Airplane cargo hold PDU test board

Abstract

The utility model relates to the technical field of airplane cargo hold PDU testing, and discloses an airplane cargo hold PDU testboard which comprises a testboard body, an inverted-U-shaped frame is fixedly installed at the upper end of the testboard body, a limiting blocking seat is fixedly sleeved outside the inverted-U-shaped frame, a guiding sliding seat is slidably sleeved outside the inverted-U-shaped frame and located above the limiting blocking seat, and the guiding sliding seat is fixedly sleeved outside the testboard body. A sensed object assembly is arranged above the guide sliding seat, the sensed object assembly comprises an electric push rod and a sensed box body, the electric push rod is fixedly installed on the guide sliding seat, the sensed box body is fixedly installed at the telescopic end of the electric push rod, a displacement sensor is fixedly installed on the outer side of the inverted-U-shaped frame, and the displacement sensor is fixedly installed on the outer side of the inverted-U-shaped frame. According to the utility model, the operation labor amount of testers can be reduced, the lifting stroke information of the airplane cargo hold PDU can be conveniently and accurately observed, and the testing effect of the airplane cargo hold PDU can be ensured.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft cargo hold PDU testing, and more specifically, to an aircraft cargo hold PDU testing platform. Background Art

[0002] Aircraft cargo hold PDU (hereinafter referred to as PDU) driver is designed for aircraft of various models and configurations. The PDU driver component can provide automatic movement of automatic containers or pallets during ground loading and unloading operations. The component is usually installed in the lower leaf of a wide-body commercial passenger aircraft or in the main deck cargo hold of a cargo aircraft. When the aircraft cargo hold PDU is produced, its photoelectric sensor needs to be subjected to induction testing. During the induction testing process of the existing aircraft cargo hold PDU photoelectric sensor, the object to be sensed is usually picked up and placed into the sensing area of ​​the aircraft cargo hold PDU manually to observe whether the aircraft cargo hold PDU can be lifted after the photoelectric sensor senses the object to be tested, so as to judge whether the photoelectric sensor of the aircraft cargo hold PDU is qualified. However, since the batch testing operation requires the test personnel to operate repeatedly for a long time, the test personnel's operation workload is relatively heavy, and it is difficult to accurately observe and obtain the lifting stroke information of the aircraft cargo hold PDU, which affects the test effect of the aircraft cargo hold PDU. In view of this, we propose an aircraft cargo hold PDU test bench. Utility Model Content

[0003] In order to overcome the deficiencies of the prior art, the utility model provides an aircraft cargo hold PDU test bench to solve the problems raised in the above background technology.

[0004] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: an aircraft cargo hold PDU test bench, comprising a test bench body, an inverted U-shaped frame fixedly installed on the upper end of the test bench body, the outer part of the inverted U-shaped frame is fixedly sleeved with a limit stop seat, the outer part of the inverted U-shaped frame is located above the limit stop seat and is slidably sleeved with a guide slide, a sensed object component is arranged above the guide slide, the sensed object component comprises an electric push rod and a sensed box, the electric push rod is fixedly installed on the guide slide, the sensed box is fixedly installed on the telescopic end of the electric push rod, a displacement sensor is fixedly installed on the outer side of the inverted U-shaped frame, and a transmission block is fixedly connected between the measuring end of the displacement sensor and the guide slide.

[0005] As a preferred technical solution of the utility model, a test carrier is fixedly mounted on the surface of the test platform, and a positioning groove is opened on the surface of the test carrier.

[0006] As a preferred technical solution of the present invention, a controller is fixedly installed on the side wall of the inverted U-shaped frame, a buzzer is fixedly installed on one side of the side wall of the inverted U-shaped frame close to the controller, the output end of the displacement sensor is electrically connected to the input end of the controller, and the output end of the controller is electrically connected to the input ends of the electric push rod and the buzzer.

[0007] As a preferred technical solution of the utility model, a displacement digital display is fixedly provided on the controller, and the output end of the controller is electrically connected to the input end of the displacement digital display.

[0008] As a preferred technical solution of the utility model, a limit rod is fixedly installed on the back side of the sensed box, a guide block is fixedly installed on the upper end of the guide slide, and the limit rod movably penetrates the surface of the guide block.

[0009] As a preferred technical solution of the present utility model, the number of the limiting rods is two, and the two limiting rods are symmetrically distributed.

[0010] Compared with the prior art, the beneficial effects of the utility model are as follows:

[0011] The utility model drives the sensed box to move by extending the electric push rod until the sensed box moves to the sensing area of ​​the aircraft cargo hold PDU to be tested. If the aircraft cargo hold PDU undergoes a lifting action, the photoelectric sensor test of the aircraft cargo hold PDU is qualified, and the sensed box is lifted upward, driving the sensed object assembly to move synchronously along the inverted U-shaped frame with the guide slide. The lifting stroke information of the aircraft cargo hold PDU can be monitored by the displacement sensor. If the lifting stroke information of the aircraft cargo hold PDU reaches a preset value, the controller controls the buzzer to emit a buzzing sound effect, prompting that the photoelectric sensor and the lifting stroke test of the aircraft cargo hold PDU are both qualified, thereby eliminating the need for manual repeated picking up and placing of the sensed object, which is beneficial to reducing the operating labor of the test personnel, and is convenient for accurately observing and obtaining the lifting stroke information of the aircraft cargo hold PDU, thereby ensuring the test effect of the aircraft cargo hold PDU. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a front view structural schematic diagram of an aircraft cargo hold PDU test bench according to the utility model;

[0013] Figure 2 This is a side structural schematic diagram of an aircraft cargo hold PDU test bench according to the utility model;

[0014] Figure 3 This is a schematic diagram of the top view of the structure of an aircraft cargo hold PDU test bench according to the utility model;

[0015] Figure 4The utility model is a principle block diagram of a controller in an aircraft cargo hold PDU test bench.

[0016] In the figure: 1. test bench body; 101. test carrier; 102. positioning groove; 2. inverted U-shaped frame; 3. limit stop seat; 4. guide slide; 401. transmission block; 402. guide block; 5. sensed object assembly; 501. electric push rod; 502. sensed box; 503. limit rod; 6. displacement sensor; 7. controller; 8. buzzer; 9. displacement digital display. DETAILED DESCRIPTION

[0017] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0018] In the description of the present invention, it should be understood that the terms "longitudinal", "lateral", "upper", "lower", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0019] like Figures 1 to 4 As shown, the utility model provides an aircraft cargo hold PDU test bench, including a test bench body 1, an inverted U-shaped frame 2 is fixedly installed on the upper end of the test bench body 1, the outer part of the inverted U-shaped frame 2 is fixedly sleeved with a limit stopper 3, the outer part of the inverted U-shaped frame 2 is slidably sleeved with a guide slide 4 above the limit stopper 3, and a sensed object component 5 is arranged above the guide slide 4.

[0020] Among them, the sensed object component 5 includes an electric push rod 501 and a sensed box 502, the electric push rod 501 is fixedly installed on the guide slide 4, and the sensed box 502 is fixedly installed on the telescopic end of the electric push rod 501. When the electric push rod 501 is extended, the sensed box 502 is driven to move until the sensed box 502 moves to the sensing area of ​​the aircraft cargo hold PDU to be tested. If the aircraft cargo hold PDU is lifted, the photoelectric sensor test of the aircraft cargo hold PDU is qualified, and the sensed box 502 is lifted upward, driving the sensed object component 5 to move synchronously with the guide slide 4 along the inverted U-shaped frame 2. A displacement sensor 6 is fixedly installed on the outer side of the inverted U-shaped frame 2, and a transmission block 401 is fixedly connected between the measuring end of the displacement sensor 6 and the guide slide 4. The displacement sensor 6 can be used to monitor the lifting stroke information of the aircraft cargo hold PDU.

[0021] A test carrier 101 is fixedly mounted on the surface of the test bench body 1 , and a positioning groove 102 is provided on the surface of the test carrier 101 , so as to facilitate the positioning and placement of the cargo hold PDU of the aircraft to be tested.

[0022] Among them, the side wall of the inverted U-shaped frame 2 is fixedly installed with a controller 7, and a buzzer 8 is fixedly installed at a position on one side of the side wall of the inverted U-shaped frame 2 near the controller 7. The output end of the displacement sensor 6 is electrically connected to the input end of the controller 7, and the output end of the controller 7 is electrically connected to the electric push rod 501 and the input end of the buzzer 8. If the lifting stroke information of the aircraft cargo compartment PDU reaches the preset value, the controller 7 controls the buzzer 8 to emit a buzzing sound effect, prompting that the photoelectric sensor and lifting stroke test of the aircraft cargo compartment PDU are qualified. A displacement digital display 9 is fixedly set on the controller 7, and the output end of the controller 7 is electrically connected to the input end of the displacement digital display 9. The displacement digital display 9 is used to display the lifting stroke information of the aircraft cargo compartment PDU, so that personnel can check the lifting stroke information of the aircraft cargo compartment PDU.

[0023] Among them, a limit rod 503 is fixedly installed on the back side of the sensed box 502, a guide block 402 is fixedly installed on the upper end of the guide slide 4, and the limit rod 503 movably penetrates the surface of the guide block 402. There are two limit rods 503, and the two limit rods 503 are symmetrically distributed, so as to achieve the purpose of playing a stable guiding and limiting role for the sensed box 502.

[0024] The working principle of this utility model:

[0025] During use, the aircraft cargo hold PDU to be tested is placed on the test carrier 101, and the electric push rod 501 is extended to drive the sensed box 502 to move until the sensed box 502 moves to the sensing area of ​​the aircraft cargo hold PDU to be tested. If the aircraft cargo hold PDU is lifted, the photoelectric sensor test of the aircraft cargo hold PDU is qualified, and the sensed box 502 is lifted upward, driving the sensed object component 5 to move synchronously with the guide slide 4 along the inverted U-shaped frame 2. The displacement sensor 6 can be used to monitor the lifting stroke information of the aircraft cargo hold PDU. If the lifting stroke information of the aircraft cargo hold PDU reaches the preset value, the controller 7 The control buzzer 8 emits a buzzing sound effect, indicating that the photoelectric sensor and lifting stroke tests of the aircraft cargo hold PDU are qualified. After the test, the sensed object component 5 and the guide slide 4 are reset as the aircraft cargo hold PDU is retracted and lowered, and the electric push rod 501 is used to retract to drive the sensed box 502 to be separated from the sensing area of ​​the aircraft cargo hold PDU, and the aircraft cargo hold PDU can be taken out. If the aircraft cargo hold PDU does not perform a lifting action, the photoelectric sensor test of the aircraft cargo hold PDU is unqualified. After the test, the electric push rod 501 is used to retract to drive the sensed box 502 to be separated from the sensing area of ​​the aircraft cargo hold PDU, and the aircraft cargo hold PDU can be taken out.

[0026] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0027] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft cargo hold PDU test bench, comprising a test bench body (1), characterized in that: An inverted U-shaped frame (2) is fixedly mounted on the upper end of the test bench body (1); a limit stop seat (3) is fixedly sleeved on the outside of the inverted U-shaped frame (2); a guide slide seat (4) is slidably sleeved on the outside of the inverted U-shaped frame (2) above the limit stop seat (3); and a sensed object assembly (5) is arranged above the guide slide seat (4); The sensed object assembly (5) comprises an electric push rod (501) and a sensed box (502); the electric push rod (501) is fixedly mounted on a guide slide (4); the sensed box (502) is fixedly mounted on a telescopic end of the electric push rod (501); a displacement sensor (6) is fixedly mounted on the outer side of the inverted U-shaped frame (2); a transmission block (401) is fixedly connected between a measuring end of the displacement sensor (6) and the guide slide (4).

2. The aircraft cargo hold PDU test bench according to claim 1, characterized in that: A test carrier (101) is fixedly mounted on the surface of the test platform body (1), and a positioning groove (102) is provided on the surface of the test carrier (101).

3. The aircraft cargo hold PDU test bench according to claim 1, characterized in that: A controller (7) is fixedly mounted on the side wall of the inverted U-shaped frame (2); a buzzer (8) is fixedly mounted on a side of the side wall of the inverted U-shaped frame (2) close to the controller (7); an output end of the displacement sensor (6) is electrically connected to an input end of the controller (7); and an output end of the controller (7) is electrically connected to an electric push rod (501) and an input end of the buzzer (8).

4. The aircraft cargo hold PDU test bench according to claim 3, characterized in that: A displacement digital display (9) is fixedly arranged on the controller (7), and an output end of the controller (7) is electrically connected to an input end of the displacement digital display (9).

5. The aircraft cargo hold PDU test bench according to claim 1, characterized in that: A limiting rod (503) is fixedly mounted on the back side of the sensed box (502), a guiding block (402) is fixedly mounted on the upper end of the guiding slide (4), and the limiting rod (503) movably penetrates the surface of the guiding block (402).

6. The aircraft cargo hold PDU test bench according to claim 5, characterized in that: The number of the limiting rods (503) is two, and the two limiting rods (503) are symmetrically distributed.

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