that: The adjusting support is slidably mounted on a slide block, which is connected to the slide table bracket via connecting rods hinged at both ends. An adjusting screw is rotatably mounted on the adjusting support, with its outer end connected to an angle adjuster, passing through the slide block and engaging with it.

3. The aircraft cockpit air intake duct durability testing device according to claim 1, characterized in that: The two ends of the slide bracket are rotatably mounted with a drive screw and a slide rod via two uprights. A linear slide is slidably mounted on the slide rod. The drive screw passes through the linear slide and engages with it. The drive screw is driven by a drive motor fixedly mounted on the uprights to adjust the position of the linear slide on the slide bracket.

4. The aircraft cockpit air intake duct durability testing device according to claim 1, characterized in that: The rotary actuator is fixedly mounted on a linear slide, and includes a fixedly mounted servo motor. The output end of the servo motor is mounted on the pneumatic clamping unit via a pneumatic clamp bracket.

5. The aircraft cockpit air intake duct durability testing device according to claim 1, characterized in that: The pneumatic clamping unit includes a set of fixedly installed air clamp brackets, on which air clamps are installed, and the air clamps are powered by an external air pump.

6. The aircraft cockpit air intake duct durability testing device according to claim 1, characterized in that: The position detection unit includes a front limit switch and a rear limit switch fixedly installed on the slide bracket; when the linear slide triggers the front limit switch or the rear limit switch, it sends a trigger signal to the ECU controller, and the ECU controller controls the rotary actuator to perform rotation.

7. The aircraft cockpit air intake duct durability testing device according to claim 6, characterized in that: When the linear slide triggers the front limit switch, the trigger signal sent by the front limit switch is counted by the counting unit in conjunction with the ECU controller.

8. The aircraft cockpit air intake duct durability testing device according to claim 1, characterized in that: The position detection unit includes a distance-type photoelectric switch fixedly installed on the slide bracket, and the distance-type photoelectric switch is electrically connected to the ECU controller.

9. A testing method based on the testing apparatus described in claims 1-8, characterized in that: Includes the following steps: The first step is to fix the main body of the aircraft cockpit air intake duct in the tooling position, control the relay to turn on, and put the end of the cable to be tested into the pneumatic clamping unit and clamp it tightly. The second step is that the ECU controller controls the linear slide unit to move backward. When the linear slide moves into the detection range of the distance photoelectric switch, the distance photoelectric switch sends a trigger signal to the ECU controller, and the ECU controller controls the rotary actuator to perform a rotation action at a set angle. Third, after the rotary actuator completes its rotation, the ECU controller controls the linear slide unit to continue moving backward until it touches the rear limit switch and immediately stops moving backward; the rear limit switch sends a signal to the ECU controller, and the ECU controller controls the rotary actuator to perform a rotation action of a set angle and then performs a reverse rotation reset. Fourth, after the rotary actuator is reset, the ECU controller controls the linear slide unit to start moving forward. When it passes the distance-type photoelectric switch again, it is triggered a second time. The ECU controller then controls the rotary actuator to perform the rotation action of the set angle again. After the rotation action is completed, the linear slide continues to move forward until it touches the front limit switch. Fifth, after the front limit switch is triggered, the counting unit completes one count, which means that a complete set of endurance cycle actions has been completed; the ECU controller automatically resets all mechanisms, and the equipment immediately enters the next cycle.

10. The test method according to claim 9, characterized in that: The counting unit is a pulse counter, with its input end connected to the front limit switch and its output end connected to the counter display screen. Each time the front limit switch is triggered and closed, the durability cycle action in step five is recorded as one test count, and the corresponding counter display automatically increments by one.

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