CN113619804A - Integrated adapter - Google Patents
Integrated adapter Download PDFInfo
- Publication number
- CN113619804A CN113619804A CN202111007623.8A CN202111007623A CN113619804A CN 113619804 A CN113619804 A CN 113619804A CN 202111007623 A CN202111007623 A CN 202111007623A CN 113619804 A CN113619804 A CN 113619804A
- Authority
- CN
- China
- Prior art keywords
- adapter
- grooves
- adapter body
- integrated
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 11
- 229920005830 Polyurethane Foam Polymers 0.000 claims abstract description 5
- 239000011496 polyurethane foam Substances 0.000 claims abstract description 5
- 238000005187 foaming Methods 0.000 claims abstract description 4
- 230000006835 compression Effects 0.000 claims description 18
- 238000007906 compression Methods 0.000 claims description 18
- 235000017166 Bambusa arundinacea Nutrition 0.000 abstract description 2
- 235000017491 Bambusa tulda Nutrition 0.000 abstract description 2
- 241001330002 Bambuseae Species 0.000 abstract description 2
- 235000015334 Phyllostachys viridis Nutrition 0.000 abstract description 2
- 230000003044 adaptive effect Effects 0.000 abstract description 2
- 239000011425 bamboo Substances 0.000 abstract description 2
- 239000000463 material Substances 0.000 description 3
- -1 etc.) Polymers 0.000 description 2
- JOYRKODLDBILNP-UHFFFAOYSA-N Ethyl urethane Chemical compound CCOC(N)=O JOYRKODLDBILNP-UHFFFAOYSA-N 0.000 description 1
- 229920000181 Ethylene propylene rubber Polymers 0.000 description 1
- 244000043261 Hevea brasiliensis Species 0.000 description 1
- 229920000459 Nitrile rubber Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229920005549 butyl rubber Polymers 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 229920003052 natural elastomer Polymers 0.000 description 1
- 229920001194 natural rubber Polymers 0.000 description 1
- 229920001084 poly(chloroprene) Polymers 0.000 description 1
- 229920003225 polyurethane elastomer Polymers 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention provides an integrated adapter, which comprises an adapter body; the adapter body is cylindrical, a plurality of grooves are distributed on the adapter body, and the distribution direction of the grooves is parallel to the axial direction of the adapter body; and reinforcing ribs parallel to the grooves are arranged at the intermittent positions of the grooves, and flange structures are arranged on the reinforcing ribs. The invention can ensure that the adapter meets the use function; the adapter body is formed by foaming polyurethane foam through a mould, so that the light design of the adapter is ensured; pin holes do not need to be arranged on the surface of the aircraft, so that the aircraft is prevented from being influenced by the adaptive adapter; the cambered surface of the adapter is matched with the semi-circular surface at the front end of the aircraft, so that the matching and supporting are reliable, the function of driving the adapter to move is met, and the structure and function integrated design is met; the adapter sets up weak region, guarantees that the adapter can reliably fracture the split again in a section of thick bamboo reliable spacing.
Description
Technical Field
The invention relates to an integrated adapter.
Background
The adapter is used as an important component of the launching device of the aircraft, is a connecting and supporting device between the aircraft and the launching device, and mainly has the functions of slowing down the impact and vibration of the aircraft caused by overload in the processes of storage, hoisting, transportation and launching of the aircraft and guiding the aircraft during launching. In recent years, due to the development of the adapter, adapter materials have been developed to adapt to different platforms, and the materials used mainly include rubber (such as natural rubber, nitrile rubber, butyl rubber, ethylene propylene rubber, neoprene rubber, etc.), polyurethane elastomer, polyurethane foam, and the like, or a mixture of the above materials. However, the adapter in the prior art is unreasonable in structural design, cannot well meet the required use performance, and does not meet the requirements of economy, manufacturability, practicability and operability.
Disclosure of Invention
In order to solve the technical problems, the invention provides an integrated adapter which can guarantee various technical requirements of the adapter, meet the use performance of the adapter and meet the requirements of economy, manufacturability, practicability and operability.
The invention is realized by the following technical scheme.
The invention provides an integrated adapter, which comprises an adapter body; the adapter body is cylindrical, a plurality of grooves are distributed on the adapter body, and the distribution direction of the grooves is parallel to the axial direction of the adapter body; and reinforcing ribs parallel to the grooves are arranged at the intermittent positions of the grooves, and flange structures are arranged on the reinforcing ribs.
The inner diameter of the inner wall of the adapter body close to the front end is gradually reduced.
And a compression spring is embedded in the position, located at the rear part of the flange structure, on the inner wall of the adapter body.
The compression spring is arranged on the spring mounting seat.
A support sleeve is arranged between the compression spring and the inner wall of the adapter body, and a limiting sleeve is arranged at the outer end of the support sleeve.
The inner wall of the adapter body is also provided with a support sleeve which passes through the limit sleeve through a compression screw to be installed and fixed.
The adapter body is formed by foaming polyurethane foam through a mould.
The grooves and the reinforcing ribs are uniformly distributed along the circumference in four ways.
The invention has the beneficial effects that: the adapter can be ensured to meet the use function; the adapter body is formed by foaming polyurethane foam through a mould, so that the light design of the adapter is ensured; pin holes do not need to be arranged on the surface of the aircraft, so that the aircraft is prevented from being influenced by the adaptive adapter; the cambered surface of the adapter is matched with the semi-circular surface at the front end of the aircraft, so that the matching and supporting are reliable, the function of driving the adapter to move is met, and the structure and function integrated design is met; the adapter sets up weak region, guarantees that the adapter can reliably fracture the split again in a section of thick bamboo reliable spacing.
Drawings
FIG. 1 is a schematic structural view of the present invention;
fig. 2 is a schematic view of the half-section structure of fig. 1.
In the figure: 1-an adapter body, 2-a spring mounting seat, 3-a supporting sleeve, 4-a limiting sleeve, 5-a compression spring and 6-a compression screw.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
Example 1
An integrated adapter shown in fig. 1 and 2 comprises an adapter body 1; the adapter body 1 is cylindrical, a plurality of grooves are distributed on the adapter body 1, and the distribution direction of the grooves is parallel to the axial direction of the adapter body 1; and reinforcing ribs parallel to the grooves are arranged at the intermittent positions of the grooves, and flange structures are arranged on the reinforcing ribs.
Example 2
Based on embodiment 1, the inner diameter of the inner wall of the adapter body 1 is gradually reduced near the front end.
Example 3
Based on embodiment 1, a compression spring 5 is embedded in a position at the rear of the flange structure on the inner wall of the adapter body 1.
Example 4
Based on embodiment 3, the compression spring 5 is mounted on the spring mount 2.
Example 5
Based on embodiment 3, there is a support sleeve 3 between the compression spring 5 and the inner wall of the adapter body 1, and a position limiting sleeve 4 is arranged at the outer end of the support sleeve 3.
Example 6
Based on embodiment 5, the inner wall of the adapter body 1 is further provided with a support sleeve 3, and the support sleeve 3 passes through the limit sleeve 4 through a compression screw 6 to be installed and fixed.
Example 7
Based on example 1, the adapter body 1 was foam-molded with urethane foam by a mold.
Example 8
Based on embodiment 1, the grooves and the reinforcing ribs are all uniformly distributed along the circumference in four ways.
Example 9
Based on the above embodiment, mainly by adapter body 1, spring mount 2, support set 3, stop collar 4, compression spring 5, housing screw 6 etc. constitute. The adapter adopts a split structure, and the components of each split structure are the same. The adapter body 1 is molded by a mold, the spring mounting seat 2, the support sleeve 3, the limiting sleeve 4 and the compression spring 5 are assembled and combined with the adapter body 1 into a whole through the compression screw 6 after being processed, and the adapter after being assembled is mounted between the launching tube and the aircraft and is fixed on the launching tube to limit the radial movement of the aircraft. The adapter is different from a common adapter which is matched with a pin hole in an aircraft, the aircraft does not need to be provided with a matching pin hole, the front end of the aircraft is supported and limited, and the adapter is fixedly arranged on a flange on the front end surface of the launch canister. The adapter body 1 is provided with a weakening groove, during launching, the adapter is driven to move forwards to shear the weakened groove of the adapter body 1, after a certain acting force is exceeded, the adapter breaks from the groove, and the adapter continues to move forwards along with the aircraft and is separated from the aircraft and falls off under the action of the compression spring 5 after being discharged from the cylinder.
Claims (8)
1. An integrated adapter comprising an adapter body (1), characterized in that: the adapter body (1) is cylindrical, a plurality of grooves are distributed on the adapter body (1), and the distribution direction of the grooves is parallel to the axial direction of the adapter body (1); and reinforcing ribs parallel to the grooves are arranged at the intermittent positions of the grooves, and flange structures are arranged on the reinforcing ribs.
2. The integrated adapter of claim 1, wherein: the inner diameter of the inner wall of the adapter body (1) close to the front end is gradually reduced.
3. The integrated adapter of claim 1, wherein: and a compression spring (5) is embedded in the position, located at the rear part of the flange structure, on the inner wall of the adapter body (1).
4. The integrated adapter of claim 3, wherein: the compression spring (5) is arranged on the spring mounting seat (2).
5. The integrated adapter of claim 3, wherein: a supporting sleeve (3) is arranged between the compression spring (5) and the inner wall of the adapter body (1), and a limiting sleeve (4) is arranged at the outer end of the supporting sleeve (3).
6. The integrated adapter of claim 5, wherein: the adapter is characterized in that a support sleeve (3) is further arranged on the inner wall of the adapter body (1) and penetrates through a limiting sleeve (4) through a compression screw (6) to be installed and fixed.
7. The integrated adapter of claim 1, wherein: the adapter body (1) is formed by foaming polyurethane foam through a die.
8. The integrated adapter of claim 1, wherein: the grooves and the reinforcing ribs are uniformly distributed along the circumference in four ways.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111007623.8A CN113619804A (en) | 2021-08-30 | 2021-08-30 | Integrated adapter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111007623.8A CN113619804A (en) | 2021-08-30 | 2021-08-30 | Integrated adapter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113619804A true CN113619804A (en) | 2021-11-09 |
Family
ID=78388549
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111007623.8A Pending CN113619804A (en) | 2021-08-30 | 2021-08-30 | Integrated adapter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113619804A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104266545A (en) * | 2014-09-23 | 2015-01-07 | 中国运载火箭技术研究院 | Underwater horizontal hot launching device |
| CN105643947A (en) * | 2015-12-09 | 2016-06-08 | 上海复合材料科技有限公司 | Missile adapter co-curing molding technique |
| CN207866112U (en) * | 2017-10-13 | 2018-09-14 | 南京理工大学 | A kind of new adaptor being applicable to special-shaped bullet |
| CN110193208A (en) * | 2019-05-23 | 2019-09-03 | 北京机电工程研究所 | Aircraft model transmitting tube adapter and model emission test system |
| CN212195970U (en) * | 2020-05-13 | 2020-12-22 | 贵州航天天马机电科技有限公司 | Lightweight adapter |
| CN112124611A (en) * | 2020-08-22 | 2020-12-25 | 西安科为实业发展有限责任公司 | Shelling and separating system and method for cylindrical jet type folding wing aircraft |
| CN112729007A (en) * | 2020-12-03 | 2021-04-30 | 上海复合材料科技有限公司 | Missile adapter, forming process method thereof and missile launching device |
-
2021
- 2021-08-30 CN CN202111007623.8A patent/CN113619804A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104266545A (en) * | 2014-09-23 | 2015-01-07 | 中国运载火箭技术研究院 | Underwater horizontal hot launching device |
| CN105643947A (en) * | 2015-12-09 | 2016-06-08 | 上海复合材料科技有限公司 | Missile adapter co-curing molding technique |
| CN207866112U (en) * | 2017-10-13 | 2018-09-14 | 南京理工大学 | A kind of new adaptor being applicable to special-shaped bullet |
| CN110193208A (en) * | 2019-05-23 | 2019-09-03 | 北京机电工程研究所 | Aircraft model transmitting tube adapter and model emission test system |
| CN212195970U (en) * | 2020-05-13 | 2020-12-22 | 贵州航天天马机电科技有限公司 | Lightweight adapter |
| CN112124611A (en) * | 2020-08-22 | 2020-12-25 | 西安科为实业发展有限责任公司 | Shelling and separating system and method for cylindrical jet type folding wing aircraft |
| CN112729007A (en) * | 2020-12-03 | 2021-04-30 | 上海复合材料科技有限公司 | Missile adapter, forming process method thereof and missile launching device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20211109 |