CN204438928U - A kind of civil rocket bullet monoblock type projectile tail - Google Patents
A kind of civil rocket bullet monoblock type projectile tail Download PDFInfo
- Publication number
- CN204438928U CN204438928U CN201420766275.1U CN201420766275U CN204438928U CN 204438928 U CN204438928 U CN 204438928U CN 201420766275 U CN201420766275 U CN 201420766275U CN 204438928 U CN204438928 U CN 204438928U
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- CN
- China
- Prior art keywords
- projectile tail
- connecting ring
- monoblock type
- back clevis
- processed
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Abstract
The utility model relates to a kind of civil rocket bullet monoblock type projectile tail, comprises front connecting ring, larynx lining, compression moulding body, back clevis, blanking cover, belongs to civil rocket bullet field.Monoblock type projectile tail of the present utility model by stabilising arrangement and jet pipe entirety compressing, reduce projectile tail design, processing complexity, improve projectile tail working (machining) efficiency and projectile tail uniformity; Before projectile tail, latter linked weak link adopts metal material, and spray larynx place adopts graphite material, and is met the demands by the bonding strength that the structural design of connecting hole and groove achieves compression moulding part and other materials, ensure that projectile tail effectively works.Monoblock type projectile tail of the present utility model has important application value.
Description
Technical field
The utility model relates to a kind of civil rocket bullet monoblock type projectile tail, belongs to civil rocket bullet field.
Background technology
Civil rocket bullet projectile tail mainly comprises stabilising arrangement and jet pipe, and stabilising arrangement provides lift, produces stabilizing moment and ensure rocket projectile stabilized flight for rocket projectile, and jet pipe and powder charge combustion chamber form rocket engine, for rocket projectile provides predetermined thrust scheme.Traditional stabilising arrangement and jet pipe individually design, and are assembled together formation projectile tail by the mode such as screw thread or screw, are difficult to ensure higher assembling uniformity, and assembly technology is complicated, and economy is bad.
Utility model content
The purpose of this utility model will solve the stabilising arrangement of traditional projectile tail and jet pipe individually designs, and then it is complicated to be assembled into the assembly technology brought together, the problems such as economy is bad, and provide a kind of civil rocket bullet monoblock type projectile tail.
The purpose of this utility model is achieved through the following technical solutions:
A kind of rocket projectile monoblock type projectile tail of the present utility model, comprises front connecting ring, larynx lining, compression moulding body, back clevis, blanking cover;
Wherein, front connecting ring is cylindrical metal part, and the front end outer wall of front connecting ring is processed with the external screw thread be connected with combustion chamber, and the rear end sidewall of front connecting ring is processed with one group of circle distribution and the connecting hole of radial aperture;
Larynx serves as a contrast as graphite material processes, and the inner chamber of larynx lining is Lavalle shape, and the outer wall stage casing of larynx lining is processed with cannelure;
Back clevis is cylindrical metal part, and the rear end outer wall of back clevis is processed with the external screw thread be connected with blanking cover, and the front end side wall of back clevis is processed with one group of circle distribution and the connecting hole of radial aperture;
By compression moulding compounds by front connecting ring, larynx lining, back clevis is compression molded into inner chamber Lavalle shape, outside is distributed with fin projectile tail component; The connecting hole of front connecting ring rear end sidewall, the larynx lining cannelure of outer wall and the connecting hole of back clevis front end side wall are all imbedded in the compression moulding body after shaping; The front connecting ring of projectile tail component front end is threaded with combustion chamber, and the back clevis of projectile tail component rear end is threaded with blanking cover.
Beneficial effect
Monoblock type projectile tail of the present utility model by stabilising arrangement and jet pipe entirety compressing, reduce projectile tail design, processing complexity, improve projectile tail working (machining) efficiency and projectile tail uniformity; Before projectile tail, latter linked weak link adopts metal material, and spray larynx place adopts graphite material, and is met the demands by the bonding strength that the structural design of connecting hole and groove achieves compression moulding part and other materials, ensure that projectile tail effectively works.Monoblock type projectile tail of the present utility model has important application value.
Accompanying drawing explanation
Fig. 1 is the sectional view of a kind of rocket projectile monoblock type of the utility model projectile tail;
Wherein: connecting ring before 1-; 2-larynx serves as a contrast; 3-compression moulding body; 4-back clevis; 5-blanking cover;
Detailed description of the invention
Below in conjunction with drawings and Examples, content of the present utility model is described further
Embodiment
A kind of rocket projectile monoblock type projectile tail of the present utility model, structure as shown in Figure 1, comprises front connecting ring 1, larynx lining 2, compression moulding body 3, back clevis 4, blanking cover 5;
Wherein, front connecting ring 1 is cylindrical metal part, and the front end outer wall of front connecting ring 1 is processed with the external screw thread be connected with combustion chamber, and the rear end sidewall of front connecting ring 1 is processed with one group of circle distribution and the connecting hole of radial aperture;
Larynx lining 2 processes for graphite material, and the inner chamber of larynx lining 2 is Lavalle shape, and the outer wall stage casing that larynx serves as a contrast 2 is processed with cannelure;
Back clevis 4 is cylindrical metal part, and the rear end outer wall of back clevis 4 is processed with the external screw thread be connected with blanking cover 5, and the front end side wall of back clevis 4 is processed with one group of circle distribution and the connecting hole of radial aperture;
By compression moulding compounds by front connecting ring 1, larynx lining 2, back clevis 4 is compression molded into inner chamber Lavalle shape, outside is distributed with fin projectile tail component; The connecting hole of cannelure and back clevis 4 front end side wall that the connecting hole of front connecting ring 1 rear end sidewall, larynx serve as a contrast 2 outer walls is all imbedded in the compression moulding body 3 after shaping; The front connecting ring 1 of projectile tail component front end is threaded with combustion chamber, and the back clevis 4 of projectile tail component rear end is threaded with blanking cover 5.
Claims (1)
1. a rocket projectile monoblock type projectile tail, is characterized in that: comprise front connecting ring, larynx lining, compression moulding body, back clevis, blanking cover;
Wherein, front connecting ring is cylindrical metal part, and the front end outer wall of front connecting ring is processed with the external screw thread be connected with combustion chamber, and the rear end sidewall of front connecting ring is processed with one group of circle distribution and the connecting hole of radial aperture;
Larynx serves as a contrast as graphite material processes, and the inner chamber of larynx lining is Lavalle shape, and the outer wall stage casing of larynx lining is processed with cannelure;
Back clevis is cylindrical metal part, and the rear end outer wall of back clevis is processed with the external screw thread be connected with blanking cover, and the front end side wall of back clevis is processed with one group of circle distribution and the connecting hole of radial aperture;
By compression moulding compounds by front connecting ring, larynx lining, back clevis is compression molded into inner chamber Lavalle shape, outside is distributed with fin projectile tail component; The connecting hole of front connecting ring rear end sidewall, the larynx lining cannelure of outer wall and the connecting hole of back clevis front end side wall are all imbedded in the compression moulding body after shaping; The front connecting ring of projectile tail component front end is threaded with combustion chamber, and the back clevis of projectile tail component rear end is threaded with blanking cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420766275.1U CN204438928U (en) | 2014-12-09 | 2014-12-09 | A kind of civil rocket bullet monoblock type projectile tail |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420766275.1U CN204438928U (en) | 2014-12-09 | 2014-12-09 | A kind of civil rocket bullet monoblock type projectile tail |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204438928U true CN204438928U (en) | 2015-07-01 |
Family
ID=53606781
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420766275.1U Expired - Fee Related CN204438928U (en) | 2014-12-09 | 2014-12-09 | A kind of civil rocket bullet monoblock type projectile tail |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204438928U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108194231A (en) * | 2017-12-17 | 2018-06-22 | 内蒙动力机械研究所 | A kind of small-scale solid rocket motor jet pipe blanking cover |
-
2014
- 2014-12-09 CN CN201420766275.1U patent/CN204438928U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108194231A (en) * | 2017-12-17 | 2018-06-22 | 内蒙动力机械研究所 | A kind of small-scale solid rocket motor jet pipe blanking cover |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150701 Termination date: 20191209 |