CN104034212B - A kind of rocket projectile connection separation mechanism - Google Patents
A kind of rocket projectile connection separation mechanism Download PDFInfo
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- CN104034212B CN104034212B CN201410229227.3A CN201410229227A CN104034212B CN 104034212 B CN104034212 B CN 104034212B CN 201410229227 A CN201410229227 A CN 201410229227A CN 104034212 B CN104034212 B CN 104034212B
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Abstract
The present invention relates to a kind of rocket projectile connection separation mechanism, belong to rocket projectile technical field.Connection separation mechanism of the present invention, comprises front connector, rear connector, screw, key; Be connected with the syndeton of rear connector by " screw thread adds key " at front connector, in the duties processes such as transport at ordinary times, carrying, axial attachment force is born by the thread segment between front connector and rear connector; The circumferential shearing force that body High Rotation Speed produces in transmit state is born by bond structure; When carrying out lock out operation, being separated medicine and only need destroying the connecting thread between front connector and rear connector and the fastening glue between screw and full circle screwed hole, can realize opening the cabin.Connection separation mechanism structure of the present invention is simple, easy to assembly, while the enough bonding strengths of guarantee, can ensure again the reliable separation of front and back connector, have important popularizing application prospect.
Description
Technical field
The present invention relates to a kind of rocket projectile connection separation mechanism, belong to rocket projectile technical field.
Background technology
When cabin, the front and back body of rocket projectile docks, the helicitic texture that conventional method adopts usually connects, this screw connection structure, for the relatively light rocket projectile of weight, both can meet bonding strength during rotary motion, can realize again being separated reliable separation between the two cabin bodies that need.But for the rocket projectile that cabin, front and back body weight is larger, learn through test, the axial shearing force that cabin, front and back body connecting portion is subject under accumulating and emission state is less, only can meet the demands by the shorter section of being threaded; And the circumferential shearing force of body High Rotation Speed generation is larger in transmit state, adopting the single screw connection structure of tradition just must increase bonding strength by the length extending the section of being threaded, disintegrating in advance when not reaching the predetermined area to avoid cabin, front and back body connecting portion; But the longer section of being threaded, opening the cabin to operate to body also been proposed higher requirement, is separated dose very few, cannot realizes effective separation; Separation dose is too much, can take more body space, and also can damage the miscellaneous part of body when being separated medicine effect, affects the normal work of rocket projectile.
Summary of the invention
The object of the invention is cabin body before and after the large weight in order to solve the traditional single helicitic texture connection of employing, there are the technological difficulties that cannot meet bonding strength simultaneously and effectively be separated, and a kind of " screw thread adds key " formula connection isolating construction is provided.
The object of the invention is to be achieved through the following technical solutions:
A kind of rocket projectile connection separation mechanism of the present invention, comprises front connector, rear connector, screw, key;
The rear end inwall of front connector inwardly has annular link slot, the leading portion of this annular link slot is processed with internal thread, the thread segment rear end of this annular link slot has the key connecting hole of an axial aperture, the forward end of this key connecting hole is processed as semi-circular hole, and the hole wall of this semi-circular hole is processed with internal thread, the end, rear end of this key connecting hole is not communicated with the rear end end face of front connector;
The front end outer wall of rear connector is processed with the annular link slot matched with front connector rear end inwall, this annular link slot leading portion is processed with the external screw thread matched with front connector annular link slot leading portion internal thread, and the thread segment rear end of this annular link slot has the key connecting hole of an axial aperture; This key connecting hole is consistent with the key connecting hole width on front connector;
The width of key is consistent with the width of key connecting hole on front connector and rear connector, on the height of key and front connector and rear connector, the degree of depth sum of key connecting hole matches, the upper rear end of key has the step trough matched with the key connecting hole degree of depth on front connector, the front end of key has the semi-circular hole matched with the key connecting hole degree of depth on front connector, the hole wall of this semi-circular hole is processed with internal thread, and the internal thread that this internal thread matches on the semi-circular hole hole wall of front connector key connecting hole front end;
The front end of rear connector insert before connector annular link slot in and be threaded, and the key connecting hole on front connector and the key connecting hole circumference on rear connector are aligned, key is inserted in two key connecting holes aligned, and promote key backward, make the occlusion part screens of key connecting hole rear end on the cascaded surface of key rear end and front connector, and the semi-circular threaded of key connecting hole front end forms full circle screwed hole on the semi-circular threaded of key front end and front connector, screw thread is connected in this full circle screwed hole, between screw and this full circle screwed hole, scribbles fastening glue.
Operation principle: in the duties processes such as transport at ordinary times, carrying, axial attachment force is born by the thread segment between front connector and rear connector; The circumferential shearing force that body High Rotation Speed produces in transmit state is born by bond structure; When carrying out lock out operation, being separated medicine and only need destroying the connecting thread between front connector and rear connector and the fastening glue between screw and full circle screwed hole, can realize opening the cabin.
Beneficial effect:
Connection separation mechanism structure of the present invention is simple, easy to assembly, the conventional thinking that length that conventional method can only extend connecting thread simply increases bonding strength has been evaded by the syndeton of " screw thread adds key ", before and after effective solution, connector is to bonding strength and the design contradiction be effectively separated, while the enough bonding strengths of guarantee, the reliable separation of front and back connector can be ensured again, there is important popularizing application prospect.
Accompanying drawing explanation
Fig. 1 is the connection diagram of connection separation mechanism of the present invention;
Fig. 2 is the generalized section of front connector in connection separation mechanism of the present invention;
Fig. 3 is the top view of Fig. 2;
Fig. 4 is the front view of key in connection separation mechanism of the present invention;
Fig. 5 is the top view of Fig. 4;
Wherein: connector before 1-; Connector after 2-; 3-screw; 4-key.
Detailed description of the invention
Below in conjunction with accompanying drawing, preferred example of the present invention is further described:
Embodiment
A kind of rocket projectile connection separation mechanism of the present invention, as shown in Figure 1, comprises front connector 1, rear connector 2, screw 3, key 4;
As shown in Figure 2,3, the rear end inwall of front connector 1 inwardly has annular link slot, the leading portion of this annular link slot is processed with internal thread, the thread segment rear end of this annular link slot has the key connecting hole of an axial aperture, the forward end of this key connecting hole is processed as semi-circular hole, and the hole wall of this semi-circular hole is processed with internal thread, the end, rear end of this key connecting hole is not communicated with the rear end end face of front connector 1;
The front end outer wall of rear connector 2 is processed with the annular link slot matched with front connector 1 rear end inwall, this annular link slot leading portion is processed with the external screw thread matched with front connector 1 annular link slot leading portion internal thread, and the thread segment rear end of this annular link slot has the key connecting hole of an axial aperture; This key connecting hole is consistent with the key connecting hole width on front connector 1;
As shown in Figure 4,5, the width of key 4 is consistent with the width of key connecting hole on front connector 1 and rear connector 2, on the height of key 4 and front connector 1 and rear connector 2, the degree of depth sum of key connecting hole matches, the upper rear end of key 4 has the step trough matched with the key connecting hole degree of depth on front connector 1, the front end of key 4 has the semi-circular hole matched with the key connecting hole degree of depth on front connector 1, the hole wall of this semi-circular hole is processed with internal thread, and the internal thread that this internal thread matches on the semi-circular hole hole wall of front connector 1 key connecting hole front end;
The front end of rear connector 2 insert before connector 1 annular link slot in and be threaded, and the key connecting hole on front connector 1 and the key connecting hole circumference on rear connector 2 are aligned, key 4 is inserted in two key connecting holes aligned, and promote key 4 backward, make the occlusion part screens of key connecting hole rear end on the cascaded surface of key 4 rear end and front connector 1, and the semi-circular threaded of key connecting hole front end forms full circle screwed hole on the semi-circular threaded of key 4 front end and front connector 1, screw 3 is threaded in this full circle screwed hole, fastening glue is scribbled between screw 3 and this full circle screwed hole.
Operation principle: in the duties processes such as transport at ordinary times, carrying, axial attachment force is born by the thread segment between front connector 1 and rear connector 2; The circumferential shearing force that body High Rotation Speed produces in transmit state is born by bond structure; When carrying out lock out operation, being separated medicine and only need destroying the connecting thread between front connector 1 and rear connector 2 and the fastening glue between screw 3 and full circle screwed hole, can realize opening the cabin.
Claims (1)
1. a rocket projectile connection separation mechanism, is characterized in that: comprise front connector, rear connector, screw, key;
The rear end inwall of front connector inwardly has annular link slot, the leading portion of this annular link slot is processed with internal thread, the thread segment rear end of this annular link slot has the key connecting hole of an axial aperture, the forward end of this key connecting hole is processed as semi-circular hole, and the hole wall of this semi-circular hole is processed with internal thread, the end, rear end of this key connecting hole is not communicated with the rear end end face of front connector;
The front end outer wall of rear connector is processed with the annular link slot matched with front connector rear end inwall, this annular link slot leading portion is processed with the external screw thread matched with front connector annular link slot leading portion internal thread, and the thread segment rear end of this annular link slot has the key connecting hole of an axial aperture; This key connecting hole is consistent with the key connecting hole width on front connector;
The width of key is consistent with the width of key connecting hole on front connector and rear connector, on the height of key and front connector and rear connector, the degree of depth sum of key connecting hole matches, the upper rear end of key has the step trough matched with the key connecting hole degree of depth on front connector, the front end of key has the semi-circular hole matched with the key connecting hole degree of depth on front connector, the hole wall of this semi-circular hole is processed with internal thread, and the internal thread that this internal thread matches on the semi-circular hole hole wall of front connector key connecting hole front end;
The front end of rear connector insert before connector annular link slot in and be threaded, and the key connecting hole on front connector and the key connecting hole circumference on rear connector are aligned, key is inserted in two key connecting holes aligned, and promote key backward, make the occlusion part screens of key connecting hole rear end on the cascaded surface of key rear end and front connector, and the semi-circular threaded of key connecting hole front end forms full circle screwed hole on the semi-circular threaded of key front end and front connector, screw thread is connected in this full circle screwed hole, between screw and this full circle screwed hole, scribbles fastening glue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410229227.3A CN104034212B (en) | 2014-05-28 | 2014-05-28 | A kind of rocket projectile connection separation mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410229227.3A CN104034212B (en) | 2014-05-28 | 2014-05-28 | A kind of rocket projectile connection separation mechanism |
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| CN104034212A CN104034212A (en) | 2014-09-10 |
| CN104034212B true CN104034212B (en) | 2015-12-09 |
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| CN201410229227.3A Active CN104034212B (en) | 2014-05-28 | 2014-05-28 | A kind of rocket projectile connection separation mechanism |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104406454B (en) * | 2014-12-10 | 2016-05-18 | 晋西工业集团有限责任公司 | The directed button automatic releasing device of a kind of bottom bar bolt formula |
| CN105547055B (en) * | 2016-01-28 | 2017-05-03 | 晋西工业集团有限责任公司 | Two-stage separating mechanism for civil rocket |
| CN110044595B (en) * | 2019-05-05 | 2020-04-07 | 大连理工大学 | Aerospace line type separation ring structure strength measurement method based on electrical measurement technology |
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| US3253842A (en) * | 1963-12-10 | 1966-05-31 | Thiokol Chemical Corp | Shear key joint |
| US5131610A (en) * | 1990-07-11 | 1992-07-21 | Aerospatiale Societe Nationale Industrielle | Front end structure of a booster rocket mounted on the main body of a launcher |
| RU2239782C1 (en) * | 2003-03-19 | 2004-11-10 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Jet projectile |
| JP4026793B2 (en) * | 1998-06-18 | 2007-12-26 | ダイセル化学工業株式会社 | Rocket motor |
| CN102494565A (en) * | 2011-11-11 | 2012-06-13 | 中国航天科技集团公司第四研究院第四十一研究所 | Separation mechanism of oriented rocket nose body |
| CN103256866A (en) * | 2013-04-25 | 2013-08-21 | 蒋成吉 | Connecting plate of rocket connector |
| CN203848761U (en) * | 2014-05-28 | 2014-09-24 | 晋西工业集团有限责任公司 | Connection and separation mechanism for rocket projectile |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2002198B1 (en) * | 2006-03-30 | 2013-04-24 | Raytheon Company | Methods and apparatus for integrated locked thruster mechanism |
| KR101117100B1 (en) * | 2009-09-03 | 2012-02-22 | 국방과학연구소 | Separation device of ejector motor for portable missile |
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2014
- 2014-05-28 CN CN201410229227.3A patent/CN104034212B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3253842A (en) * | 1963-12-10 | 1966-05-31 | Thiokol Chemical Corp | Shear key joint |
| US5131610A (en) * | 1990-07-11 | 1992-07-21 | Aerospatiale Societe Nationale Industrielle | Front end structure of a booster rocket mounted on the main body of a launcher |
| JP4026793B2 (en) * | 1998-06-18 | 2007-12-26 | ダイセル化学工業株式会社 | Rocket motor |
| RU2239782C1 (en) * | 2003-03-19 | 2004-11-10 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Jet projectile |
| CN102494565A (en) * | 2011-11-11 | 2012-06-13 | 中国航天科技集团公司第四研究院第四十一研究所 | Separation mechanism of oriented rocket nose body |
| CN103256866A (en) * | 2013-04-25 | 2013-08-21 | 蒋成吉 | Connecting plate of rocket connector |
| CN203848761U (en) * | 2014-05-28 | 2014-09-24 | 晋西工业集团有限责任公司 | Connection and separation mechanism for rocket projectile |
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| CN104034212A (en) | 2014-09-10 |
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