CN220139916U - Spacecraft electronic single machine airtight structure - Google Patents

Abstract

The utility model provides an electronic single-machine airtight structure of a spacecraft. At least comprises a shell, a cover plate, a bottom plate and a sealing connector; one side of the shell is in sealing connection with the cover plate through a first sealing element, and the other side of the shell is in sealing connection with the bottom plate through a second sealing element; the inside of the shell is also provided with a printed board for installing components, and the printed board and the components are sealed in the shell by the cover plate and the bottom plate; the sealing connector is arranged on the cover plate and used for penetrating through the cover plate and being connected with the components through cables so as to realize signal and data transmission.

Description

Spacecraft electronic single machine airtight structure

Technical Field

The utility model relates to the technical field of spacecraft electronic single units, in particular to a spacecraft electronic single unit airtight structure.

Background

Currently, most of space electronic single units are in a laminated or spliced structure. The internal environment of the electronic single machine is the same as the external environment, and the internal environment of the electronic single machine is gradually changed into a high-vacuum environment along with the orbit of the spacecraft, so that the problems of layering of devices, vacuum discharge and the like are easy to occur. In order to adapt to a large number of commercial devices in the field of future commercial aerospace and solve the problems of vacuum discharge caused by layering of devices and loss of air pressure in a single unit, it is highly desirable to design an electronic single unit airtight structure of a spacecraft for preventing the loss of air pressure in the single unit.

Disclosure of Invention

In order to solve the technical problems, the utility model provides an electronic single-machine airtight structure of a spacecraft.

The utility model provides a spacecraft electronic single-machine airtight structure, which at least comprises a shell, a cover plate, a bottom plate and a sealing connector; one side of the shell is in sealing connection with the cover plate through a first sealing element, and the other side of the shell is in sealing connection with the bottom plate through a second sealing element; the inside of the shell is also provided with a printed board for installing components, and the printed board and the components are sealed in the shell by the cover plate and the bottom plate; the sealing connector is arranged on the cover plate and used for penetrating through the cover plate and being connected with the components through cables so as to realize signal and data transmission.

In one embodiment, the sealed connector includes an electrical connector body and an electrical connector pin; the electric connector body set up in the apron, electric connector contact pin install in electric connector body and run through the apron sets up.

In one embodiment, the first seal comprises a first inner seal ring and a first outer seal ring; a first inner sealing groove and a first outer sealing groove are formed in one side, connected with the cover plate, of the shell, the first inner sealing ring is installed in the first inner sealing groove, and the first outer sealing ring is installed in the first outer sealing groove; the cover plate is connected with the shell through screws, and the first inner sealing ring and the first outer sealing ring are tightly pressed between the cover plate and the shell, so that redundant sealing is realized.

In one embodiment, the second seal comprises a second inner seal ring and a second outer seal ring; a second inner sealing groove and a second outer sealing groove are formed in one side, connected with the shell, of the bottom plate, the second inner sealing ring is installed in the second inner sealing groove, and the second outer sealing ring is installed in the second outer sealing groove; the bottom plate is connected with the shell through screws, and the second inner sealing ring and the second outer sealing ring are tightly pressed between the bottom plate and the shell, so that redundant sealing is realized.

In one embodiment, the printed board is mounted to the housing by pan head screws and washers.

In any one of the above embodiments, the bottom plate is provided with an air vent; when ventilation is not needed, the ventilation hole is sealed by a plug; when ventilation is needed, the plug is disassembled and then the charging and discharging valve is installed for ventilation.

In one embodiment, the ventilation hole is a threaded hole, and a sealing gasket is arranged in the hole; the plug and the charging and discharging valve are respectively provided with threads matched with the threaded holes.

In one embodiment, the housing comprises four side plates, and each side plate is connected through a concave-convex buckle to form the housing.

In one embodiment, the cover plate, the bottom plate and each of the side plates are anodized.

In one embodiment, the sealing connector is integrally designed with the cover plate.

The electronic single-machine airtight structure of the spacecraft provided by the embodiment of the utility model has good airtight performance, can be freely disassembled and assembled, and can be completely sealed by welding the butt joint surface of the whole structure by utilizing laser welding after the final structure is determined by an airtight test.

The electronic single-machine airtight structure of the spacecraft, disclosed by the embodiment of the utility model, is applied to the airtight structure of the aerospace, and can greatly reduce low-pressure discharge and device layering failure rate through pressure maintaining of a full life cycle.

Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.

Drawings

In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 is an exploded view of the overall structure of a spacecraft electronic stand-alone containment structure in accordance with an embodiment of the present utility model.

Fig. 2 is a cross-sectional view of the whole structure of the electronic single-machine airtight structure of the spacecraft according to the embodiment of the utility model.

Fig. 3 is a schematic structural view of a sealing connector according to an embodiment of the present utility model.

Fig. 4 is a schematic diagram of a connection end structure of a printed board and a housing according to an embodiment of the present utility model.

Detailed Description

Features and exemplary embodiments of various aspects of the present utility model will be described in detail below, and in order to make the objects, technical solutions and advantages of the present utility model more apparent, the present utility model will be described in further detail below with reference to the accompanying drawings and the detailed embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the principles of the present utility model and not in limitation thereof. In addition, the mechanical components in the drawings are not necessarily to scale. For example, the dimensions of some of the structures or regions in the figures may be exaggerated relative to other structures or regions to help facilitate an understanding of embodiments of the present utility model.

The directional terms appearing in the following description are all directions shown in the drawings and do not limit the specific structure of the embodiment of the present utility model. In the description of the present utility model, it should be noted that, unless otherwise indicated, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present utility model can be understood as appropriate by those of ordinary skill in the art.

Furthermore, the terms "comprises," "comprising," "includes," "including," "having," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a structure or assembly that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such structure, assembly. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of other like elements in an article or apparatus that comprises the element.

Spatially relative terms such as "under", "below", "under …", "low", "above", "over …", "high", and the like, are used for convenience of description to explain the positioning of one element relative to a second element and to represent different orientations of the device in addition to those shown in the figures. In addition, for example, "one element above/below another element" may mean that two elements are in direct contact, or that other elements are present between the two elements. Furthermore, terms such as "first," "second," and the like, are also used to describe various elements, regions, sections, etc., and should not be taken as limiting. Like terms refer to like elements throughout the description.

It will be apparent to one skilled in the art that the present utility model may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the utility model by showing examples of the utility model.

Referring to fig. 1, the utility model provides a spacecraft electronic single-machine airtight structure, which at least comprises a shell 1, a cover plate 2, a bottom plate 3 and a sealing connector 4. Wherein, one side of the shell 1 is in sealing connection with the cover plate 2 through a first sealing element 5, and the other side is in sealing connection with the bottom plate 3 through a second sealing element 6. The interior of the shell 1 is also provided with a printed board 8 for mounting the components 7, and the printed board 8 and the components 7 are sealed in the shell 1 by the cover plate 2 and the bottom plate 3. The first sealing element 5 and the second sealing element 6 can strengthen the sealing effect and improve the sealing strength.

In order to facilitate the transmission of data and signals between the components inside the housing 1 and the outside, a sealing connector 4 may be provided on the cover plate 2. The sealing insert 4 can pass through the cover plate 2 and be connected with the component 7 through a cable so as to realize signal and data transmission. The sealing plug-in 4 can be welded with the cover plate 2 into a whole in a laser welding mode, so that the vacuum leakage rate of the sealing plug-in 4 and the cover plate is smaller than 1 x 10 < -9 > Pa m3/s, the sealing effect of the whole sealing structure can be ensured, and the sealing structure is ensured to have a proper working environment in space.

Referring also to fig. 2 and 3, in one embodiment, the sealing connector 4 includes an electrical connector body 41 and an electrical connector pin 42. The electrical connector body 41 and the electrical connector pins 42 may be assembled into the hermetic connector 4 by glass sintering. The electrical connector body 41 is disposed on the cover plate 2, and the electrical connector pins 42 are mounted on the electrical connector body 41 and penetrate through the cover plate 2 for connection with the component 7 through cables. The assembled sealing connector can be welded with the cover plate 2 into a whole in a laser welding mode, so that the vacuum leakage rate of the sealing connector and the cover plate is ensured to be less than 1 x 10 < -9 > Pa x 3/s.

In the above embodiment, the component includes at least the PCB.

Referring to both fig. 1 and 2, in one embodiment, the first seal 5 includes a first inner seal ring 51 and a first outer seal ring 52. The housing 1 is provided with a first inner seal groove 11 and a first outer seal groove 12 on the side which is connected with the cover plate 2, and the seal grooves are required to be clean and have no excessive residues before assembly. When assembled, the first inner seal ring 51 is mounted in the first inner seal groove 11, and the first outer seal ring 52 is mounted in the first outer seal groove 12. After the cover plate 2 is connected with the shell 1 through the screws, the first inner sealing ring 51 and the first outer sealing ring 52 can be pressed between the cover plate 2 and the shell 1, so that redundant sealing and sealing effect improvement are realized. Wherein, the outer edge chamfer setting of casing 1 and apron 2 contact end has avoided the stress concentration that the acute angle caused.

According to the electronic single-machine airtight structure of the spacecraft, the sealing between the cover plate and the shell is realized through the sealing rings of the inner ring and the outer ring, the tolerance margin control is strictly carried out on the matching between the cover plate and the shell according to the actual requirement of the sealing piece, and the effectiveness of the structural matching is ensured.

With continued reference to fig. 1 and 2, in one embodiment, the second seal 6 includes a second inner seal ring 61 and a second outer seal ring 62. The side of the bottom plate 3, which is used for being connected with the shell 1, is provided with a second inner sealing groove 31 and a second outer sealing groove 32, and the sealing grooves are required to be clean and free of excessive materials before being assembled. When assembled, the second inner seal ring 61 is mounted in the second inner seal groove 31 and the second outer seal ring 62 is mounted in the second outer seal groove 32. After the bottom plate 3 is connected with the shell 1 through the screws, the second inner sealing ring 61 and the second outer sealing ring 62 can be pressed between the bottom plate 3 and the shell 1, so that redundant sealing and sealing effect improvement are realized.

According to the electronic single-machine airtight structure of the spacecraft, the sealing between the cover plate and the shell is realized through the sealing rings of the inner ring and the outer ring, the tolerance margin control is strictly carried out on the matching between the bottom plate and the shell according to the actual requirement of the sealing piece, and the effectiveness of the structural matching is ensured.

Referring to fig. 1 and 4 together, in one embodiment, the printed board 8 is mounted inside the housing 1 by means of pan head screws 81 and washers 82. Specifically, a printed board mounting surface is provided at a position approximately in the middle of the housing 1 for mounting the printed board 8 on the housing 1. After the printed board 8 is in place with the printed board mounting surface, the locking is fixed by using the pan head screw 81 and the washer 82. According to the electronic single-machine airtight structure of the spacecraft, disclosed by the embodiment of the utility model, the vibration transmission can be reduced by utilizing the gasket, the vibration amplitude of an internal device is reduced, and the fatigue and impact damage of the device are reduced.

Referring to fig. 1, in any of the above embodiments, the base plate 3 is further provided with ventilation holes 33. When ventilation is not needed, the ventilation hole 33 is sealed by the plug 34, and when ventilation is needed, the plug 34 is disassembled and then the charging and discharging valve is installed for ventilation.

In the above embodiment, in order to secure the sealing effect of the spacecraft electronic stand-alone sealing structure, the gasket 35 may be provided in the ventilation hole 33. The plug 34 passes through the sealing gasket 35 and presses the plug against the edge of the ventilation hole 33, so that the plug is ensured to be capable of completely sealing the ventilation hole.

In one embodiment, in order to facilitate replacement and disassembly of the plug and the charging and discharging valve, the ventilation hole may be provided with a threaded hole, and the plug and the charging and discharging valve are respectively provided with threads matched with the threaded hole. After the plug is screwed into the threaded hole, a certain moment is applied, so that the effectiveness of thread sealing can be maintained. When ventilation is needed, the plug can be screwed off, and then the threaded charging and discharging valve is replaced, so that ventilation of gas in the airtight structure is completed. After the air is changed, the adding and discharging valve can be directly disassembled, and the upper plug is replaced to realize sealing. Because the internal and external pressure is the same after ventilation, the effect of the internal gas after ventilation can not be influenced by adding the discharge valve to replace the sealing plug in a short period.

After final debugging of the product is finished, the interfaces between the shell and the cover plate, between the shell and the bottom plate and between the plug and the bottom plate can be fully sealed in a welding mode, so that the tightness of the electronic single-machine airtight structure of the spacecraft can be greatly improved.

In one embodiment, the housing comprises four side plates, each of which is connected by a male-female snap to form the housing. The shell is connected with the bottom plate and the cover plate through the screws, so that the contact resistance of the adjacent shell is reduced, good shielding is facilitated, and the vibration resistance of the structure is improved.

The screw and the nut used by the airtight structure of the embodiment of the utility model are standard components. If the maintenance requirement exists, the standard component can be directly selected for replacement, and the interchangeability is good.

Further, tantalum sheets or lead skins can be attached to the inner sides of the side plates to reduce external radiation. Alternatively, the bottom plate, the cover plate, and the respective side plates may be anodized.

The structural seal is sealed by a sealing gasket, and the material is usually fluororubber or silicon rubber. The rubber has excellent high and low temperature resistance, good electrical property and irradiation resistance, and can meet the severe conditions of space environment.

In order to ensure that the leak rate meets the requirements, a sealed vacuum connector is used as the sealed connector. The connector is welded on the cover plate, and the whole vacuum leakage rate of the connector after the welding is completed is less than 1 x 10 < -9 > Pa m3/s, so that the sealed device is ensured to have a proper working environment in the sky within the design life.

In one embodiment, the sealing connector and the cover plate are integrally designed, so that the vacuum leakage rate can be further reduced.

The above-described embodiments of the present utility model can be combined with each other with corresponding technical effects.

The spacecraft electronic single-machine airtight structure can greatly reduce low-pressure discharge and device layering failure rate through pressure maintaining in a full life cycle. The whole structure is sealed, the product is sealed by adopting a sealing gasket convenient to disassemble and assemble, the operation is simple, and the cost is low. The connector adopts a sealed vacuum connector or uses a connector pin and a ferrule to directly sinter with the structure, so that the internal gas leakage rate is reduced, and the stable working environment of the airtight device in space is ensured.

The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the utility model.

Claims (10)

1. The electronic single-machine airtight structure of the spacecraft is characterized by at least comprising a shell, a cover plate, a bottom plate and a sealing connector;

one side of the shell is in sealing connection with the cover plate through a first sealing element, and the other side of the shell is in sealing connection with the bottom plate through a second sealing element; the inside of the shell is also provided with a printed board for installing components, and the printed board and the components are sealed in the shell by the cover plate and the bottom plate;

the sealing connector is arranged on the cover plate and used for penetrating through the cover plate and being connected with the components through cables so as to realize signal and data transmission.

2. The spacecraft electronic stand-alone containment structure of claim 1, wherein said sealed connector comprises an electrical connector body and an electrical connector pin; the electric connector body set up in the apron, electric connector contact pin install in electric connector body and run through the apron sets up.

3. The spacecraft electronic stand-alone containment structure of claim 1, wherein said first seal comprises a first inner seal ring and a first outer seal ring; a first inner sealing groove and a first outer sealing groove are formed in one side, connected with the cover plate, of the shell, the first inner sealing ring is installed in the first inner sealing groove, and the first outer sealing ring is installed in the first outer sealing groove;

the cover plate is connected with the shell through screws, and the first inner sealing ring and the first outer sealing ring are tightly pressed between the cover plate and the shell, so that redundant sealing is realized.

4. The spacecraft electronic stand-alone containment structure of claim 1, wherein said second seal comprises a second inner seal ring and a second outer seal ring; a second inner sealing groove and a second outer sealing groove are formed in one side, connected with the shell, of the bottom plate, the second inner sealing ring is installed in the second inner sealing groove, and the second outer sealing ring is installed in the second outer sealing groove;

the bottom plate is connected with the shell through screws, and the second inner sealing ring and the second outer sealing ring are tightly pressed between the bottom plate and the shell, so that redundant sealing is realized.

5. The electronic single-machine airtight structure of a spacecraft of claim 1, wherein said printed board is mounted to said case by pan head screws and washers.

6. The spacecraft electronic stand-alone containment structure of any of claims 1 to 5, wherein said base plate is provided with ventilation holes; when ventilation is not needed, the ventilation hole is sealed by a plug; when ventilation is needed, the plug is disassembled and then the charging and discharging valve is installed for ventilation.

7. The electronic single-machine airtight structure of spacecraft according to claim 6, wherein said ventilation hole is a threaded hole, and a gasket is provided inside; the plug and the charging and discharging valve are respectively provided with threads matched with the threaded holes.

8. The electronic single-machine airtight structure of spacecraft according to claim 6, wherein said housing comprises four side plates, each of which constitutes said housing by means of a male-female snap connection.

9. The electronic single-machine airtight structure for a spacecraft of claim 8, wherein said cover plate, said bottom plate and each of said side plates are anodized.

10. The spacecraft electronic stand-alone containment structure of claim 1, wherein said sealing connector is integrally designed with said cover plate.