Connecting mechanism socket of aerospace system equipment

Abstract

The invention discloses a connecting mechanism socket of aerospace system equipment. The connecting mechanism socket comprises a shell, a protection part and a signal transmission assembly, one end of the shell is an installation end, and the installation end of the shell can be installed on a shell body of aerospace system equipment and is communicated with the shell body; the protection piece adopts a multi-layer staggered chip capacitor; the signal transduction assembly is installed in the shell, the input end of the signal transduction assembly can be connected with the plug so as to receive signals, the output end of the signal transduction assembly can be connected with aerospace system equipment so as to transmit the signals to the aerospace system equipment, and the signal transduction assembly penetrates through the protection part so that the protection part can filter electromagnetic pulses in the signals. The connecting mechanism socket of the aerospace system equipment has an electromagnetic pulse protection function, and the environmental adaptability and safety of the system equipment are improved.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to a connection mechanism socket for aerospace system equipment. Background Art

[0002] During the launch and operation of many aerospace system equipment, artificial and natural electromagnetic pulses can easily enter the system equipment through the connection mechanism socket, causing temporary functional failure of the system equipment at the least, or causing damage to the internal components and equipment of the system, resulting in the system equipment being unable to work normally. This results in low environmental adaptability of aerospace system equipment. Summary of the invention

[0003] In order to solve the shortcoming that the connection mechanism socket of the existing aerospace model system equipment easily causes external electromagnetic pulses to enter the system equipment, the present invention proposes a connection mechanism socket of aerospace system equipment, which has an electromagnetic pulse protection function and improves the environmental adaptability and safety of the system equipment.

[0004] To achieve the above object, the present invention adopts the following technical solutions: A connection mechanism socket for aerospace system equipment comprises: a shell, a protective member and a signal conduction component; the shell is grounded, one end of the shell is a mounting end, the mounting end of the shell can be mounted on a shell of the aerospace system equipment and is in conduction with the shell; the protective member adopts a multi-layer staggered chip capacitor, the protective member is mounted in the shell, and the outer periphery of the protective member is electrically connected to the shell along the inner periphery of the shell, and a shielding body structure is formed between the protective member, the shell and the shell of the aerospace system equipment to prevent external electromagnetic pulses from entering the interior of the aerospace system equipment; the signal conduction component is mounted in the shell, the input end of the signal conduction component can be connected to a plug to receive a signal, the output end of the signal conduction component can be connected to the aerospace system equipment to transmit the signal to the aerospace system equipment, and the signal conduction component passes through the protective member so that the protective member can filter the electromagnetic pulses in the signal.

[0005] Through the above arrangement, firstly, the protective part is installed in the outer shell, which basically does not increase the volume of the connecting mechanism socket and has a more compact structure; secondly, a shielding structure is formed between the protective part and the outer shell and the shell of the aerospace system equipment to prevent electromagnetic pulses radiated from the outside; thirdly, multi-layer staggered chip capacitors are used as protective parts to filter electromagnetic pulses in signal conduction components, and the protection performance is comprehensive.

[0006] Furthermore, the outer periphery of the protective member is connected to the inner wall of the housing by welding or metal fasteners.

[0007] Furthermore, the connection mechanism socket also includes: a backplane and a panel; the backplane is installed at the mounting end of the shell, the protective piece is installed inside the backplane, and the output end of the signal conduction component passes through the backplane and is installed on the backplane; the panel is installed at the other end of the shell, and the input end of the signal conduction component passes through the panel and is installed on the panel.

[0008] With the above arrangement, the back plate and the front plate support the signal conducting components.

[0009] Furthermore, a closed active cavity is formed between the panel, the housing and the back plate; the signal conduction component includes: an input contact, an output contact and a movable contact sleeve; the input contact passes through the panel and is installed on the panel; the output contact is coaxially arranged with the input contact, and the output contact passes through the back plate and is installed on the back plate; the movable contact sleeve is coaxially arranged between the input contact and the output contact, a sliding sleeve at one end of the movable contact sleeve is arranged on the output contact, and a socket is arranged at the other end of the movable contact sleeve, and the movable contact sleeve can move along its axis so that the input contact is inserted into the socket, and the input contact is connected to the output contact through the movable contact sleeve.

[0010] Through the above arrangement, firstly, the signal is conducted through the input contact piece, the movable contact sleeve and the output contact piece; and secondly, it is convenient to repair the connection mechanism socket.

[0011] Furthermore, the connecting mechanism socket also includes a locking mechanism; the locking mechanism includes: a movable part, a locking sleeve and a spring; the movable part is slidably connected in the shell, and the movable contact sleeve is installed on the movable part; one end of the locking sleeve is installed on the movable part, a through hole is provided on the panel, the other end of the locking sleeve is slidably connected in the through hole, and a connecting groove that can cooperate with the plug is provided; the spring is connected to the movable part to apply a force toward the back plate to the movable part; the connecting mechanism socket includes a connected state and a disconnected state, when the connecting mechanism socket is in the connected state, the connecting groove cooperates with the plug, and the input contact is inserted into the socket of the movable contact sleeve; after the plug is disengaged from the connecting groove, the spring drives the movable part, and the input contact is disengaged from the movable contact sleeve, so that the connecting mechanism socket is in the disconnected state.

[0012] Through the above arrangement, the connection mechanism socket has an anti-short circuit function, which increases the stability and safety of the connection mechanism socket, thereby increasing the stability of the aerospace system equipment.

[0013] Furthermore, the locking mechanism also includes a guide rod, which is parallel to the movable contact sleeve, installed between the face plate and the back plate, and passes through the movable part and is slidably connected to the movable part.

[0014] Through the above arrangement, the stability of the movement of the movable part is increased.

[0015] Furthermore, the spring sleeve is arranged on the lock sleeve, one end of the spring is connected to the panel, and the other end of the spring is connected to the movable part.

[0016] Furthermore, a mounting hole is provided on the movable part, a boss is provided along the outer circumference of the lock sleeve, the locking mechanism also includes a nut, the end of the lock sleeve away from the panel passes through the mounting hole and is threadedly connected with the nut, and the movable part is locked between the boss and the nut.

[0017] Through the above arrangement, the locking sleeve is locked on the movable part through the nut and the boss. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the connection mechanism socket of the embodiment in a disconnected state.

[0019] Figure 2 It is a schematic diagram of the connection mechanism socket of the embodiment in a connected state. DETAILED DESCRIPTION

[0020] The technical solution of the present invention is further specifically described below through embodiments and in conjunction with the accompanying drawings.

[0021] See also Figure 1 to Figure 2 A connection mechanism socket for an aerospace system device comprises: a shell 1, a protective member 2 and a signal conduction component 3; the shell 1 is grounded, one end of the shell 1 is a mounting end, the mounting end of the shell 1 can be mounted on a shell of the aerospace system device and is in conduction with the shell; the protective member 2 adopts a multi-layer staggered chip capacitor, the protective member 2 is mounted in the shell 1, and the outer periphery of the protective member 2 is electrically connected to the shell along the inner periphery of the shell, and a shielding body structure is formed between the protective member 2, the shell 1 and the shell of the aerospace system device to prevent external electromagnetic pulses from entering the interior of the aerospace system device; the signal conduction component 3 is mounted in the shell 1, the input end of the signal conduction component 3 can be connected to a plug to receive a signal, the output end of the signal conduction component 3 can be connected to the aerospace system device to transmit the signal to the aerospace system device, and the signal conduction component 3 passes through the protective member 2 so that the protective member 2 filters the electromagnetic pulses in the signal.

[0022] Through the above arrangement, first, the protective member 2 is installed in the outer shell 1, which basically does not increase the volume of the connecting mechanism socket, and the structure is more compact; second, a shielding structure is formed between the protective member 2 and the outer shell 1 and the shell of the aerospace system equipment, which can prevent electromagnetic pulses radiated from the outside; third, the use of multi-layer staggered chip capacitors as the protective member 2 can filter the electromagnetic pulses in the signal conduction component 3, and the protection performance is comprehensive.

[0023] In the present application, the shell 1 is integrally formed of a metal material, and an installation cavity is provided in the shell 1, and the installation cavity runs through both ends of the shell 1; the installation end of the shell 1 can be installed on the shell of the aerospace system equipment through a fastener, and the shell 1 is grounded through the shell; the protective member 2 is a multi-layer staggered chip capacitor, which has the advantages of smaller size and large capacitance value. Specifically, the protective member 2 can adopt a multi-layer ceramic capacitor; the protective member 2 is horizontally installed in the shell, and when there is a radiated electromagnetic pulse from the outside, the electromagnetic pulse is introduced into the ground through the shielding body structure to prevent the radiated electromagnetic pulse from entering the aerospace system equipment; when in use, the plug matched with the connection mechanism socket is connected to the input end of the signal conduction component 3, and the output end of the signal conduction component 3 is connected to the inside of the aerospace system equipment. The plug transmits a signal to the aerospace system equipment through the signal conduction component 3. When an electromagnetic pulse doped with a non-conducting signal passes through the protective member 2, the electromagnetic pulse passes through the protective member 2 and the shell 1 and enters the ground, thereby preventing the electromagnetic pulse in the signal conduction component 3 from entering the inside of the aerospace system equipment.

[0024] As an implementation manner, the outer periphery of the protective element is connected to the inner wall of the housing by welding or metal fasteners.

[0025] As an implementation method, the connection mechanism socket also includes: a back panel 4 and a panel 5; the back panel 4 is installed at the installation end of the shell 1, the protective member 2 is installed in the back panel 4, and the output end of the signal conduction component 3 passes through the back panel 4 and is installed on the back panel 4; the panel 5 is installed at the other end of the shell 1, and the input end of the signal conduction component 3 passes through the panel 5 and is installed on the panel 5.

[0026] Through the above arrangement, the back plate 4 and the face plate 5 support the signal conducting component 3 .

[0027] In the present application, the outer end of the input end of the signal conduction component 3 is flush with the outer side of the panel 5 and is provided with a slot for easy plug insertion; the outer end of the output end of the signal conduction component 3 protrudes from the outer side of the back panel 4 so as to be connected to the aerospace system equipment.

[0028] As an implementation method, a closed active cavity is formed between the panel 5, the housing 1 and the back plate 4; the signal conduction component 3 includes: an input contact 31, an output contact 32 and a movable contact sleeve 33; the input contact 31 passes through the panel 5 and is installed on the panel 5; the output contact 32 is coaxially arranged with the input contact 31, and the output contact 32 passes through the back plate 4 and is installed on the back plate 4; the movable contact sleeve 33 is coaxially arranged between the input contact 31 and the output contact 32, one end of the movable contact sleeve 33 is slidingly sleeved on the output contact 32, and the other end of the movable contact sleeve 33 is provided with a socket 331, and the movable contact sleeve 33 can move along its axis so that the input contact 31 is inserted into the socket 331, and the input contact 31 is connected to the output contact 32 through the movable contact sleeve 33.

[0029] Through the above arrangement, firstly, the signal is conducted through the input contact 31, the movable contact sleeve 33 and the output contact 32; secondly, it is convenient to repair the connection mechanism socket.

[0030] In the present application, the input contact 31 is fixed on the panel 5. When the panel 5 or the input contact 31 needs to be repaired, the panel 5 is removed from the housing 1, and the input contact 31 is taken away together with the panel 5, so that it is convenient to repair the panel 5 and the input contact 31. Since the input contact 31 often needs to contact the plug, the input contact 31 can be replaced alone without replacing the entire signal transmission component 3, which is convenient for maintenance and saves costs. Similarly, the backplane 4 and the output contact 32 can also be replaced alone.

[0031] As an implementation method, the connection mechanism socket also includes a locking mechanism 6; the locking mechanism 6 includes: a movable part 61, a locking sleeve 62 and a spring 63; the movable part 61 is slidably connected in the housing 1, and the movable contact sleeve 33 is installed on the movable part 61; one end of the locking sleeve 62 is installed on the movable part 61, and a through hole 51 is provided on the panel 5, and the other end of the locking sleeve 62 is slidably connected in the through hole 51, and is provided with a connecting groove 621 that can cooperate with the plug; the spring 63 is connected to the movable part 61 to apply a force toward the back plate 4 to the movable part 61; the connection mechanism socket includes a connected state and a disconnected state. When the connection mechanism socket is in the connected state, the connecting groove 621 cooperates with the plug, and the input contact 31 is inserted into the socket 331 of the movable contact sleeve 33; after the plug is disengaged from the connecting groove 621, the spring 63 drives the movable part 61, and the input contact 31 is disengaged from the movable contact sleeve 33, so that the connection mechanism socket is in the disconnected state.

[0032] Through the above arrangement, the connection mechanism socket has an anti-short circuit function, which increases the stability and safety of the connection mechanism socket, thereby increasing the stability of the aerospace system equipment.

[0033] In the present application, the movable member 61 is made of insulating material. When the plug is connected to the socket of the connection mechanism, the plug is connected to the outer end of the input contact member 31. The plug is connected to the lock sleeve 62 through the connecting groove 621 and the lock sleeve 62 is pulled outward. The lock sleeve 62 drives the movable contact sleeve 33 to move toward the input contact member 31 through the movable member 61. After the input contact member 31 is inserted into the movable contact sleeve 33, see Figure 2 , the connection mechanism socket is in the connected state, and the plug can transmit signals to the aerospace system equipment through the input contact 31, the movable contact sleeve 33 and the output contact 32; when the plug is disconnected from the connection mechanism socket, see Figure 1On the one hand, the plug is separated from the input contact 31, and on the other hand, the plug is disengaged from the locking sleeve 62. The spring 63 drives the movable part 61 to move toward the back plate 4, so that the movable contact sleeve 33 is disengaged from the input contact 31, realizing the double-layer anti-short circuit function.

[0034] As an implementation method, the locking mechanism 6 further includes a guide rod 64 , which is parallel to the movable contact sleeve 33 , is installed between the panel 5 and the back panel 4 , and passes through the movable member 61 and is slidably connected to the movable member 61 .

[0035] Through the above arrangement, the stability of the movement of the movable member 61 is increased.

[0036] As an implementation method, the spring 63 is sleeved on the lock sleeve 62 , one end of the spring 63 is connected to the panel 5 , and the other end of the spring 63 is connected to the movable member 61 .

[0037] As an implementation method, a mounting hole 611 is provided on the movable part 61, a boss 622 is provided along the outer periphery of the locking sleeve 62, the locking mechanism 6 also includes a nut 65, the end of the locking sleeve 62 away from the panel 5 passes through the mounting hole 611 and is threadedly connected with the nut 65, and the movable part 61 is locked between the boss 622 and the nut 65.

[0038] Through the above arrangement, the locking sleeve 62 is locked on the movable member 61 through the nut 65 and the boss 622 .

[0039] It should be understood that those skilled in the art can make improvements or changes based on the above description, and all these improvements and changes should fall within the scope of protection of the appended claims of the present invention.

Claims

1. A connection mechanism socket for aerospace system equipment, characterized in that: include: A housing, the housing is grounded, one end of the housing is a mounting end, the mounting end of the housing can be mounted on a housing of an aerospace system device and is in electrical communication with the housing; A protective member, wherein the protective member adopts a multi-layer staggered chip capacitor, the protective member is installed in the shell, and the outer periphery of the protective member is electrically connected to the shell along the inner periphery of the shell, and a shielding structure is formed between the protective member, the shell and the shell of the aerospace system equipment to prevent external electromagnetic pulses from entering the interior of the aerospace system equipment; A signal conduction component is installed in the housing, an input end of the signal conduction component can be connected to a plug to receive a signal, an output end of the signal conduction component can be connected to the aerospace system equipment to transmit the signal to the aerospace system equipment, and the signal conduction component passes through the protective element so that the protective element filters the electromagnetic pulse in the signal.

2. A connection mechanism socket for aerospace system equipment according to claim 1, characterized in that: The outer periphery of the protective member is connected to the inner wall of the housing by welding or metal fasteners.

3. The connection mechanism socket of an aerospace system equipment according to claim 1, characterized in that: The connection mechanism socket also includes: A backplane, the backplane is mounted on the mounting end of the housing, the protective member is mounted inside the backplane, and the output end of the signal conducting component passes through the backplane and is mounted on the backplane; A panel is installed at the other end of the housing, and an input end of the signal conducting component passes through the panel and is installed on the panel.

4. A connection mechanism socket for aerospace system equipment according to claim 3, characterized in that: A closed active cavity is formed between the panel, the housing and the back panel; The signal transduction component comprises: an input contact member, the input contact member passing through the panel and mounted on the panel; An output contact, the output contact is coaxially arranged with the input contact, the output contact passes through the back plate and is mounted on the back plate; A movable contact sleeve is coaxially arranged between the input contact piece and the output contact piece, a sliding sleeve at one end of the movable contact sleeve is arranged on the output contact piece, and a socket is arranged at the other end of the movable contact sleeve. The movable contact sleeve can move along its axis so that the input contact piece is inserted into the socket and the input contact piece is connected to the output contact piece through the movable contact sleeve.

5. The connection mechanism socket of an aerospace system device according to claim 4, characterized in that: The connection mechanism socket also includes a locking mechanism; The locking mechanism comprises: A movable member, the movable member is slidably connected in the housing, and the movable contact sleeve is mounted on the movable member; A lock sleeve, one end of which is mounted on the movable part, a through hole is provided on the panel, the other end of which is slidably connected in the through hole and is provided with a connection groove that can cooperate with the plug; a spring connected to the movable member to apply a force to the movable member toward the back plate; The connection mechanism socket includes a connection state and a disconnection state. When the connection mechanism socket is in the connection state, the connection groove cooperates with the plug, and the input contact piece is inserted into the socket of the movable contact sleeve; after the plug is disengaged from the connection groove, the spring drives the movable piece, and the input contact piece is disengaged from the movable contact sleeve, so that the connection mechanism socket is in the disconnection state.

6. The connection mechanism socket of an aerospace system device according to claim 5, characterized in that: The locking mechanism further comprises a guide rod, the guide rod is parallel to the movable contact sleeve, the guide rod is installed between the face plate and the back plate, and the guide rod passes through the movable member and is slidably connected to the movable member.

7. The connection mechanism socket of an aerospace system device according to claim 5, characterized in that: The spring sleeve is arranged on the lock sleeve, one end of the spring is connected to the panel, and the other end of the spring is connected to the movable part.

8. The connection mechanism socket of an aerospace system device according to claim 5, characterized in that: The movable part is provided with a mounting hole, a boss is provided along the outer circumference of the locking sleeve, the locking mechanism also includes a nut, one end of the locking sleeve away from the panel passes through the mounting hole and is threadedly connected with the nut, and the movable part is locked between the boss and the nut.

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