Connector assembly for aircraft computer socket and detection device thereof

Abstract

The utility model relates to the technical field of space flight and aviation, and discloses a connector assembly for an aircraft computer socket and a detection device thereof, which comprises a shell, a positioning module, a plug pin fixing module, a relay matrix and a plurality of aviation plug pins, the shell is provided with a mounting groove and an opening for mounting an aircraft computer socket; the opening and the mounting groove are oppositely arranged along a first direction, the positioning module is mounted in the mounting groove, a positioning groove is formed in the positioning module, the plug pin fixing module is mounted in the positioning groove, a plurality of positioning channels extending along the first direction are formed in the plug pin fixing module, and the aviation plug pins are mounted in the positioning channels in a one-to-one correspondence manner. And one end of the aviation plug pin facing the opening is connected with an aircraft computer socket, and one end deviating from the opening is connected with the relay matrix. According to the utility model, one-time full matching of the plug pins of the aircraft computer socket can be realized, any two plug pins can be selected for electrical measurement, and the flexibility and the stability are extremely high.

Description

Technical Field

[0001] The utility model relates to the technical field of aerospace, in particular to a connector assembly for an airplane computer socket and a detection device thereof. Background Art

[0002] At present, Airbus aircraft are equipped with multiple computer devices in different systems, such as flight control computers, landing gear control computers, etc. During maintenance, it is usually necessary to disassemble these computers and test the socket circuits at the rear. Usually, a multimeter is used for testing, and the test leads are inserted into the pin holes of the socket circuits for measurement.

[0003] This method has the following significant disadvantages:

[0004] 1) Since the socket area at the rear of the computer is deep and the ambient light in the area is dim, the worker's vision is blocked during measurement, making it difficult to clearly identify the corresponding measurement socket, increasing the risk of mismeasurement and possibly obtaining erroneous measurement results.

[0005] 2) The specifications of the multimeter pen do not completely match the measurement jack. It is difficult to maintain full and stable contact during the measurement process, and poor contact often occurs. This not only affects the efficiency of the measurement, but also has a direct impact on the precision and accuracy of the measurement results, greatly reducing the reliability of the measurement data.

[0006] Therefore, the existing measurement technology has obvious deficiencies in terms of operational convenience and measurement accuracy, and further technical optimization and improvement are needed. Utility Model Content

[0007] The purpose of the utility model is to design a connector assembly for an aircraft computer socket and a detection device thereof which can solve the above-mentioned problem.

[0008] In order to achieve the above object, the utility model provides a connector assembly for an aircraft computer socket, comprising:

[0009] Housing, positioning module, pin fixing module, relay matrix and multiple aviation pins;

[0010] The shell has a mounting groove and an opening for mounting an aircraft computer socket; the opening and the mounting groove are arranged opposite to each other along a first direction, the positioning module is installed in the mounting groove, a positioning groove is provided on the positioning module, the pin fixing module is installed in the positioning groove, a plurality of positioning channels extending along the first direction are provided on the pin fixing module, each of the aviation pins is installed in each of the positioning channels in a one-to-one correspondence, one end of the aviation pin facing the opening is used to connect with the aircraft computer socket, and the other end of the aviation pin facing away from the opening is connected with the relay matrix.

[0011] Furthermore, the pin fixing module includes a first fixing member and a second fixing member arranged in sequence along the first direction, the positioning channel includes a first sub-channel and a second sub-channel coaxially arranged along the first direction, the first sub-channel is arranged on the first fixing member, the second sub-channel is arranged on the second fixing member, the aviation pin passes through the second sub-channel and is inserted into the first sub-channel, a positioning boss is arranged on the outer peripheral wall of the aviation pin, and the positioning boss is located between the second fixing member and the first fixing member.

[0012] Furthermore, a retaining groove is formed on an edge of an end surface of the second sub-channel facing one end of the first fixing member, and the positioning boss is arranged in the retaining groove.

[0013] Furthermore, it also includes a wire for connecting to an aircraft computer socket, the end of the aviation pin facing away from the second fixing piece is connected to the wire, and a receiving cavity is formed between a part of the inner circumferential wall of the first sub-channel and the end face of the aviation pin facing away from the second fixing piece, and the wire portion is placed in the receiving cavity.

[0014] Further, a size of the first fixing member in the first direction is Lmm, and a size of the second fixing member in the first direction is Jmm, wherein L≥3J.

[0015] Furthermore, a plurality of the positioning channels are arranged in an array on the nail fixing module.

[0016] Furthermore, it comprises a plurality of the pin fixing modules, the positioning module is provided with a plurality of the positioning slots, and each of the pin fixing modules is installed in each of the positioning slots in a one-to-one correspondence.

[0017] Furthermore, the positioning module is detachably connected to the housing via bolts.

[0018] The utility model also provides a detection device for an aircraft computer socket, comprising a component control interface, a digital control component and the above-mentioned connector component for the aircraft computer socket, wherein the digital control component is communicatively connected to the component control interface, and the component control interface is communicatively connected to the relay matrix.

[0019] Compared with the prior art, the connector assembly and detection device for an aircraft computer socket according to the embodiment of the utility model have the following beneficial effects:

[0020] The connector assembly for an aircraft computer socket and the detection device thereof of the embodiment of the utility model are used for a one-time fully matched connection with the aircraft computer socket through a pin fixing module and a plurality of aviation pins, thereby improving the efficiency of installation and testing; during the detection process, any two pins can be selected through a relay matrix for electrical measurement as needed, without the need to match the pins one by one, thus having a high degree of flexibility, reducing the number of operating steps and the probability of potential errors, ensuring the stability and reliability of the detection process, and having a significant cost advantage. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of a connector assembly for an aircraft computer socket according to an embodiment of the utility model;

[0022] Figure 2 It is an exploded schematic diagram of a connector assembly for an aircraft computer socket according to an embodiment of the utility model;

[0023] Figure 3 It is a schematic diagram of electrical connection of a connector assembly for an aircraft computer socket according to an embodiment of the utility model;

[0024] Figure 4 It is a cross-sectional view of the connection structure between the pin fixing module and the aviation pin in the connector assembly for the aircraft computer socket according to the embodiment of the utility model;

[0025] Figure 5 It is a cross-sectional view of the exploded structure of a pin fixing module and an aviation pin in a connector assembly for an aircraft computer socket according to an embodiment of the utility model.

[0026] In the figure, 1, shell; 11, opening; 12, installation slot; 2, positioning module; 21, positioning slot; 3, pin fixing module; 31, first fixing member; 32, second fixing member; 4, positioning channel; 41, first sub-channel; 411, accommodating cavity; 42, second sub-channel; 421, positioning slot; 5, aviation pin; 51, positioning boss; 6, relay matrix; 7, component control interface; x, first direction. DETAILED DESCRIPTION

[0027] The following is a further detailed description of the specific implementation of the present invention in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0028] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like used in the present invention to indicate the orientation or position relationship are based on the orientation or position relationship 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.

[0029] In the description of the present invention, it should be understood that the terms "connected", "connected", "fixed" and the like used in the present invention 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 a welding connection; it can be directly connected, or indirectly connected through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0030] The present invention uses the terms "first", "second", etc. to describe various information, but these information should not be limited to these terms, which are only used to distinguish the same type of information from each other. For example, without departing from the scope of the present invention, the "first" information may also be referred to as the "second" information, and similarly, the "second" information may also be referred to as the "first" information.

[0031] Reference Figure 1 and Figure 2 , a connector assembly for an aircraft computer socket according to an embodiment of the utility model comprises: a housing 1, a positioning module 2, a pin fixing module 3, a relay matrix 6 and a plurality of aviation pins 5;

[0032] The shell 1 has a mounting groove 12 and an opening 11 for installing an aircraft computer socket; the opening 11 and the mounting groove 12 are arranged relatively to each other along a first direction x, the positioning module 2 is installed in the mounting groove 12, a positioning groove 21 is provided on the positioning module 2, the pin fixing module 3 is installed in the positioning groove 21, a plurality of positioning channels 4 extending along the first direction x are provided on the pin fixing module 3, each of the aviation pins 5 is installed in each of the positioning channels 4 in a one-to-one correspondence, one end of the aviation pin 5 facing the opening 11 is used to connect with the aircraft computer socket, and the end thereof away from the opening 11 is connected with the relay matrix 6.

[0033] Among them, the shell 1, the positioning module 2, and the pin fixing module 3 can all be formed by plastic injection molding, which reduces the manufacturing cost and difficulty. The shell 1 can be designed into different sizes according to different aircraft computers, and a positioning module 2 installation groove 12 is reserved on the surface during manufacturing; the specific shape of the positioning module 2 matches the aircraft computer socket to ensure that it is compatible with the overall structure of the aircraft computer socket after being installed on the shell 1. Different shells 1 and positioning modules 2 can be replaced and matched with each other according to the actual aircraft computer socket, and then the pin fixing module 3 is installed to fix the pins, using modular design to reduce the detection cost. The aviation pin 5 can use a female pin, which is compatible with the male pin used in the aircraft computer socket.

[0034] Before testing, each aviation pin 5 is installed one by one on the aircraft computer socket, and a one-time full-matching connection is made with the aircraft computer socket through the pin fixing module 3. During the testing process, any two pins can be selected through the relay matrix 6 for electrical measurement as needed, without the need to match the pins one by one. It has high flexibility, improves the efficiency of installation and testing, reduces the operating steps and the probability of potential errors, ensures the stability and reliability of the testing process, and has significant cost advantages.

[0035] Reference Figure 4 and Figure 5 In some improved solutions of the present application, the pin fixing module 3 includes a first fixing member 31 and a second fixing member 32 sequentially arranged along the first direction x, the positioning channel 4 includes a first sub-channel 41 and a second sub-channel 42 coaxially arranged along the first direction x, the first sub-channel 41 is arranged on the first fixing member 31, the second sub-channel 42 is arranged on the second fixing member 32, the aviation pin 5 passes through the second sub-channel 42 and is inserted into the first sub-channel 41, and a positioning boss 51 is arranged on the outer peripheral wall of the aviation pin 5, and the positioning boss 51 is located between the second fixing member 32 and the first fixing member 31. According to the structure of the positioning boss 51 of the aviation pin 5, a "sandwich" type pin fixing module 3 is designed, and the positioning boss 51 is firmly clamped between the first fixing member 31 and the second fixing member 32, so that the aviation pin 5 is reliably and stably fixed at the required position.

[0036] In some improved schemes of the present application, a locking groove 421 is provided on the end face edge of the second sub-channel 42 facing one end of the first fixing member 31, and the positioning boss 51 is arranged in the locking groove 421. The locking groove 421 is used to install the locking boss to ensure that the aviation pin 5 is firmly fixed without shaking, thereby achieving precise docking with the aircraft computer socket pin.

[0037] In some improved solutions of the present application, a wire for connecting to an aircraft computer socket is further included, the end of the aviation pin 5 facing away from the second fixing piece 32 is connected to the wire, and a portion of the inner peripheral wall of the first sub-channel 41 and the end surface of the aviation pin 5 facing away from the second fixing piece 32 enclose a receiving cavity 411, and the wire is partially placed in the receiving cavity 411. The receiving cavity 411 is used to wrap and protect the wire to prevent the interface between the wire and the aviation pin 5 from being exposed and bending to cause fatigue damage.

[0038] In some improved schemes of the present application, the size of the first fixing member 31 in the first direction x is Lmm, and the size of the second fixing member 32 in the first direction x is Jmm, where L≥3J, thereby optimizing the size ratio of the first fixing member 31 and the second fixing member 32 in the pin fixing module 3, and further ensuring that a certain length of wire can be placed in the accommodating cavity 411.

[0039] In some improved solutions of the present application, a plurality of the positioning channels 4 are arranged in an array on the pin fixing module 3. In order to achieve a stable electrical connection between the interface assembly and the aircraft computer socket, the positioning slots are arranged in an array, and matching aviation pins 5 are installed in the positioning slots at the corresponding positions according to the positions of the male pins inside the computer socket, so as to achieve accurate docking with the pins of the aircraft computer socket.

[0040] In some improved solutions of the present application, a plurality of the pin fixing modules 3 are included, and a plurality of the positioning grooves 21 are provided on the positioning module 2, and each of the pin fixing modules 3 is installed in each of the positioning grooves 21 in a one-to-one correspondence. The plurality of positioning grooves 21 and the plurality of pin fixing modules 3 are provided, so that the arrangement of the pin fixing modules 3 on the positioning module 2 is more flexible, so that the positioning module 2 can adapt to a variety of aircraft computer sockets of different structural sizes.

[0041] In some improved solutions of the present application, the positioning module 2 is detachably connected to the housing 1 by bolts, and the positioning module 2 and the housing 1 can be replaced with each other, so installation and disassembly are convenient and quick.

[0042] Reference Figure 3 The utility model also provides a detection device for an aircraft computer socket, comprising a component control interface 7, a digital control component and the above-mentioned connector component for an aircraft computer socket, wherein the digital control component is communicatively connected to the component control interface 7, and the component control interface 7 is communicatively connected to the relay matrix 6. By switching the on-off state of the relay using the component control interface 7, the electrical connection between any two aviation pins 5 can be realized, and the electrical detection of the aircraft computer socket is performed by connecting the digital control component to the component control interface 7.

[0043] In summary, the embodiment of the utility model provides a connector assembly for an aircraft computer socket and a detection device thereof, which performs a one-time fully matched connection with the aircraft computer socket through a pin fixing module 3 and a plurality of aviation pins 5, thereby improving the efficiency of installation and testing; during the detection process, any two pins can be selected through a relay matrix 6 for electrical measurement as needed, without the need to match the pins one by one, with high flexibility, reducing the number of operating steps and the probability of potential errors, and ensuring the stability and reliability of the detection process; its modular design can replace different shells 1, positioning modules 2, etc. according to the actual aircraft computer structure being detected, with low manufacturing cost and significant cost advantages.

[0044] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and substitutions can be made without departing from the technical principle of the present invention. These improvements and substitutions should also be regarded as the protection scope of the present invention.

Claims

1. A connector assembly for an aircraft computer socket, characterized in that: include: Housing, positioning module, pin fixing module, relay matrix and multiple aviation pins; The housing has a mounting groove and an opening for mounting an aircraft computer socket; the opening and the mounting groove are arranged opposite to each other along a first direction, the positioning module is mounted in the mounting groove, a positioning groove is provided on the positioning module, the pin fixing module is mounted in the positioning groove, a plurality of positioning channels extending along the first direction are provided on the pin fixing module, each of the aviation pins is correspondingly mounted in each of the positioning channels, one end of the aviation pin facing the opening is used to connect with the aircraft computer socket, and the end of the aviation pin facing away from the opening is connected with the relay matrix; The pin fixing module includes a first fixing member and a second fixing member arranged in sequence along the first direction, the positioning channel includes a first sub-channel and a second sub-channel coaxially arranged along the first direction, the first sub-channel is arranged on the first fixing member, the second sub-channel is arranged on the second fixing member, the aviation pin passes through the second sub-channel and is inserted into the first sub-channel, a positioning boss is arranged on the outer peripheral wall of the aviation pin, and the positioning boss is located between the second fixing member and the first fixing member.

2. The connector assembly for an aircraft computer socket as claimed in claim 1, characterized in that: A retaining groove is formed on an edge of an end surface of the second sub-channel facing one end of the first fixing member, and the positioning boss is arranged in the retaining groove.

3. The connector assembly for an aircraft computer socket according to claim 1, characterized in that: It also includes a wire for connecting to an aircraft computer socket, the end of the aviation pin facing away from the second fixing piece is connected to the wire, a portion of the inner circumferential wall of the first sub-channel and the end face of the aviation pin facing away from the second fixing piece form a receiving cavity, and the wire portion is placed in the receiving cavity.

4. The connector assembly for an aircraft computer socket as claimed in claim 3, characterized in that: The dimension of the first fixing member in the first direction is L mm, and the dimension of the second fixing member in the first direction is J mm, wherein L≥3J.

5. The connector assembly for an aircraft computer socket as claimed in claim 1, characterized in that: The plurality of positioning channels are arranged in an array on the nail fixing module.

6. The connector assembly for an aircraft computer socket as claimed in claim 1, characterized in that: It comprises a plurality of the pin fixing modules, the positioning module is provided with a plurality of the positioning slots, and each of the pin fixing modules is installed in each of the positioning slots in a one-to-one correspondence.

7. The connector assembly for an aircraft computer socket as claimed in claim 1, characterized in that: The positioning module is detachably connected to the housing via bolts.

8. A detection device for an aircraft computer socket, characterized in that: It comprises a component control interface, a digital control component and a connector component for an aircraft computer socket as described in any one of claims 1 to 7, wherein the digital control component is communicatively connected to the component control interface, and the component control interface is communicatively connected to the relay matrix.

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