CN203224177U - Sleeve sealing structure for cabin segment - Google Patents
Sleeve sealing structure for cabin segment Download PDFInfo
- Publication number
- CN203224177U CN203224177U CN 201320098782 CN201320098782U CN203224177U CN 203224177 U CN203224177 U CN 203224177U CN 201320098782 CN201320098782 CN 201320098782 CN 201320098782 U CN201320098782 U CN 201320098782U CN 203224177 U CN203224177 U CN 203224177U
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- area
- sealing
- cabin
- section
- ring
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- Expired - Lifetime
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Abstract
The utility model relates to a sleeve sealing structure for a cabin segment. The sleeve sealing structure is characterized by comprising an outer-ring cabin segment with a transition guide bevel, and an inner-ring cabin segment matched with the outer-ring cabin segment, and the matched surface of the outer-ring cabin segment and the inner-ring cabin segment is axially divided into a connecting area, a transition guide area and a sealing area; and the radial height of the sealing area is lower than the radial height of the connecting area, and the transition guide area is a tapered surface for connecting the sealing area with the connecting area. According to the difference between functions, the sleeve part of the sleeve cabin segment is divided into a sealing area and a screw connecting area, the height difference between the sealing area and the screw connecting area exists, the screw connecting area is higher than the sealing area, and a guide transition area is arranged between the sealing area and the screw connecting area, accordingly, the situation that a sealing ring is stuck to be damaged by the edge of the end face of the outer-ring cabin segment and the edge of a screw hole to result in sealing failure during assembly is avoided.
Description
Technical field
The utility model relates to the cabin section socket hermetically-sealed construction of a kind of hermetically-sealed construction, particularly a kind of guided missile.
Background technology
Guided missile in use residing natural environment is often very complicated, and for guaranteeing equipment in the bullet, cable, connector etc. is in good working order, must take the measure that seals.Way commonly used is that body is sealed.The most important part of body sealing is exactly the sealing of connecting portion between each cabin section.For guided missile, the cabin section connects the general socket form that adopts, as shown in Figure 1, be specially: the inside and outside surface that the connection box of cabin, two adjacent compartment section outer rings section 1 and inner ring cabin section 2 is processed into cylinder respectively, utilize their mating surface to carry out socket, be connected and fixed with the plate nut 5 of radial bolts 4 with the band hermetically-sealed construction along circumference then.The general seal with O ring that adopts of the connection sealing of this form, O-ring seals 3 generally is placed in the rectangle groove (seal groove) 10 and uses, and the screen resilience that relies on sealing ring compression back to produce gives sealing contact surface with certain pressure, reaches sealing purpose.The standardization of the size of sealing ring and seal groove.This cabin section connects hermetically-sealed construction and has following shortcoming: (1) when assembling, sealing ring is hindered at cabin, outer ring section end surface edge and screw hole edge card easily, causes seal failure; (2) sealing at plate nut place is difficult to solve.
The utility model content
The purpose of this utility model provides a kind of cabin section socket hermetically-sealed construction, comprise cabin, the outer ring section with transition guiding surface and the inner ring cabin section that cooperates with it, the mating surface of described outer ring cabin section and inner ring cabin section is divided into bonding pad, transition guide portion and seal area vertically; Wherein, the radial height of described seal area is lower than the radial height of described bonding pad, and described transition guide portion is for connecting the coned face of seal area and bonding pad.
Further, cabin, described outer ring section can adopt sunk screw to fixedly connected in the bonding pad with inner ring cabin section.Described inner ring cabin section can arrange certain thickness boss in the inboard at position, bonding pad, is processed with on the described boss for the blind hole that connects described sunk screw.
Technique effect of the present utility model is: the belled position of socket cabin section is according to the function difference, be divided into seal area and screw bonding pad, there is difference in height seal area and screw bonding pad, screw connects the district and is higher than seal area, and between seal area and screw bonding pad, the guiding transition region is arranged, can avoid like this when assembling, cabin, outer ring section end surface edge and screw hole edge card are hindered sealing ring, cause seal failure.In addition, the utility model has also increased the thickness of supporting plate, and changes bolt connection of the prior art into the sunk screw connection, thereby has solved the seal failure problem at section palet nut place, inner ring cabin.
Fig. 1 is the cabin section socket sealed structural representation of guided missile in the prior art;
Fig. 2 is section socket sealed structural representation in cabin of the present utility model; Wherein:
1. cabin, outer ring section 2. inner ring cabin section 3. sealing rings, 4. screws (bolt)
5. plate nut 6. screw blind holes 7. seal areas 8. transition guide portion
9. bonding pad 10. seal grooves 11. boss 12. transition guiding surfaces
The specific embodiment
Below in conjunction with accompanying drawing, by specific embodiment the utility model is elaborated.
As shown in Figure 2, be a most preferred embodiment of the utility model cabin section socket bindiny mechanism, comprise cabin, outer ring section 1 and inner ring with matching cabin section 2 with transition guiding surface 12.The mating surface of cabin, outer ring section 1 and inner ring cabin section 2 is divided into seal area 7, transition guide portion 8 and bonding pad 9.Wherein, the radial height of seal area 7 is lower than the radial height of bonding pad 9, and transition guide portion 8 is for connecting the conical transition face of seal area 7 and bonding pad 9.
Inner ring cabin section 2 is provided with certain thickness boss 11 in the inboard at position, bonding pad, be processed with screw blind hole 6 on the boss 11, and cabin, outer ring section 1 is processed with counter sink in the relevant position of bonding pad, so that available sunk screw 4 is fixedly connected between the two cabin sections.
Inner ring cabin section 2 also is provided with seal groove 10 at the seal area position, is used for holding sealing ring 3 to reach the purpose of sealing.During assembling, earlier sealing ring 3 is placed in the seal groove 10, then two cabin section sockets are got up.In the cover termination process, because the height of seal area 7 is lower than the height of bonding pad 9, therefore can avoid the end face edge of cabin, outer ring section 1 and sunk screw hole contact card to hinder sealing ring.At last, tighten all radial screws 4, finish connection and the sealing of socket cabin section.
Claims (4)
1. a cabin section socket hermetically-sealed construction is characterized in that, comprises cabin, the outer ring section with transition guiding surface and the inner ring cabin section that cooperates with it, and the mating surface of described outer ring cabin section and inner ring cabin section is divided into bonding pad, transition guide portion and seal area vertically; Wherein, the radial height of described seal area is lower than the radial height of described bonding pad, and described transition guide portion is for connecting the coned face of seal area and bonding pad.
2. hermetically-sealed construction as claimed in claim 1 is characterized in that, cabin, described outer ring section is fixedlyed connected with sunk screw in the bonding pad with inner ring cabin section.
3. hermetically-sealed construction as claimed in claim 2 is characterized in that, described inner ring cabin section is provided with certain thickness boss in the inboard at position, bonding pad, is processed with on the described boss for the blind hole that connects described sunk screw.
4. hermetically-sealed construction as claimed in claim 1 is characterized in that, described seal area adopts the sealing ring sealing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320098782 CN203224177U (en) | 2013-03-05 | 2013-03-05 | Sleeve sealing structure for cabin segment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320098782 CN203224177U (en) | 2013-03-05 | 2013-03-05 | Sleeve sealing structure for cabin segment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203224177U true CN203224177U (en) | 2013-10-02 |
Family
ID=49251180
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320098782 Expired - Lifetime CN203224177U (en) | 2013-03-05 | 2013-03-05 | Sleeve sealing structure for cabin segment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203224177U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105737689A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Cabin segment abut-joint sealing structure |
| CN113645794A (en) * | 2021-07-15 | 2021-11-12 | 北京遥测技术研究所 | Double-layer convolution type sealing structure and method based on height difference |
| CN113928506A (en) * | 2021-11-05 | 2022-01-14 | 西北工业大学 | Large-section connecting structure and tool of supercavitation high-speed navigation test prototype |
| CN115929757A (en) * | 2022-12-13 | 2023-04-07 | 西安现代控制技术研究所 | Sealing ring protection structure for radial screw connection |
-
2013
- 2013-03-05 CN CN 201320098782 patent/CN203224177U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105737689A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Cabin segment abut-joint sealing structure |
| CN113645794A (en) * | 2021-07-15 | 2021-11-12 | 北京遥测技术研究所 | Double-layer convolution type sealing structure and method based on height difference |
| CN113645794B (en) * | 2021-07-15 | 2023-01-06 | 北京遥测技术研究所 | Double-layer convolution type sealing structure and method based on height difference |
| CN113928506A (en) * | 2021-11-05 | 2022-01-14 | 西北工业大学 | Large-section connecting structure and tool of supercavitation high-speed navigation test prototype |
| CN115929757A (en) * | 2022-12-13 | 2023-04-07 | 西安现代控制技术研究所 | Sealing ring protection structure for radial screw connection |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20131002 |