CN104567561B - A kind of distinguish that is applicable to throws the special-shaped configuration missile cabin syndeton of covering - Google Patents
A kind of distinguish that is applicable to throws the special-shaped configuration missile cabin syndeton of covering Download PDFInfo
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- CN104567561B CN104567561B CN201310515564.4A CN201310515564A CN104567561B CN 104567561 B CN104567561 B CN 104567561B CN 201310515564 A CN201310515564 A CN 201310515564A CN 104567561 B CN104567561 B CN 104567561B
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- cabin
- metal shell
- adapter ring
- guiding
- body adapter
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Abstract
The present invention relates to section interconnection technique field, special-shaped aircraft cabin, specifically disclose a kind of distinguish that is applicable to and throw the special-shaped configuration missile cabin syndeton of covering.This syndeton comprises guiding cabin metal shell, warhead cabin metal shell and cabin body adapter ring, wherein, cabin body adapter ring is stepped cylindrical barrel structure, it is fixedly connected with guiding cabin metal shell by helicitic texture, and the left side barrel of cabin body adapter ring and guiding cabin metal shell is connected and fixed by check pin; Warhead cabin metal shell mate with guiding cabin metal shell end face, and warhead cabin metal shell inwall mates with barrel on the right side of the body adapter ring of cabin, and passes through connecting pin, realizes being fixedly connected with of warhead cabin metal shell and cabin body adapter ring.This syndeton solves that cabin section major thread connects cannot the inconsistent problem of locking, special-shaped configuration cabin body interface; Connect fast compared to petal type, this structure interface load performance is good, interface gapless, and manufacturing process easily realizes.
Description
Technical field
The invention belongs to section interconnection technique field, special-shaped aircraft cabin, be specifically related to a kind of distinguish that is applicable to and throw the special-shaped configuration missile cabin syndeton of covering.
Background technology
For meeting in guided missile emergent battle, the precision strike of little territory target is required and demand to the precision strike of multiple types target under different battlefield surroundings, the symmetrical special-shaped configuration coasting in certain face adopts the high accuracy combined guidance system of inertia+GPS+ infrared imaging, gps signal is utilized to revise used grouping error in glide section, enter after attacking section, arrive the infrared seeker start moment, proceed to Terminal Infrared Guidance mode.Target seeker, when predetermined altitude works, needs the thermal shield of distinguish jettisoning target seeker, exposes the optical dome of its front end.Target seeker cabin throwing cover after require with back segment cabin body Joint failure, existing cabin body connected mode meet throw cover require for major thread connection and petal type connect fast.Because guided missile is Special-Shaped Surface, cabin section major thread cannot ensure when connecting screw thread be screwed to position after two cabin body interfaces consistent, and when major thread connects, cabin body realizes connecting by rotating, and rotary course easily makes cabin inner cable strand together, and threaded pre-tightening power not easily applies, cannot be locking.And the quick connected mode of petal type belongs to socket join structure, abutment joint place will leave certain gap, and there is adverse influence in gap for the solar heat protection of housing and vibration characteristics, and radial fit dimensional requirement is higher, and technique not easily ensures, needs careful design.
Summary of the invention
The object of the present invention is to provide and be a kind ofly applicable to the special-shaped configuration missile cabin syndeton that distinguish throws cover, solve when special-shaped missile cabin connects that screw thread cannot be locking, the problem that interface is inconsistent, and overcome abutment joint place and have gap, the problem of manufacturability difference.
Technical scheme of the present invention is as follows: a kind of distinguish that is applicable to throws the special-shaped configuration missile cabin syndeton of covering, this syndeton comprises guiding cabin metal shell, warhead cabin metal shell and cabin body adapter ring, wherein, cabin body adapter ring is stepped cylindrical barrel structure, it is fixedly connected with guiding cabin metal shell by helicitic texture, and the left side barrel of cabin body adapter ring and guiding cabin metal shell is connected and fixed by check pin; Warhead cabin metal shell mate with guiding cabin metal shell end face, and warhead cabin metal shell inwall mates with barrel on the right side of the body adapter ring of cabin, and passes through connecting pin, realizes being fixedly connected with of warhead cabin metal shell and cabin body adapter ring.
Described guiding cabin metal shell right side edge inwall has helicitic texture, and is bulge-structure on the left of the metal shell helicitic texture end of guiding cabin, form the thrust surface of screw tip, and on this bulge-structure, have two anti-porosities, described cabin body adapter ring is ladder barrel structure, on the left of it, barrel diameter is less, and match with guiding cabin metal shell bulge-structure, and barrel has two screwed holes matched with the anti-porosity of guiding cabin metal shell on the left of this, on the right side of the body adapter ring of cabin, barrel diameter is larger, it has one section of screw thread mated with guiding cabin metal shell helicitic texture, cabin body adapter ring entirety screws in the metal shell of guiding cabin, and located by the thrust surface of screw tip in the metal shell of guiding cabin, and screwed hole on the left of the body adapter ring of cabin on barrel is corresponding with the anti-porosity on the metal shell of guiding cabin, check pin with the cylindrical bar shape structure of one section of helicitic texture screws in the screwed hole on the body adapter ring of cabin, and check pin upper end enters in the anti-porosity of guiding cabin metal shell, prevent guiding cabin metal shell and cabin body adapter ring major thread from loosening.
On the right side of described cabin body adapter ring, barrel also has screwed hole, warhead cabin metal shell has through hole, it is corresponding with the screwed hole on barrel on the right side of the body adapter ring of cabin, the connecting pin that lower end is threaded structure, from the screwed hole of barrel on the right side of the through hole warhead cabin metal shell screws in cabin body adapter ring, realizes the connection of warhead cabin metal shell and cabin body adapter ring.
Described guiding cabin metal shell outer wall is coated with guiding cabin heat shield.
Described warhead cabin metal shell outer wall is coated with warhead cabin heat shield.
Described warhead cabin heat shield has the through hole consistent with warhead cabin metal shell, and in the through hole of warhead cabin heat shield, be provided with solar heat protection plug screw.
Described cabin body adapter ring material is aluminium alloy, or titanium alloy or steel.
Remarkable result of the present invention is: be of the present inventionly a kind ofly applicable to the special-shaped configuration missile cabin syndeton that distinguish throws cover, utilize adapter ring and check pin to solve cabin section major thread connects cannot the inconsistent problem of locking, special-shaped configuration cabin body interface; Connect fast compared to petal type, this structure interface load performance is good, interface gapless, and manufacturing process easily realizes.
Accompanying drawing explanation
Fig. 1 is that a kind of distinguish that is applicable to of the present invention throws the special-shaped configuration missile cabin syndeton schematic diagram covered;
In figure: 1, guide cabin metal shell; 2, cabin heat shield is guided; 3, solar heat protection plug screw; 4, warhead cabin heat shield; 5, warhead cabin metal shell; 6, connecting pin; 7, cabin body adapter ring; 8, check pin.
Detailed description of the invention
Below in conjunction with drawings and the specific embodiments, the present invention is described in further detail.
As shown in Figure 1, a kind of distinguish that is applicable to throws the special-shaped configuration missile cabin syndeton of covering, comprise guiding cabin metal shell 1, warhead cabin metal shell 5 and cabin body adapter ring 7, wherein, the outside guiding cabin metal shell 1 right side edge inwall covering guiding cabin heat shield 2 has helicitic texture, and be bulge-structure on the left of the metal shell 1 helicitic texture end of guiding cabin, form the thrust surface of screw tip, and on this bulge-structure, have two anti-porosities, cabin body adapter ring 7 is ladder barrel structure, on the left of it, barrel diameter is less, and match with guiding cabin metal shell 1 bulge-structure, and barrel has two screwed holes matched with the anti-porosity of guiding cabin metal shell 1 on the left of this, on the right side of cabin body adapter ring 7, barrel diameter is larger, it has one section of screw thread mated with guiding cabin metal shell 1 helicitic texture, and also have screwed hole on the right side of barrel thread segment on the right side of cabin body adapter ring 7, cabin body adapter ring 7 entirety screws in guiding cabin metal shell 1, and located by the thrust surface of screw tip in guiding cabin metal shell 1, and screwed hole on the left of cabin body adapter ring 7 on barrel is corresponding with the anti-porosity on guiding cabin metal shell 1, check pin 8 with the cylindrical bar shape structure of one section of helicitic texture screws in the screwed hole on cabin body adapter ring 7, and check pin 8 upper end enters in the anti-porosity of guiding cabin metal shell 1, prevent guiding cabin metal shell 1 from loosening with cabin body adapter ring 7 major thread, outside warhead cabin metal shell 5 left end face covering warhead cabin heat shield 4 is alignd with guiding cabin metal shell 1 its right end face, and barrel external diameter matches on the right side of the inwall of warhead cabin metal shell 5 and cabin body adapter ring 7, warhead cabin heat shield 4 and warhead cabin metal shell 5 have through hole, make it corresponding with the screwed hole on barrel on the right side of cabin body adapter ring 7, the connecting pin 6 that lower end is threaded structure is from the screwed hole of barrel on the right side of the through hole warhead cabin metal shell 5 screws in cabin body adapter ring 7, realize the connection of warhead cabin metal shell 5 and cabin body adapter ring 7, and in the through hole of warhead cabin heat shield 4, solar heat protection plug screw 3 is installed, wherein, the material of solar heat protection plug screw 3 guides cabin heat shield 2 with outside covering, the material of warhead cabin heat shield 4 is consistent, cabin body adapter ring 7 material can be aluminium alloy, titanium alloy or steel.
Claims (7)
1. one kind is applicable to the special-shaped configuration missile cabin syndeton that distinguish throws cover, it is characterized in that: this syndeton comprises guiding cabin metal shell (1), warhead cabin metal shell (5) and cabin body adapter ring (7), wherein, cabin body adapter ring (7) is stepped cylindrical barrel structure, it is fixedly connected with guiding cabin metal shell (1) by helicitic texture, and the left side barrel in cabin body adapter ring (7) and guiding cabin metal shell (1) is connected and fixed by check pin (8); Warhead cabin metal shell (5) mates with guiding cabin metal shell (1) end face, and warhead cabin metal shell (5) inwall mates with right side, cabin body adapter ring (7) barrel, and by connecting pin (6), realize being fixedly connected with of warhead cabin metal shell (5) and cabin body adapter ring (7).
2. a kind of distinguish that is applicable to according to claim 1 throws the special-shaped configuration missile cabin syndeton of covering, it is characterized in that: described guiding cabin metal shell (1) right side edge inwall has helicitic texture, and be bulge-structure on the left of metal shell (1) the helicitic texture end of guiding cabin, form the thrust surface of screw tip, and on this bulge-structure, have two anti-porosities, described cabin body adapter ring (7) is ladder barrel structure, on the left of it, barrel diameter is less, and match with guiding cabin metal shell (1) bulge-structure, and barrel has two screwed holes matched with guiding cabin metal shell (1) anti-porosity on the left of this, right side, cabin body adapter ring (7) barrel diameter is larger, it has one section of screw thread mated with guiding cabin metal shell (1) helicitic texture, cabin body adapter ring (7) entirety screws in guiding cabin metal shell (1), and located by the thrust surface of screw tip in guiding cabin metal shell (1), and screwed hole on the barrel of left side, cabin body adapter ring (7) is corresponding with the anti-porosity of guiding on cabin metal shell (1), check pin (8) with the cylindrical bar shape structure of one section of helicitic texture screws in the screwed hole on cabin body adapter ring (7), and check pin (8) upper end enters in the anti-porosity of guiding cabin metal shell (1), prevent guiding cabin metal shell (1) from loosening with cabin body adapter ring (7) major thread.
3. a kind of distinguish that is applicable to according to claim 1 and 2 throws the special-shaped configuration missile cabin syndeton of covering, it is characterized in that: described right side, cabin body adapter ring (7) barrel also has screwed hole, warhead cabin metal shell (5) has through hole, it is corresponding with the screwed hole on the barrel of right side, cabin body adapter ring (7), the connecting pin (6) that lower end is threaded structure screws in the screwed hole of right side, cabin body adapter ring (7) barrel from the through hole warhead cabin metal shell (5), realize the connection in warhead cabin metal shell (5) and cabin body adapter ring (7).
4. a kind of distinguish that is applicable to according to claim 1 throws the special-shaped configuration missile cabin syndeton of covering, and it is characterized in that: described guiding cabin metal shell (1) outer wall is coated with guiding cabin heat shield (2).
5. a kind of distinguish that is applicable to according to claim 3 throws the special-shaped configuration missile cabin syndeton of covering, and it is characterized in that: described warhead cabin metal shell (5) outer wall is coated with warhead cabin heat shield (4).
6. a kind of distinguish that is applicable to according to claim 5 throws the special-shaped configuration missile cabin syndeton of covering, it is characterized in that: described warhead cabin heat shield (4) has the through hole consistent with warhead cabin metal shell (5), and be provided with solar heat protection plug screw (3) in the through hole of warhead cabin heat shield (4).
7. be according to claim 1ly a kind ofly applicable to the special-shaped configuration missile cabin syndeton that distinguish throws cover, it is characterized in that: described cabin body adapter ring (7) material is aluminium alloy, or titanium alloy or steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310515564.4A CN104567561B (en) | 2013-10-28 | 2013-10-28 | A kind of distinguish that is applicable to throws the special-shaped configuration missile cabin syndeton of covering |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310515564.4A CN104567561B (en) | 2013-10-28 | 2013-10-28 | A kind of distinguish that is applicable to throws the special-shaped configuration missile cabin syndeton of covering |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104567561A CN104567561A (en) | 2015-04-29 |
| CN104567561B true CN104567561B (en) | 2015-12-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310515564.4A Expired - Fee Related CN104567561B (en) | 2013-10-28 | 2013-10-28 | A kind of distinguish that is applicable to throws the special-shaped configuration missile cabin syndeton of covering |
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| CN106555706A (en) * | 2016-11-04 | 2017-04-05 | 上海新力动力设备研究所 | A kind of missile propulsive plant is threadedly coupled stop anti-loose structure |
| CN108194669A (en) * | 2017-12-29 | 2018-06-22 | 宁波海天金属成型设备有限公司 | Reliable locking one-way isolation valve arrangement and supercharging cylinder structure |
| CN109596010B (en) * | 2018-11-23 | 2021-06-11 | 中国运载火箭技术研究院 | Dismantled and assembled multilobe formula cabin section butt joint heat protection structure |
| CN110631433B (en) * | 2019-08-20 | 2021-08-17 | 西安航天动力技术研究所 | Shear screw type hood separating mechanism |
| CN111380423B (en) * | 2020-03-23 | 2022-09-13 | 上海机电工程研究所 | Eccentric hoop structure and installation mode thereof |
| CN114046694A (en) * | 2021-11-03 | 2022-02-15 | 天津爱思达航天科技有限公司 | Composite material shell connecting frame reinforcing structure |
| CN114286559B (en) * | 2021-12-23 | 2023-07-11 | 航天科工微电子系统研究院有限公司 | Guide head hood mounting structure |
| CN115158709B (en) * | 2022-06-07 | 2022-12-27 | 精易兴航(北京)科技创新有限公司 | Carrier rocket with pneumatic separation and power recovery system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6497530B1 (en) * | 2000-01-07 | 2002-12-24 | Raytheon Company | Universal flange joint for attaching |
| CN202320771U (en) * | 2011-09-26 | 2012-07-11 | 江西洪都航空工业集团有限责任公司 | Connecting structure with inner fixture block for cabin sections |
| CN102619860A (en) * | 2012-03-30 | 2012-08-01 | 北京机电工程研究所 | Self locking fastening structure and sealing structure |
| CN102765471A (en) * | 2012-07-02 | 2012-11-07 | 江西洪都航空工业集团有限责任公司 | Wing surface root rib and capsule section longitudinal beam integrated structure of guided missile |
| CN103075411A (en) * | 2012-12-10 | 2013-05-01 | 江西洪都航空工业集团有限责任公司 | Anti-loosening structure of threaded connection of missile covering cap and missile body |
| CN202964525U (en) * | 2012-11-27 | 2013-06-05 | 凯迈（洛阳）气源有限公司 | Missile bay section connection auxiliary tool |
| CN203224176U (en) * | 2012-11-23 | 2013-10-02 | 北京机电工程研究所 | Fixing structure for the jointing and connecting of three layers of cabin segments |
-
2013
- 2013-10-28 CN CN201310515564.4A patent/CN104567561B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6497530B1 (en) * | 2000-01-07 | 2002-12-24 | Raytheon Company | Universal flange joint for attaching |
| CN202320771U (en) * | 2011-09-26 | 2012-07-11 | 江西洪都航空工业集团有限责任公司 | Connecting structure with inner fixture block for cabin sections |
| CN102619860A (en) * | 2012-03-30 | 2012-08-01 | 北京机电工程研究所 | Self locking fastening structure and sealing structure |
| CN102765471A (en) * | 2012-07-02 | 2012-11-07 | 江西洪都航空工业集团有限责任公司 | Wing surface root rib and capsule section longitudinal beam integrated structure of guided missile |
| CN203224176U (en) * | 2012-11-23 | 2013-10-02 | 北京机电工程研究所 | Fixing structure for the jointing and connecting of three layers of cabin segments |
| CN202964525U (en) * | 2012-11-27 | 2013-06-05 | 凯迈（洛阳）气源有限公司 | Missile bay section connection auxiliary tool |
| CN103075411A (en) * | 2012-12-10 | 2013-05-01 | 江西洪都航空工业集团有限责任公司 | Anti-loosening structure of threaded connection of missile covering cap and missile body |
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| CN104567561A (en) | 2015-04-29 |
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