Host device for measuring aircraft lock pin and lock ring

Abstract

The invention provides a host device for measuring aircraft lock pins and lock rings, and relates to the technical field of aircraft lock pins and lock rings. The device comprises a machine shell, the machine shell is installed on an aircraft cockpit system and arranged corresponding to a lock ring on the aircraft cockpit system, and an image detection module on the aircraft cockpit system is arranged corresponding to an aircraft lock pin and the lock ring. The distance positioning contacts are installed on the opposite faces between the two ends of the machine shell and are correspondingly arranged, and the aircraft lock pin sequentially penetrates through the space between the two ends of the machine shell and the lock ring; the display screen is installed at the first end of the machine shell and electrically connected with the image detection module and the distance positioning contact. As a whole, the device can accurately detect the assembly conditions of the inner lock pin, the lock ring assembly clearance and the like, and facilitates the firm fixation of the hatch cover on the fuselage.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft locking pins and locking rings, and in particular to a main device for measuring aircraft locking pins and locking rings. Background Art

[0002] The aircraft cockpit lock is a mechanism connecting the movable cabin cover and the fuselage structure. Its function is to firmly fix the movable cabin cover on the fuselage structure. In addition to bearing the normal locking and unlocking operation loads, it can transfer the pneumatic and pressurization loads on the movable cabin cover during flight to the fuselage. Its main characteristics are easy locking and unlocking, and the normal lock also serves as an emergency lock, which is convenient for inspection and maintenance.

[0003] The aircraft cabin cover locking pin and locking ring are in a closed space, and quantitative detection of their assembly gaps is required; however, there is currently a lack of a detection device suitable for detecting the assembly conditions such as the assembly gaps of the locking pin and locking ring in a relatively closed space, and it is impossible to accurately grasp the opening and closing states of the cabin cover and the fuselage.

[0004] Therefore, there is an urgent need for a main device for measuring aircraft locking pins and locking rings that can accurately detect the assembly conditions such as the assembly gaps of the locking pins and locking rings, and help to firmly fix the cabin cover on the fuselage. Summary of the Invention

[0005] The purpose of the present invention is to provide a main device for measuring aircraft locking pins and locking rings, which solves the technical problem in the prior art that there is a lack of a detection device suitable for detecting the assembly conditions such as the assembly gaps of the locking pins and locking rings in a relatively closed space, and it is impossible to accurately grasp the opening and closing states of the cabin cover and the fuselage. The many technical effects that can be produced by the preferred technical solutions among the many technical solutions provided by the present invention are described in detail below.

[0006] To achieve the above purpose, the present invention provides the following technical solutions:

[0007] A main device for measuring aircraft locking pins and locking rings provided by the present invention includes:

[0008] A machine shell, which is installed on the aircraft cockpit system and is correspondingly arranged with the locking ring on the aircraft cockpit system. The image detection modules on the aircraft cockpit system are respectively correspondingly arranged with the aircraft locking pin and the locking ring;

[0009] Distance positioning contacts, a plurality of the distance positioning contacts are respectively installed on the opposite surfaces between the two ends of the machine shell and are respectively correspondingly arranged. The aircraft locking pin sequentially passes through between the two ends of the machine shell and the locking ring;

[0010] A display screen, which is installed at the first end of the machine shell and is electrically connected to the image detection module and the distance positioning contacts.

[0011] Preferably, the distance positioning contact includes:

[0012] An optoelectronic sensor, which is installed on the opposite surface between the two ends of the housing.

[0013] Preferably, it further includes:

[0014] A D-type magnetic attraction interface, which is installed at the second end of the housing and is electrically connected to the optoelectronic sensor and the display screen. The housing is electrically connected to the aircraft cockpit system through the D-type magnetic attraction interface.

[0015] Preferably, it further includes:

[0016] A data conversion board, which is installed inside the second end of the housing and is electrically connected to the optoelectronic sensor. The D-type magnetic attraction interface is installed on the data conversion board;

[0017] A processor main board, which is installed inside the first end of the housing and is electrically connected to the display screen and the data conversion board.

[0018] Preferably, it further includes:

[0019] An FMC connector, which is installed inside the housing and is connected between the data conversion board and the processor main board.

[0020] Preferably, it further includes:

[0021] A buzzer, which is installed on the processor main board.

[0022] Preferably, it further includes:

[0023] A button and a reset key, which are installed on the side wall of the housing and are respectively electrically connected to the processor main board;

[0024] A power switch, which is installed on the side wall of the housing and is electrically connected to the data conversion board.

[0025] Preferably, it further includes:

[0026] A program interface, which is arranged on the housing and is electrically connected to the processor main board.

[0027] In the technical solution provided by the present invention, the casing and the lock ring are respectively installed on the aircraft cockpit system and aligned. The aircraft locking pin passes through between a plurality of distance positioning contacts and then is inserted into the lock ring. Among them, the plurality of distance positioning contacts can detect the distances between both sides of the aircraft locking pin and the casing, so as to judge the assembly gap between the locking pin and the lock ring. Under the cooperative action of the image detection module, the assembly gap and the image information of the locking pin and the lock ring are transmitted to the display screen and displayed for the subsequent operation of the operator. At the same time, its working mode and state are also monitored. Overall, the present application can accurately detect the assembly conditions such as the assembly gap between the locking pin and the lock ring, which helps to firmly fix the hatch on the fuselage. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0029] Figure 1 It is a schematic front view of the main device of the present invention;

[0030] Figure 2 It is an isometric schematic diagram of the main device of the present invention;

[0031] Figure 3 It is a schematic diagram of the data conversion board and the processor main board of the present invention.

[0032] In the figure: 1, casing; 2, display screen; 3, button; 4, program interface; 5, buzzer; 6, power switch; 7, D-type magnetic suction interface; 8, distance positioning contact; 9, FMC connector; 10, battery; 11, data conversion board; 12, reset key; 13, processor main board. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0033] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art without creative efforts based on the embodiments of the present invention belong to the scope protected by the present invention.

[0034] Refer to Figures 1-3 , the specific embodiment of the present invention provides a main device for measuring an aircraft locking pin and a lock ring, including:

[0035] The housing 1 is installed on the aircraft cockpit system and is correspondingly arranged with the locking ring on the aircraft cockpit system. The image detection module on the aircraft cockpit system is correspondingly arranged with the aircraft locking pin and the locking ring respectively;

[0036] Distance positioning contacts 8. A plurality of distance positioning contacts 8 are respectively installed on the opposite surfaces between the two ends of the housing 1 and are correspondingly arranged respectively. The aircraft locking pin passes through between the two ends of the housing 1 and then into the locking ring;

[0037] The display screen 2 is installed at the first end of the housing 1 and is electrically connected to the image detection module and the distance positioning contacts 8.

[0038] The aircraft canopy locking pin and the locking ring are in a closed space, and quantitative detection of their assembly clearance is required; however, there is currently a lack of a detection device suitable for detecting the assembly conditions such as the assembly clearance between the locking pin and the locking ring in a relatively closed space, and it is impossible to accurately grasp the opening and closing states of the canopy and the fuselage. In this application, the housing 1 and the locking ring are respectively installed on the aircraft cockpit system and are aligned. The aircraft locking pin passes through between a plurality of distance positioning contacts 8 and then is inserted into the locking ring. Among them, a plurality of distance positioning contacts 8 can detect the distances between both sides of the aircraft locking pin and the housing 1, and then judge the assembly clearance between the locking pin and the locking ring; under the cooperative action of the image detection module, the assembly clearance and the image information of the locking pin and the locking ring are transmitted to the display screen 2 and displayed for the subsequent operation of the operator. At the same time, its working mode and state are also monitored. Overall, this application can accurately detect the assembly conditions such as the assembly clearance between the locking pin and the locking ring, which helps the canopy to be firmly fixed on the fuselage.

[0039] For a further optimized solution, the distance positioning contacts 8 include:

[0040] Photoelectric sensors. The photoelectric sensors are installed on the opposite surfaces between the two ends of the housing 1.

[0041] The main functions of the photoelectric sensors are to detect the presence or change of light, measure the light intensity, identify colors, measure distances and speeds, and then judge the movement of the locking pin and the assembly clearance between the locking pin and the locking ring.

[0042] For a further optimized solution, it further includes:

[0043] The D-type magnetic interface 7. The D-type magnetic interface 7 is installed at the second end of the housing 1 and is electrically connected to the photoelectric sensors and the display screen 2. The housing 1 is electrically connected to the aircraft cockpit system through the D-type magnetic interface 7.

[0044] The housing 1 is installed on the aircraft cockpit system through the D-type magnetic interface 7 and transmits the detection information to the aircraft cockpit system.

[0045] For a further optimized solution, it further includes:

[0046] The data conversion board 11 is installed inside the second end of the chassis 1 and is electrically connected to the photoelectric sensor. The D-type magnetic suction interface 7 is installed on the data conversion board 11;

[0047] The processor main board 13 is installed inside the first end of the chassis 1 and is electrically connected to the display screen 2 and the data conversion board 11;

[0048] The FMC connector 9 is installed inside the chassis 1 and is connected between the data conversion board 11 and the processor main board 13.

[0049] The data conversion board 11 is self-developed and designed to convert the data collected by the image detection module and the photoelectric sensor, and then transmit it to the processor main board 13 through the FMC connector 9. The processor main board 13 is a self-designed and developed integrated circuit PCB board. Its main function is to control the whole machine system, perform logical processing, calculations, and drive the display screen 2 through a pre-designed program. The FMC connector 9 completes the data connection and transmission between the data conversion board 11 and the processor main board 13.

[0050] The further optimized solution further includes:

[0051] The buzzer 5 is installed on the processor main board 13.

[0052] The buzzer 5 can give an alarm sound prompt when the operation is completed or in case of an abnormal situation.

[0053] The further optimized solution further includes:

[0054] The button 3 and the reset key 12 are installed on the side wall of the chassis 1 and are respectively electrically connected to the processor main board 13;

[0055] The power switch 6 is installed on the side wall of the chassis 1 and is electrically connected to the data conversion board 11.

[0056] The functions of each button 3 are defined by the program to realize the operation and control of the entire host; the power switch 6 realizes the on / off control of the power supply of the host system.

[0057] The further optimized solution further includes:

[0058] The program interface 4 is set on the chassis 1 and is electrically connected to the processor main board 13.

[0059] The program interface 4 is used to complete the input of the program and the import and export of data, which is convenient for debugging.

[0060] The further optimized solution further includes:

[0061] The battery 10 is installed in the housing 1 and is electrically connected to the data conversion board 11 and the processor main board 13.

[0062] In this application, first, install the corresponding data acquisition module according to the working mode (image detection or optoelectronic position detection), and then accurately position the housing and the locking ring on the cockpit system of the aircraft to complete the positioning of the main unit. Then, fix the locking pin laser module as a whole on the aircraft locking pin, turn on the power switch of the module, and the high-power battery 10 supplies power to the module. The module starts to work normally. When the main body measurement module and the optoelectronic position measurement module are used in combination, it can accurately complete the precise calibration measurement of the axis position of the locking pin; when the main body measurement module and the image detection module are used in combination, it can accurately measure the assembly gap between the locking ring and the locking pin. The display screen 2 displays different output data according to different working modes, and saves and processes the data for convenient calling, querying, and data export.

[0063] It should be noted that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. described in this article indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. They are only for the convenience of describing this application and simplifying the description, rather than indicating or implying 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 to this application. In addition, the terms "first", "second", "third", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0064] In the description of this article, it should also be noted that unless otherwise clearly specified and limited, the terms "install", "connect", "couple" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0065] The above is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A host device for measuring aircraft lock pins and lock rings, characterized in that: include: A casing (1), the casing (1) being mounted on an aircraft cockpit system and being arranged corresponding to a locking ring on the aircraft cockpit system, and an image detection module on the aircraft cockpit system being arranged corresponding to an aircraft locking pin and a locking ring respectively; Distance positioning contacts (8), a plurality of the distance positioning contacts (8) are respectively mounted on opposite surfaces between the two ends of the housing (1) and are respectively arranged correspondingly, and the aircraft lock pin passes through the two ends of the housing (1) and the lock ring in sequence; A display screen (2), the display screen (2) is mounted on the first end of the housing (1), and is electrically connected to the image detection module and the distance positioning contact (8).

2. The host device for measuring aircraft lock pins and lock rings according to claim 1, characterized in that: The distance positioning contact (8) comprises: A photoelectric sensor is mounted on opposite surfaces between the two ends of the housing (1).

3. The host device for measuring aircraft lock pins and lock rings according to claim 2, characterized in that: Also includes: A D-type magnetic interface (7), the D-type magnetic interface (7) is installed at the second end of the housing (1) and is electrically connected to the photoelectric sensor and the display screen (2); the housing (1) is electrically connected to the aircraft cabin system via the D-type magnetic interface (7).

4. The host device for measuring aircraft lock pins and lock rings according to claim 3, characterized in that: Also includes: A data conversion board (11), the data conversion board (11) is installed in the second end of the housing (1) and is electrically connected to the photoelectric sensor, and the D-type magnetic interface (7) is installed on the data conversion board (11); A processor mainboard (13), the processor mainboard (13) is installed in the first end of the housing (1) and is electrically connected to the display screen (2) and the data conversion board (11).

5. The host device for measuring aircraft lock pins and lock rings according to claim 4, characterized in that: Also includes: An FMC connector (9), the FMC connector (9) is installed in the housing (1) and connected between the data conversion board (11) and the processor main board (13).

6. The host device for measuring aircraft lock pins and lock rings according to claim 4, characterized in that: Also includes: A buzzer (5), wherein the buzzer (5) is mounted on the processor mainboard (13).

7. The host device for measuring aircraft lock pins and lock rings according to claim 4, characterized in that: Also includes: A button (3) and a reset key (12), wherein the button (3) and the reset key (12) are mounted on the side wall of the housing (1) and are electrically connected to the processor mainboard (13) respectively; A power switch (6), the power switch (6) being mounted on a side wall of the housing (1) and being electrically connected to the data conversion board (11).

8. The host device for measuring aircraft lock pins and lock rings according to claim 4, characterized in that: Also includes: A program interface (4), wherein the program interface (4) is arranged on the housing (1) and is electrically connected to the processor mainboard (13).

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