CN104406467B - A kind of guided missile and cable radome fairing thereof and enging cabin section body - Google Patents
A kind of guided missile and cable radome fairing thereof and enging cabin section body Download PDFInfo
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- CN104406467B CN104406467B CN201410671588.3A CN201410671588A CN104406467B CN 104406467 B CN104406467 B CN 104406467B CN 201410671588 A CN201410671588 A CN 201410671588A CN 104406467 B CN104406467 B CN 104406467B
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- section body
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- enging cabin
- radome fairing
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Abstract
The present invention relates to a kind of guided missile and cable radome fairing thereof and enging cabin section body, enging cabin section body comprises the enging cabin section body axially extended along the longitudinal direction, the periphery of enging cabin section body is provided with notch and slides along the longitudinal direction the left hanging groove loaded towards the left auricle on the confession respective cable radome fairing on the right side, the periphery of enging cabin section body is also provided with notch and slides along the longitudinal direction the right hanging groove loaded towards the auris dextra sheet on the confession described cable radome fairing on a left side, left, right hanging groove all has the upper cell wall for radially being deviate from by enging cabin section body to prevent cable radome fairing with the spacing cooperation of corresponding auricle, enging cabin section body is also provided with and spacingly with described cable radome fairing coordinates to limit the movable axial limit structure of cable radome fairing opposite engine cabin section body.The invention solves the problem causing cable installing space deficiency in prior art because stator installing cables radome fairing need be arranged.
Description
Technical field
The present invention relates to a kind of guided missile and cable radome fairing thereof and enging cabin section body.
Background technology
Existing air-to-air missile comprises guidance fuze cabin section body, enging cabin section body and the tiller room section body that cable radome fairing and tandem are arranged, between tiller room section body with guidance fuze cabin section body, non-structure is connected, and needs the connection realized by cable electrically between tiller room section body and guidance fuze cabin section body.In order to realize the installation of radome fairing, enging cabin section body is arranged at intervals with multiple stator along the longitudinal direction, stator is provided with screwed hole, cable radome fairing is fixed on stator by screw, cable for connecting tiller room section body and guidance fuze section body is layed between stator and cable radome fairing, and cable is fixed sheet and cable radome fairing clamping position.Existing this guided missile Problems existing is: the clearance height that the aerodynamic configuration of whole guided missile determines between radome fairing and enging cabin section body only has 4mm.And the thickness of stator itself just has 2mm, cable by clamping position between stator and radome fairing, and certain thickness to be occupied due to stator, the clearance height can holding cable is caused to only have 2mm, the making of deficiency to cable of installing space is had higher requirement, cable must be made flat, and cable is coated can not do further water-proofing treatment, the great like this service life shortening cable.
Summary of the invention
The object of the present invention is to provide a kind of enging cabin section body, to solve the problem causing cable installing space deficiency in prior art because stator installing cables radome fairing need be arranged; The present invention also aims to provide a kind of with enging cabin section body with the use of cable radome fairing and use the guided missile of this enging cabin section body.
In order to solve the problem, in the present invention, the technical scheme of enging cabin section body is:
A kind of enging cabin section body of guided missile, comprise the enging cabin section body axially extended along the longitudinal direction, the periphery of enging cabin section body is provided with notch and slides along the longitudinal direction the left hanging groove loaded towards the left auricle on the confession respective cable radome fairing on the right side, the periphery of enging cabin section body is also provided with notch and slides along the longitudinal direction the right hanging groove loaded towards the auris dextra sheet on the confession described cable radome fairing on a left side, left, right hanging groove all has the upper cell wall for radially being deviate from by enging cabin section body to prevent cable radome fairing with the spacing cooperation of corresponding auricle, enging cabin section body is also provided with and spacingly with described cable radome fairing coordinates to limit the movable axial limit structure of cable radome fairing opposite engine cabin section body.
Enging cabin section body also comprises that left end is fixedly arranged on the outer peripheral face of described enging cabin section body, right-hand member towards the left lacing film of right overhanging, form described left hanging groove between the outer peripheral face of described left lacing film and described enging cabin section body; Enging cabin section body also comprises that right-hand member is fixedly arranged on the outer peripheral face of described enging cabin section body, left end towards the right lacing film of left overhanging, form described right hanging groove between the outer peripheral face of described right lacing film and described enging cabin section body.
Described axial limit structure comprises and is opened in screwed hole on described enging cabin section body and the stop screw of spinning in described screwed hole, and stop screw is threaded onto on cable radome fairing.
In the present invention, the technical scheme of cable radome fairing is:
A kind of cable radome fairing of guided missile, comprise the radome fairing body that length extends along the longitudinal direction, the left side of radome fairing body is installed with the left auricle in the left hanging groove loaded for sliding along the longitudinal direction on corresponding enging cabin section body, and the right side of radome fairing body is installed with the auris dextra sheet in the right hanging groove loaded for sliding along the longitudinal direction on described enging cabin section body.
In the present invention, the technical scheme of guided missile is:
A kind of guided missile, comprise enging cabin section body and cable radome fairing, enging cabin section body comprises the enging cabin section body axially extended along the longitudinal direction, cable radome fairing comprises the radome fairing body that length extends along the longitudinal direction, the left side of radome fairing is installed with left auricle, the right side of radome fairing is installed with auris dextra sheet, the periphery of enging cabin section body is provided with notch and slides along the longitudinal direction the left hanging groove loaded towards the described left auricle of confession on the right side, the periphery of enging cabin section body is also provided with notch and slides along the longitudinal direction the right hanging groove loaded towards the confession described auris dextra sheet on a left side, left, right hanging groove all has the upper cell wall radially deviate from by enging cabin section body to prevent cable radome fairing with the spacing cooperation of corresponding auricle, enging cabin section body is also provided with and spacingly with described cable radome fairing coordinates to limit the movable axial limit structure of cable radome fairing opposite engine cabin section body.
Enging cabin section body also comprises that left end is fixedly arranged on the outer peripheral face of described enging cabin section body, right-hand member towards the left lacing film of right overhanging, form described left hanging groove between the outer peripheral face of described left lacing film and described enging cabin section body; Enging cabin section body also comprises that right-hand member is fixedly arranged on the outer peripheral face of described enging cabin section body, left end towards the right lacing film of left overhanging, form described right hanging groove between the outer peripheral face of described right lacing film and described enging cabin section body.
Described axial limit structure comprises and is opened in screwed hole on described enging cabin section body and the stop screw of spinning in described screwed hole, and stop screw is threaded onto on cable radome fairing.
Beneficial effect of the present invention is: the present invention is by setting firmly left auricle and auris dextra sheet respectively in the left and right sides of cable radome fairing, after lay cable on enging cabin section body peripheral face, along the longitudinal direction by a left side, auris dextra sheet slides respectively and loads in corresponding hanging groove, then by axial limit structure, cable radome fairing axial limiting is just completed to the installation process of cable radome fairing, need by stator in the installation process of cable radome fairing, therefore stator need be set on enging cabin section body, such stator would not occupy the installing space of cable, reduce the making requirement to cable.
Accompanying drawing explanation
Fig. 1 is the structural representation of an embodiment of guided missile in the present invention;
Fig. 2 is the structural representation of cable radome fairing in Fig. 1.
Detailed description of the invention
The embodiment of guided missile is as shown in Figure 1 and 2: comprise guidance fuze cabin section body, enging cabin section body 5 and a tiller room section body that tandem is arranged, enging cabin section body is provided with cable radome fairing 6.Enging cabin section body comprises the enging cabin section body axially extended along the longitudinal direction, cable radome fairing comprises the radome fairing body that length extends along the longitudinal direction, the left side of radome fairing is installed with left auricle 7, the right side of radome fairing is installed with auris dextra sheet 8, left auricle has multiple, the number of auris dextra sheet is identical with the number of left auricle, left, auris dextra sheet is arranged in pairs, the periphery of enging cabin section body is provided with the left hanging groove of notch towards the loading of sliding along the longitudinal direction for left auricle respectively on the right side, left hanging groove and left auricle one_to_one corresponding, the periphery of enging cabin section body is also provided with the right hanging groove of notch towards the loading of sliding along the longitudinal direction for auris dextra sheet on a left side, right hanging groove and auris dextra sheet one_to_one corresponding, left, right hanging groove all has the upper cell wall radially deviate from by enging cabin section body to prevent cable radome fairing with the spacing cooperation of corresponding auricle, enging cabin section body also comprises left end and is fixedly arranged on the outer peripheral face of enging cabin section body, right-hand member is towards the left lacing film 9 of right overhanging, left hanging groove is formed between the outer peripheral face of left lacing film and enging cabin section body, enging cabin section body also comprises that right-hand member is fixedly arranged on the outer peripheral face of enging cabin section body, left end towards the right lacing film 10 of left overhanging, form described right hanging groove between the outer peripheral face of right lacing film and enging cabin section body.Enging cabin section body is also provided with and spacingly with cable radome fairing coordinates to limit the movable axial limit structure of cable radome fairing opposite engine cabin body, axial limit structure comprises the screwed hole be opened on enging cabin section body, cable radome fairing is provided with the screw perforation 11 corresponding with screwed hole, in screwed hole and screw perforation, is coated with stop screw.
During actual use, connect the laying cable between guidance fuze cabin section body and tiller room section body on enging cabin section body after, along the longitudinal direction each auricle of cable radome fairing is pushed in corresponding hanging groove respectively, auricle is combined closely with the cell wall of corresponding hanging groove, can also judge whether cable radome fairing is in place according to hanging groove, after cable radome fairing is in place, movable spacing by what install stop screw to realize to cable radome fairing in screwed hole and screw perforation.The present invention is on the basis not changing missile aerodynamic profile, cancel stator, install for cable and leave sufficient space, cable is too thin without the need to what do, cable processing can conveniently technique be processed, can also wrap up cable with silicon rubber self-adhesive tape simultaneously, enhance the characteristic of drenching with rain of cable.In other embodiment of this guided missile: the number of left and right hanging groove and left and right auricle can be arranged as required, such as 1 ~ 3 left hanging groove, right hanging groove are only set, 1 ~ 3 left auricle, auris dextra sheet, certain left and right auricle also can not be arranged in pairs, such as the number of left and right auricle is inconsistent; Left hanging groove also can be can't help left lacing film and enging cabin section body peripheral face and be formed, such as left hanging groove is opened on left lacing film completely, and same right hanging groove also can be opened on right stator completely; Stop screw also can not be threaded onto on cable radome fairing, such as the forward and backward side that stop screw is positioned at cable radome fairing is carried out movable spacing to cable radome fairing; Certain axial limit structure can also be fixed on corresponding lacing film for the spacing cooperation of corresponding auricle to limit the positive stop of cable radome fairing movement forward, axial limit structure now also comprises the backstop that coordinate to limit cable radome fairing backwards movement spacing with cable radome fairing be arranged on rear side of cable radome fairing.
The embodiment of enging cabin section body is as shown in Figure 1 and 2: the concrete structure of enging cabin section body is identical with the enging cabin section body described in above-mentioned each guided missile embodiment, is not described in detail in this.
The embodiment of cable radome fairing is as shown in 1 ~ 2: the concrete structure of cable radome fairing is identical with the cable radome fairing described in above-mentioned each guided missile embodiment, is not described in detail in this.
Claims (7)
1. the enging cabin section body of a guided missile, comprise the enging cabin section body axially extended along the longitudinal direction, it is characterized in that: the periphery of enging cabin section body is provided with notch and slides along the longitudinal direction the left hanging groove loaded towards the left auricle on the confession respective cable radome fairing on the right side, the periphery of enging cabin section body is also provided with notch and slides along the longitudinal direction the right hanging groove loaded towards the auris dextra sheet on the confession described cable radome fairing on a left side, left, right hanging groove all has the upper cell wall for radially being deviate from by enging cabin section body to prevent cable radome fairing with the spacing cooperation of corresponding auricle, enging cabin section body is also provided with and spacingly with described cable radome fairing coordinates to limit the movable axial limit structure of cable radome fairing opposite engine cabin section body.
2. enging cabin section body according to claim 1, it is characterized in that: enging cabin section body also comprises that left end is fixedly arranged on the outer peripheral face of described enging cabin section body, right-hand member towards the left lacing film of right overhanging, form described left hanging groove between the outer peripheral face of described left lacing film and described enging cabin section body; Enging cabin section body also comprises that right-hand member is fixedly arranged on the outer peripheral face of described enging cabin section body, left end towards the right lacing film of left overhanging, form described right hanging groove between the outer peripheral face of described right lacing film and described enging cabin section body.
3. enging cabin section body according to claim 1 and 2, it is characterized in that: described axial limit structure comprises and is opened in screwed hole on described enging cabin section body and the stop screw of spinning in described screwed hole, and stop screw is threaded onto on cable radome fairing.
4. the cable radome fairing of a guided missile, comprise the radome fairing body that length extends along the longitudinal direction, it is characterized in that: the left side of radome fairing body is installed with the left auricle in the left hanging groove loaded for sliding along the longitudinal direction on corresponding enging cabin section body, the right side of radome fairing body is installed with the auris dextra sheet in the right hanging groove loaded for sliding along the longitudinal direction on described enging cabin section body.
5. a guided missile, comprise enging cabin section body and cable radome fairing, enging cabin section body comprises the enging cabin section body axially extended along the longitudinal direction, cable radome fairing comprises the radome fairing body that length extends along the longitudinal direction, it is characterized in that: the left side of radome fairing is installed with left auricle, the right side of radome fairing is installed with auris dextra sheet, the periphery of enging cabin section body is provided with notch and slides along the longitudinal direction the left hanging groove loaded towards the described left auricle of confession on the right side, the periphery of enging cabin section body is also provided with notch and slides along the longitudinal direction the right hanging groove loaded towards the confession described auris dextra sheet on a left side, left, right hanging groove all has the upper cell wall radially deviate from by enging cabin section body to prevent cable radome fairing with the spacing cooperation of corresponding auricle, enging cabin section body is also provided with and spacingly with described cable radome fairing coordinates to limit the movable axial limit structure of cable radome fairing opposite engine cabin section body.
6. guided missile according to claim 5, it is characterized in that: enging cabin section body also comprises that left end is fixedly arranged on the outer peripheral face of described enging cabin section body, right-hand member towards the left lacing film of right overhanging, form described left hanging groove between the outer peripheral face of described left lacing film and described enging cabin section body; Enging cabin section body also comprises that right-hand member is fixedly arranged on the outer peripheral face of described enging cabin section body, left end towards the right lacing film of left overhanging, form described right hanging groove between the outer peripheral face of described right lacing film and described enging cabin section body.
7. the guided missile according to claim 5 or 6, is characterized in that: described axial limit structure comprises and is opened in screwed hole on described enging cabin section body and the stop screw of spinning in described screwed hole, and stop screw is threaded onto on cable radome fairing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410671588.3A CN104406467B (en) | 2014-11-21 | 2014-11-21 | A kind of guided missile and cable radome fairing thereof and enging cabin section body |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410671588.3A CN104406467B (en) | 2014-11-21 | 2014-11-21 | A kind of guided missile and cable radome fairing thereof and enging cabin section body |
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| Publication Number | Publication Date |
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| CN104406467A CN104406467A (en) | 2015-03-11 |
| CN104406467B true CN104406467B (en) | 2016-01-06 |
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| CN201410671588.3A Active CN104406467B (en) | 2014-11-21 | 2014-11-21 | A kind of guided missile and cable radome fairing thereof and enging cabin section body |
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| CN107394698B (en) * | 2017-08-04 | 2019-01-11 | 北京航空航天大学 | Cable shade assembly and rocket |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03208000A (en) * | 1990-01-08 | 1991-09-11 | Mitsubishi Electric Corp | Guided missile |
| JPH07190700A (en) * | 1993-12-28 | 1995-07-28 | Mitsubishi Electric Corp | Target searching method for airframe |
| KR20130106211A (en) * | 2012-03-19 | 2013-09-27 | 국방과학연구소 | Core type cable duct and missiles having the same and method of maufacturing of the core type cable duct |
| CN104008260A (en) * | 2014-06-19 | 2014-08-27 | 哈尔滨工业大学 | Designing method of conformal fairing optimum face type and parameters |
| CN204373526U (en) * | 2014-11-21 | 2015-06-03 | 中国空空导弹研究院 | Guided missile and cable radome fairing thereof and enging cabin section body |
-
2014
- 2014-11-21 CN CN201410671588.3A patent/CN104406467B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03208000A (en) * | 1990-01-08 | 1991-09-11 | Mitsubishi Electric Corp | Guided missile |
| JPH07190700A (en) * | 1993-12-28 | 1995-07-28 | Mitsubishi Electric Corp | Target searching method for airframe |
| KR20130106211A (en) * | 2012-03-19 | 2013-09-27 | 국방과학연구소 | Core type cable duct and missiles having the same and method of maufacturing of the core type cable duct |
| CN104008260A (en) * | 2014-06-19 | 2014-08-27 | 哈尔滨工业大学 | Designing method of conformal fairing optimum face type and parameters |
| CN204373526U (en) * | 2014-11-21 | 2015-06-03 | 中国空空导弹研究院 | Guided missile and cable radome fairing thereof and enging cabin section body |
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| CN104406467A (en) | 2015-03-11 |
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