CN211601729U - Reinforcing structure of missile launcher - Google Patents
Reinforcing structure of missile launcher Download PDFInfo
- Publication number
- CN211601729U CN211601729U CN202020082715.7U CN202020082715U CN211601729U CN 211601729 U CN211601729 U CN 211601729U CN 202020082715 U CN202020082715 U CN 202020082715U CN 211601729 U CN211601729 U CN 211601729U
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- Prior art keywords
- launcher
- reinforcing
- missile
- main body
- suspension
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Abstract
A reinforcing structure of a missile launcher is used for reinforcing a suspended part of a carbon fiber composite missile launcher; the launcher comprises a launcher main body, wherein a pair of coaxial hanging holes are formed in the hanging part of the launcher main body; the launcher also comprises a pair of stiffening plates arranged on the inner side of the launcher main body, wherein the stiffening plates are provided with suspension shaft sleeves correspondingly matched with the suspension holes; the launcher main body is connected with the reinforcing plate through a plurality of rivets. The suspension shaft sleeve of the utility model increases the contact area between the suspension part and the suspension shaft, and disperses the contact stress; the stiffening plate is connected with the launcher main part, has strengthened the intensity of guided missile launcher linkage. The utility model discloses strengthen the intensity of guided missile launcher mounted part, improved the security of guided missile transmission, had that the implementation is strong, characteristics with low costs.
Description
Technical Field
The utility model belongs to the technical field of the guided missile technique and specifically relates to a reinforcement structure of guided missile launcher is related to.
Background
The carbon fiber composite material is widely applied to the field of aviation due to the characteristics of light weight and high strength. The missile launcher of some kind of aircraft also adopts carbon fiber composite material. However, there are insufficient strength in the suspended portion of the missile launcher, especially the suspension hole. The suspension hole is connected with a suspension shaft of the aircraft to bear the weight of the missile and the launcher. The suspension hole is formed by drilling at the later stage, the contact surface is small, the stress is large, and the drilling destroys the fiber organization structure of the carbon fiber composite material at the position, so that the strength of the suspension part is reduced, and the safety of missile launching is influenced.
In view of this, with the abundant design development and practical manufacturing experience of the related industry for many years, the existing structure and deficiency are researched and improved, and a reinforcing structure of the missile launcher is provided to achieve the purpose of higher strength.
SUMMERY OF THE UTILITY MODEL
In order to overcome not enough in the background art, the utility model discloses a reinforcing structure of guided missile launcher, its aim at: the strength of the hanging part of the missile launcher is enhanced, and the safety of missile launching is improved.
In order to realize the purpose of the utility model, the utility model adopts the following technical scheme:
a reinforcing structure of a missile launcher is used for reinforcing a suspended part of a carbon fiber composite missile launcher; the launcher comprises a launcher main body, wherein a pair of coaxial hanging holes are formed in the hanging part of the launcher main body; the launcher also comprises a pair of stiffening plates arranged on the inner side of the launcher main body, and the stiffening plates are provided with suspension shaft sleeves correspondingly connected with the suspension holes in a matched manner; the launcher main body is connected with the reinforcing plate through a plurality of rivets.
The technical scheme is further improved, and resin glue is filled between the launcher main body and the reinforcing plate.
Further improve technical scheme, the stiffening plate is the aluminum alloy material.
Owing to adopt above-mentioned technical scheme, compare the background art, the utility model discloses following beneficial effect has:
the suspension shaft sleeve of the utility model increases the contact area between the suspension part and the suspension shaft, and disperses the contact stress; the stiffening plate is connected with the launcher main part, has strengthened the intensity of guided missile launcher linkage.
The utility model discloses strengthen the intensity of guided missile launcher mounted part, improved the security of guided missile transmission, had that the implementation is strong, characteristics with low costs.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic cross-sectional view of fig. 1.
In the figure: 1. a launcher body; 2. a reinforcing plate; 2.1, hanging a shaft sleeve; 3. riveting; 4. and (3) resin glue.
Detailed Description
Preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only for explaining the technical principle of the present invention, and are not intended to limit the scope of the present invention.
A reinforcing structure of a missile launcher is shown in figures 1-2 and is used for reinforcing a suspended part of a missile launcher made of carbon fiber composite materials.
The reinforcing structure of the missile launcher comprises a launcher main body 1 made of carbon fiber composite materials, and a pair of coaxial suspension holes are formed in the suspension part of the launcher main body 1; the launcher is characterized by further comprising a pair of reinforcing plates 2 arranged on the inner side of the launcher body 1, wherein the reinforcing plates 2 are provided with hanging shaft sleeves 2.1 correspondingly connected with the hanging holes in a matched mode. Each reinforcing plate 2 is connected with the launcher body 1 by four rivets 3. The rivet 3 is used for riveting because riveting is more reliable than screwing.
The suspension shaft sleeve 2.1 increases the contact area of the suspension part and the suspension shaft and disperses the contact stress; the reinforcing plate 2 is connected with the launcher body 1, and the strength of the hanging part of the missile launcher is enhanced.
In order to reduce vibration and enhance the connection strength, the technical scheme is further improved, and resin glue 4 is filled between the launcher body 1 and the reinforcing plate 2.
In order to reduce the weight, the technical scheme is further improved, and the reinforcing plate 2 is made of an aluminum alloy material.
The part of the utility model not detailed is prior art. Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (3)
1. A reinforcing structure of a missile launcher is used for reinforcing a suspended part of a carbon fiber composite missile launcher; the method is characterized in that: comprises a launcher body (1), wherein a pair of coaxial hanging holes are formed in the hanging part of the launcher body (1); the launcher is characterized by further comprising a pair of reinforcing plates (2) arranged on the inner side of the launcher body (1), wherein the reinforcing plates (2) are provided with hanging shaft sleeves (2.1) correspondingly connected with the hanging holes in a matched mode; the launcher body (1) is connected with the reinforcing plate (2) through a plurality of rivets (3).
2. The missile launcher reinforcing structure as claimed in claim 1, wherein: resin glue (4) is filled between the launcher body (1) and the reinforcing plate (2).
3. The missile launcher reinforcing structure as claimed in claim 1, wherein: the reinforcing plate (2) is made of aluminum alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020082715.7U CN211601729U (en) | 2020-01-15 | 2020-01-15 | Reinforcing structure of missile launcher |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020082715.7U CN211601729U (en) | 2020-01-15 | 2020-01-15 | Reinforcing structure of missile launcher |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211601729U true CN211601729U (en) | 2020-09-29 |
Family
ID=72577160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020082715.7U Active CN211601729U (en) | 2020-01-15 | 2020-01-15 | Reinforcing structure of missile launcher |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211601729U (en) |
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2020
- 2020-01-15 CN CN202020082715.7U patent/CN211601729U/en active Active
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