Mechanical environmental suitability test device and test method for aircraft door in-place switch

Abstract

The application discloses a kind of mechanical environmental adaptability test device and test method of aircraft cabin door in-place switch, test device includes vibration simulation unit, switch clamping unit, signal monitoring unit and impact simulation unit, vibration simulation unit is used to simulate the vibration under various working conditions of aircraft, impact simulation unit is used to simulate the rotary impact received under aircraft flight working condition, switch clamping unit includes vibration transmission sheet, by through-hole design to vibration transmission sheet, make the trigger rod of test in-place switch pass through through-hole, can simultaneously test the adaptability of in-place switch to vibration and impact two kinds of mechanical environment, more in line with actual airborne working condition, the present device simple structure, it is convenient to adjust, can solve the problem that in-place switch mechanical environmental adaptability test is single, step by step in prior art, cannot truly simulate aircraft flight working condition.

Description

Technical Field

[0001] This invention relates to the field of aircraft door position switch testing, and more particularly to a test device and test method for the mechanical environmental adaptability of aircraft door position switches. Background Technology

[0002] Aircraft doors are moving parts of an aircraft, frequently undergoing opening and closing movements. Current door movements are hydraulically driven, therefore, a position switch is needed to indicate the door's starting and ending points and to promptly stop the hydraulic drive, preventing accidents. During the development of door position switches, their technical specifications typically include mechanical environmental adaptability tests such as vibration and shock, requiring a series of rigorous tests and evaluations.

[0003] Existing mechanical environmental adaptability tests for position switches often employ a single, step-by-step testing approach. This means that the environmental adaptability tests of position switches under vibration and shock are conducted separately. Since position switches are often subjected to both vibration and shock simultaneously under actual flight conditions, existing testing equipment and methods cannot realistically simulate aircraft flight conditions. Consequently, accidents frequently occur where the performance test passes but the position switch malfunctions during flight. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of existing technologies in which the mechanical environment adaptability test of the door position switch is singular and carried out in steps, and cannot truly simulate the flight conditions of an aircraft. This invention provides a test device and test method for the mechanical environment adaptability test of an aircraft door position switch.

[0005] To achieve the above-mentioned objectives, the present invention provides the following technical solution:

[0006] A mechanical environment adaptability testing device for an aircraft door positioning switch includes a vibration simulation unit, a switch clamping unit, a signal monitoring unit, and an impact simulation unit. The vibration simulation unit simulates vibrations under various operating conditions of an aircraft. The switch clamping unit includes a vibration conduction plate, one end of which contacts the vibration simulation unit, and the other end of which has a through hole. The signal monitoring unit includes a signal receiving display and a test positioning switch, connected to each other. The signal receiving display monitors the status of the test positioning switch. The test positioning switch includes a fixing member and a trigger rod. The fixing member secures the trigger rod to the vibration conduction plate, and the trigger rod passes through the through hole. Vibrations generated by the vibration simulation unit are conducted to the test positioning switch through the vibration conduction plate. The impact simulation unit simulates impacts experienced by the aircraft during flight, and the impact simulation unit is capable of rotating and impacting the trigger rod.

[0007] The present invention discloses a mechanical environment adaptability test device for an aircraft door positioning switch. The vibration simulation unit simulates vibration under various operating conditions of the aircraft, and the impact simulation unit simulates rotational impact under flight conditions. By designing a through hole in the vibration transmission plate, the trigger rod of the positioning switch can be passed through the through hole. This device can simultaneously test the adaptability of the positioning switch to both vibration and impact mechanical environments, which is more in line with the actual airborne operating conditions.

[0008] Preferably, the switch clamping unit further includes a switch fixing support frame, and the vibration conduction plate and the switch fixing support frame are detachably connected.

[0009] This structural design, with its detachable connection, facilitates the replacement of vibration transmission plates of different sizes, thereby enabling the simulation of vibrations experienced by the position switch under different aircraft flight conditions.

[0010] Preferably, the impact simulation unit includes a rotary drive motor and a support arm, the rotary drive motor being able to drive the support arm to rotate, and the support arm being used to impact the trigger rod.

[0011] Preferably, the impact simulation unit further includes a movable mounting bracket, the movable mounting bracket is provided with a drive shaft, the support arm is fixedly connected to the drive shaft, and the rotary drive motor drives the drive shaft to drive the support arm to perform reciprocating rotational motion.

[0012] The impact force that an aircraft experiences during actual flight is usually a rotational impact force. With this structural design, the rotational drive motor drives the support arm to rotate, which can realistically simulate the impact that the position switch experiences during aircraft flight, making the test results closer to the actual airborne conditions.

[0013] Preferably, the rotary drive motor is fixed to the movable mounting bracket.

[0014] Preferably, the impact simulation unit further includes a slide rail, and the bottom of the movable mounting bracket has a groove that mates with the slide rail track.

[0015] Preferably, a keyway is provided on the support arm, and one side of the keyway has a scale for indicating the distance between the drive shaft and the test position switch.

[0016] Preferably, a counterweight is detachably connected to the end of the support arm away from the movable mounting bracket.

[0017] With this structural design, when it is necessary to simulate the rotational impact force experienced by the test position switch under different flight conditions, the distance between the drive shaft and the test position switch and / or the weight of the counterweight can be adjusted under the guidance of the slide rail to adjust the magnitude of the impact force experienced by the test position switch.

[0018] Preferably, the vibration simulation unit includes a vibration drive motor, a motor mounting bracket, and a vibration excitation link. The vibration drive motor is fixedly connected to the motor mounting bracket, and the vibration drive motor drives the vibration excitation link to perform mechanical vibration.

[0019] With this structural design, the vibration of an aircraft under various operating conditions can be simulated by using a vibration motor to drive the excitation linkage.

[0020] A method for testing the mechanical environmental adaptability of an aircraft door positioning switch, using the mechanical environmental adaptability testing device for an aircraft door positioning switch described in this invention, includes the following steps:

[0021] a. Connect and fix the vibration simulation unit, the impact simulation unit, the switch clamping unit, and the signal monitoring unit;

[0022] b. Adjust the distance R between the drive shaft and the test position switch according to the force conditions of different position switches on the aircraft. The distance R is adjusted according to the following formula:

[0023]

[0024]

[0025] m represents the counterweight mass (Kg), N represents the rotational speed of the rotary drive motor (r / min), R represents the distance between the drive shaft and the test positioning switch (mm), F represents the impact force (N) on the test positioning switch, and V represents the linear velocity (m / s) of the support arm during rotation.

[0026] c. Simultaneously turn on the vibration drive motor and the rotation drive motor to simulate the adaptability of the test position switch to two mechanical environments: vibration and impact. Read and record the signal output of the test position switch for each test on the signal receiving display.

[0027] This testing method can simultaneously simulate and test the adaptability of position switches to two mechanical environments: vibration and impact. It is easy to operate, and the vibration and impact forces under different working conditions can be adjusted to meet the mechanical environment adaptability testing of position switches under different technical requirements.

[0028] Compared with the prior art, the beneficial effects of the present invention are:

[0029] 1. The mechanical environment adaptability test device for aircraft door position switch described in this invention uses the vibration simulation unit to simulate the vibration of the position switch under different flight conditions of the aircraft, and the impact simulation unit to simulate the rotational impact of the position switch under different flight conditions of the aircraft. By designing through holes in the vibration transmission plate, the trigger rod of the position switch can be passed through the through holes, which can simultaneously test the adaptability of the position switch to both vibration and impact mechanical environments, which is more in line with the actual airborne conditions. This device has a simple structure and is easy to adjust, which can solve the problem that the mechanical environment adaptability test of the position switch in the prior art is single and carried out in steps, and cannot truly simulate the flight conditions of the aircraft.

[0030] 2. The mechanical environment adaptability test method for aircraft door position switch described in this invention can simultaneously simulate and test the adaptability of the position switch to two mechanical environments: vibration and impact. It is easy to operate, and the vibration and impact forces under different working conditions can be adjusted to meet the mechanical environment adaptability test of the position switch under different technical requirements. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the overall three-dimensional structure of a mechanical environmental adaptability test device for an aircraft cabin door positioning switch proposed in this invention.

[0032] Figure 2 This is a schematic diagram of the three-dimensional structure of the vibration simulation test unit in this invention;

[0033] Figure 3 This is a three-dimensional structural diagram of the switch clamping unit in this invention;

[0034] Figure 4 This is a schematic diagram of the three-dimensional structure of the impact simulation unit in this invention;

[0035] Figure 5 This is a three-dimensional structural diagram of the signal monitoring unit in this invention;

[0036] The numbers in the diagram are: 1-Motor mounting bracket, 2-Vibration drive motor, 3-Vibration excitation connecting rod, 4-Vibration transmission plate, 41-Through hole, 5-Switch fixing support bracket, 6-Positioning pin, 7-Limit screw, 8-Signal receiving display, 9-Test position switch, 91-Fixing component, 92-Trigger rod, 10-Counterweight, 11-Slide rail, 12-Support arm, 13-Moving mounting bracket, 14-Drive shaft, 15-Rotary drive motor, 16-Scale, 17-Keyway, 18-Groove. Detailed Implementation

[0037] The present invention will be further described in detail below with reference to experimental examples and specific embodiments. However, this should not be construed as limiting the scope of the above-mentioned subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0038] Example 1

[0039] like Figure 1-5 As shown, the mechanical environment adaptability test device for an aircraft door positioning switch according to the present invention includes a vibration simulation unit, a switch clamping unit, a signal monitoring unit, and an impact simulation unit.

[0040] The vibration simulation unit includes a motor mounting bracket 1, a vibration drive motor 2, and a vibration excitation link 3. The vibration drive motor 2 is located on the motor mounting bracket 1 and is connected to the vibration excitation link 3. The vibration drive motor 2 drives the vibration excitation link 3 to perform mechanical vibration. By driving the vibration excitation link 3 through the vibration drive motor 2, vibration under various operating conditions of the aircraft can be simulated.

[0041] The switch clamping unit includes a vibration conduction plate 4 and a switch fixing support frame 5. The vibration conduction plate 4 and the switch fixing support frame 5 are detachably connected. The height of the vibration drive motor 2 is adjusted so that the vibration excitation connecting rod 3 contacts one end of the vibration conduction plate 4. The other end of the vibration conduction plate 4 is provided with a through hole 41. During use, the specification of the vibration conduction plate 4 is selected according to the vibration test requirements. The vibration conduction plate 4 can use a positioning strain gauge. The vibration conduction plate 4 is connected to the switch fixing bracket 5, the positioning pin 6 is inserted, and the limit screw 7 is tightened to fix the vibration conduction plate 4. This fixing method makes it more convenient and faster to replace vibration conduction plates 4 of different specifications.

[0042] The signal monitoring unit includes a signal receiving display 8 and a test position switch 9, which are connected. The test position switch 9 includes a fixing member 91 and a trigger rod 92. In this embodiment, the fixing member 91 is a mounting nut integrated with the test position switch 9. During use, the trigger rod 92 is passed through the through hole 41 on the vibration transmission plate 4, and then the mounting nut is tightened. When the test position switch 9 functions normally, the signal receiving display 8 can display a complete signal. When the test position switch 9 malfunctions, the signal receiving display 8 displays an incomplete signal or no signal, thereby determining whether the test position switch 9 functions normally under different operating conditions during simulated aircraft flight.

[0043] The fixing member 91 is fixedly connected to the trigger rod 92, and the diameter of the fixing member 91 is larger than the diameter of the through hole 41, so that the fixing member 91 can be fixed above the through hole 41. The vibration of the vibration simulation unit is transmitted to the fixing member 91 through the vibration conduction plate 4, thereby driving the test position switch 9 to vibrate.

[0044] By designing a through hole in the vibration transmission plate 4, the trigger rod 92 of the test position switch 9 can pass through the through hole, and the impact simulation unit can directly impact the trigger rod 92. This allows for the simultaneous testing of the position switch's adaptability to both vibration and impact mechanical environments, which is more in line with actual airborne operating conditions.

[0045] The impact simulation unit includes a slide rail 11, a rotary drive motor 15, a support arm 12, and a movable mounting bracket 13. The rotary drive motor 15 is located on the movable mounting bracket 13. The upper part of the movable mounting bracket 13 is provided with a drive shaft 14, and the lower part of the movable mounting bracket 13 is provided with a groove 18 that mates with the slide rail 11. The drive shaft 14 passes through the movable mounting bracket 13 and is connected to the rotary drive motor 15. The support arm 12 is connected to the drive shaft 14 by bolts. The upper part of the support arm 12 has a keyway 17. The side of the support arm 12 has a scale 16 for indicating the distance between the drive shaft 14 and the test position switch 9. A counterweight 10 is detachably connected to the end of the support arm 12 near the test position switch 9. In use, based on the force exerted on the position switch 9 under different operating conditions on the aircraft, the position of the impact simulation test unit is initially adjusted by adjusting the position of the movable mounting bracket 13 on the slide rail 11. Then, the bolt assembly fixing the support arm 12 is loosened, and the distance between the impact point of the support arm 12 and the position switch 9 is precisely adjusted according to the scale on the support arm 12. The weight of the counterweight 10 is adjusted, thereby adjusting the force of the support arm 12 impacting the position switch 9. The rotary drive motor 15 drives the transmission shaft 14 to drive the support arm 12 to perform reciprocating rotational motion. With this structural setup, the rotary drive motor 15 drives the support arm 12 to perform reciprocating rotational motion to impact the position switch 9. By adjusting the distance between the transmission shaft 14 and the position switch 9, and / or adjusting the weight of the counterweight 10, the force of the support arm 12 impacting the position switch 9 can be adjusted, which can realistically simulate the impact on the position switch during aircraft flight, making the test results closer to real airborne conditions.

[0046] Example 2

[0047] This invention also discloses a method for testing the mechanical environmental adaptability of an aircraft door positioning switch, using the mechanical environmental adaptability testing device for an aircraft door positioning switch described in this invention, comprising the following steps:

[0048] a. Connect and fix the vibration simulation unit, the impact simulation unit, the switch clamping unit, and the signal monitoring unit;

[0049] In the specific implementation process, the switch fixing support frame 5, motor mounting bracket 1, and slide rail 11 can be fixed to the load-bearing floor according to the positioning line.

[0050] b. Adjust the distance R between the drive shaft 14 and the test position switch 9 according to the different force conditions of the position switches on the aircraft. The distance R is adjusted according to the following formula:

[0051]

[0052]

[0053] m represents the mass of the counterweight 10 (Kg), N represents the rotational speed of the rotary drive motor 15 (r / min), R represents the distance between the transmission shaft 14 and the test positioning switch 9 (mm), F represents the impact force (N) on the test positioning switch 9, and V represents the linear velocity (m / s) of the support arm 12 when it rotates.

[0054] c. Simultaneously turn on the vibration drive motor 2 and the rotary drive motor 15 to simulate the adaptability of the position switch 9 to both vibration and impact mechanical environments. Monitor the signal of the position switch for each test on the signal receiving display 8 to determine whether the position switch is functioning properly. When it is necessary to change the vibration, it can be adjusted by replacing the vibration transmission plate 4 and / or adjusting the vibration drive motor 2. When it is necessary to change the impact force, it can be achieved by changing the weight of the counterweight 10 and / or the distance between the transmission shaft 14 and the position switch 9. This method can simultaneously simulate and test the adaptability of the position switch 9 to both vibration and impact mechanical environments. It is easy to operate, and the vibration and impact forces under different working conditions can be adjusted to meet the mechanical environment adaptability test requirements of the position switch under different technical requirements.

[0055] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A mechanical environmental adaptability testing device for an aircraft cabin door positioning switch, characterized in that: The system includes a vibration simulation unit, a switch clamping unit, a signal monitoring unit, and an impact simulation unit. The vibration simulation unit is used to simulate the vibration of an aircraft under various operating conditions. The switch clamping unit includes a vibration transmission plate (4), one end of which is in contact with the vibration simulation unit, and the other end of which is provided with a through hole (41). The signal monitoring unit includes a signal receiving display (8) and a test position switch (9), which are connected. The signal receiving display (8) is used to monitor the status of the test position switch (9). The test position switch (9) includes a fixing member (91) and a trigger rod (92). The fixing member (91) is located above the through hole (41), and the trigger rod (92) passes through the through hole (41). The vibration generated by the vibration simulation unit is transmitted to the fixing member (91) through the vibration transmission plate (4). The impact simulation unit is used to simulate the impacts experienced by the aircraft under flight conditions, and the impact simulation unit can impact the trigger rod (92).

2. The mechanical environmental adaptability testing device for an aircraft cabin door positioning switch according to claim 1, characterized in that, The switch clamping unit also includes a switch fixing support frame (5), and the vibration transmission plate (4) and the switch fixing support frame (5) are detachably connected.

3. The mechanical environmental adaptability test device for an aircraft cabin door positioning switch according to claim 2, characterized in that, The impact simulation unit includes a rotary drive motor (15) and a support arm (12). The rotary drive motor (15) can drive the support arm (12) to rotate. The support arm (12) is used to impact the trigger rod (92).

4. The mechanical environmental adaptability testing device for an aircraft cabin door positioning switch according to claim 3, characterized in that, The impact simulation unit also includes a movable mounting bracket (13), which is provided with a transmission shaft (14). The support arm (12) is fixedly connected to the transmission shaft (14), and the rotary drive motor (15) drives the transmission shaft (14) to drive the support arm (12) to perform reciprocating rotational motion.

5. The mechanical environmental adaptability testing device for an aircraft cabin door positioning switch according to claim 4, characterized in that, The rotary drive motor (15) is fixed on the movable mounting bracket (13).

6. The mechanical environmental adaptability testing device for an aircraft cabin door positioning switch according to claim 5, characterized in that, The impact simulation unit also includes a slide rail (11), and the bottom of the movable mounting bracket (13) has a groove (18) that matches the track of the slide rail (11).

7. The aircraft cabin door positioning switch mechanical environment adaptability test device according to claim 6, characterized in that, A keyway (17) is provided on the support arm (12), and a scale (16) is provided on one side of the keyway (17) to indicate the distance between the drive shaft (14) and the test position switch (9).

8. The mechanical environmental adaptability testing device for an aircraft cabin door positioning switch according to claim 7, characterized in that, The arm (12) is detachably connected to a counterweight (10) at the end away from the movable mounting bracket (13).

9. The mechanical environmental adaptability testing device for an aircraft cabin door positioning switch according to claim 8, characterized in that, The vibration simulation unit includes a vibration drive motor (2), a motor mounting bracket (1), and a vibration excitation link (3). The vibration drive motor (2) is fixedly connected to the motor mounting bracket (1), and the vibration drive motor (2) drives the vibration excitation link (3) to perform mechanical vibration.

10. A method for testing the mechanical environmental adaptability of an aircraft cabin door positioning switch, characterized in that, The mechanical environmental adaptability testing device for an aircraft door positioning switch as described in claim 9 includes the following steps: The vibration simulation unit, the impact simulation unit, the switch clamping unit, and the signal monitoring unit are connected and fixed together; The distance R between the drive shaft (14) and the test position switch (9) is adjusted according to the force conditions of different position switches on the aircraft. The distance R is adjusted according to the following formula: In the formula, m This represents the mass (Kg) of the counterweight (10). N This represents the rotational speed (r / min) of the rotary drive motor (15). R The distance (mm) between the drive shaft (14) and the test position switch (9) represents the distance between them. F The impact force N represents the force N experienced by the test-positioned switch (9). V The linear velocity m / s represents the rotational speed of the arm (12); Simultaneously turn on the vibration drive motor (2) and the rotation drive motor (15) to simulate the adaptability of the test position switch (9) to both vibration and shock mechanical environments. Read and record the signal output of the test position switch (9) each time on the signal receiving display (8).

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