CN113899252A - Connecting device for missile wing and missile body and missile - Google Patents
Connecting device for missile wing and missile body and missile Download PDFInfo
- Publication number
- CN113899252A CN113899252A CN202111226605.9A CN202111226605A CN113899252A CN 113899252 A CN113899252 A CN 113899252A CN 202111226605 A CN202111226605 A CN 202111226605A CN 113899252 A CN113899252 A CN 113899252A
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- missile
- wing
- fixed block
- missile wing
- fixed
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- 230000005540 biological transmission Effects 0.000 claims abstract description 12
- 238000009434 installation Methods 0.000 claims abstract description 7
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 239000003365 glass fiber Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/04—Stabilising arrangements using fixed fins
- F42B10/06—Tail fins
Abstract
The invention provides a connecting device for missile wings and a missile body and a missile, belonging to the technical field of missile structure design, and comprising: a body; the missile wing main body is connected with the missile body main body; the main force transmission joint is used for main force transmission connection between the missile body and the missile wing body and comprises a convex block and a second installation groove, the second installation groove is formed in the outer surface of the missile body, and the convex block is arranged below the missile wing body in a protruding mode; the auxiliary joint is used for auxiliary connection between the missile body and the missile wing body and comprises a support lug and a fixed block, the fixed block is arranged on the missile wing body, and the support lug is fixedly arranged on the outer surface of the missile body; when the missile wing main part is fixed on the missile body main part, the fixed block is fixedly arranged with the support lug, and the fixed block is fixedly arranged in the second mounting groove. The invention meets the requirement of the connection rigidity between the missile wing and the missile body under the condition of the flying working condition of the missile, and ensures that the first-order modal frequency of the missile wing meets the design requirement.
Description
Technical Field
The invention relates to the technical field of missile structural design, in particular to a connecting device for missile wings and a missile body and a missile.
Background
For ease of manufacture and transportation, the wings and body are usually manufactured separately and are usually joined by a detachable joint. The connection joint must ensure reliable connection, and above all, reliable force transmission; the disassembly is convenient and rapid, and the assembly is convenient; the interchangeability and the manufacturability are good, the interchanging between the missile wings is ensured, and the manufacturability of manufacturing and processing is good. The connection joints are generally classified into a centralized force transmission type and a distributed force transmission type.
The specific structures used at present are tab type connections, multi-tenon type connections, plug-in type connections, etc. The rigidity of the lug connection is relatively weak, and the designed missile wing has low first-order modal frequency; the design of the multi-tenon type connecting structure is relatively complex, and the manufacturability is poor; the plug-in connection structure is simple, the manufacturability is good, the assembly and disassembly are convenient, the connection rigidity is good, but the bearing capacity is limited.
Found through prior art retrieval, chinese utility model patent publication number is CN214344074U, discloses a fire extinguishing bomb missile wing fixed knot constructs, and this structure includes: the bullet comprises a bullet body, a head cover arranged at the front end of the bullet body and a connecting layer arranged at the joint of the bullet body and the bullet wings; the connection layer includes: the glass fiber layer, the bonding layer arranged on the outer surface of the glass fiber layer and the curing layer arranged on the outer surface of the bonding layer are sequentially arranged; the glass fiber layer is arranged on the missile body and is positioned at the contact part of the missile body and the missile wing, and the solidified layer is connected with the missile wing; the body of bullet includes from the front end to the rear end in proper order: the bullet body first section, the bullet body second section and the bullet body third section; and all the sections of the bullet bodies are connected through carbon tubes. The patented technology suffers from the problems associated with it as described above.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a connecting device for a missile wing and a missile body and a missile.
According to the invention, the connecting device for the missile wing and the missile body comprises:
a body;
a projectile body connected to the projectile body;
the main force transmission joint is used for main force transmission connection between the missile body and the missile wing body and comprises a convex block and a second installation groove, the second installation groove is formed in the outer surface of the missile body, and the convex block is arranged below the missile wing body in a protruding mode;
the auxiliary joint comprises a support lug and a fixed block, the fixed block is arranged on the missile wing main body, and the support lug is fixedly arranged on the outer surface of the missile wing main body;
when the missile wing main body is fixed on the missile body main body, the fixed block is fixedly arranged with the support lug, and the fixed block is fixedly arranged in the second mounting groove.
In some embodiments, the fixing block and the protrusion are disposed on the same plane, and the support lug and the second mounting groove are disposed on the same plane.
In some embodiments, the support lug is provided with a first mounting groove and a pin shaft hole, the fixing block is provided with a second mounting hole, the fixing block is clamped in the first mounting groove, the second mounting hole corresponds to the pin shaft hole, and the second mounting hole is provided with a pin shaft element in the pin shaft hole in a penetrating manner.
In some embodiments, a cotter pin is disposed at an end of the pin member, and the pin member is fixedly disposed in the second mounting hole and the pin hole through the cotter pin.
In some embodiments, a third mounting hole is formed in the fixing block, a counter bore is formed in the projectile body, the counter bore penetrates through the projectile body and is communicated with the second mounting groove, and the counter bore corresponds to the third mounting hole.
In some embodiments, fastening screws are disposed in the countersunk holes and the third mounting holes, and the protruding block is fixed in the second mounting groove by sequentially passing through the countersunk holes and the third mounting holes through the fastening screws.
In some embodiments, the thickness of the fixing block is smaller than that of the missile wing main body, and the cross section of the support lug is the same as that of the fixing block.
In some embodiments, the cross section of the protrusion is configured in a rectangular structure, and the cross section of the second mounting groove is configured in the same shape as the cross section of the protrusion.
The invention also provides a missile which adopts the connecting device for the missile wing and the missile body.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the missile wing body, the missile body can be stably connected with the missile wing body by arranging the auxiliary connector and the main force transmission connector, the requirement on the connection rigidity between the missile wing and the missile body under the condition of a flight working condition of a missile is met, and the first-order modal frequency of the missile wing is ensured to meet the design requirement;
2. according to the invention, the support lug and the fixed block are arranged as auxiliary joints and are fixed through the pin shaft piece, the lug and the second mounting groove are arranged as main force transmission joints and are fixed through the fastening screw, so that the missile wing and the missile body can be quickly assembled and disassembled, the assembly efficiency is greatly improved, the structure is simple, the manufacturability is good, the manufacturing and processing cost is low, and the low-cost design requirement of weapon equipment is met.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of the construction of the device for joining a projectile wing to a projectile body according to the present invention;
FIG. 2 is a partial schematic view of the projectile of the present invention;
FIG. 3 is a schematic view of the configuration of the missile wing of the invention;
FIG. 4 is a schematic structural view of an auxiliary joint according to the present invention;
FIG. 5 is a schematic view of the main force transfer joint of the present invention;
reference numerals:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Fig. 1 is a schematic structural view of a connection device for a missile wing and a missile body, fig. 2 is a partial schematic structural view of the missile body, and fig. 3 is a schematic structural view of the missile wing, and the connection device comprises: a body 1;
and a missile wing body 2 connected with the missile body 1.
As shown in fig. 5, it is a schematic structural diagram of a main force transfer joint 4 for main force transfer connection between the missile body 1 and the missile wing body 2, where the main force transfer joint 4 includes a protrusion 11 and a second mounting groove 7, the second mounting groove 7 is opened on the outer surface of the missile body 1, and the protrusion 11 is protruded below the missile wing body 2.
As shown in fig. 4, which is a schematic structural diagram of an auxiliary joint, the auxiliary joint 3 is used for auxiliary connection between the missile body 1 and the missile wing body 2, the auxiliary joint 3 includes a support lug 5 and a fixed block 15, the fixed block 15 is disposed on the missile wing body 2, and the support lug 5 is fixedly disposed on the outer surface of the missile body 1.
In the present embodiment, the fixing block 15 is disposed on the same plane as the protrusion 11, and the support lug 5 is disposed on the same plane as the second mounting groove 7. When the missile wing main body 2 is fixed on the missile body main body 1, the fixing block 15 is fixedly arranged with the support lug 5, and the fixing block 15 is fixedly arranged in the second mounting groove 7.
In the present embodiment, the thickness of the fixing block 15 is smaller than that of the missile wing body 2, and the cross-sectional shape of the lug 5 is set to be the same as that of the fixing block 15. When the fixing block 15 is fixed in the first mounting groove 51, the pin shaft 12 fixes the fixing block 15 and the support lug 5 stably, and the portion of the missile wing main body 2 with the thickness exceeding that of the fixing block 15 further fixes the support lug 5 to prevent the support lug 5 from moving relative to the missile wing main body 2.
In this embodiment, the cross section of the bump 11 is formed in a rectangular structure to ensure a high bending resistance of the joint, and the cross section of the second mounting groove 7 is formed in the same shape as the cross section of the bump 11. When the projection 11 is fixed in the second mounting groove 7, the projection 11 prevents the movement of the missile wing body 2 relative to the missile body 1 after the fastening screw 14 is fixed.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (9)
1. A connection device for use between a missile wing and a missile body, comprising:
a projectile body (1);
a missile wing main body (2) connected with the missile body main body (1);
the main force transmission joint (4) is used for main force transmission connection between the missile body main body (1) and the missile wing main body (2), the main force transmission joint (4) comprises a convex block (11) and a second installation groove (7), the second installation groove (7) is formed in the outer surface of the missile body main body (1), and the convex block (11) is arranged below the missile wing main body (2) in a protruding mode;
the auxiliary joint (3) is used for auxiliary connection between the missile body (1) and the missile wing body (2), the auxiliary joint (3) comprises a support lug (5) and a fixed block (15), the fixed block (15) is arranged on the missile wing body (2), and the support lug (5) is fixedly arranged on the outer surface of the missile body (1);
when missile wing main part (2) is fixed on missile body main part (1), fixed block (15) with journal stirrup (5) are fixed to be set up, fixed block (15) are fixed to be set up in second mounting groove (7).
2. The device for connecting a missile wing and a missile body according to claim 1, wherein the fixed block (15) and the projection (11) are arranged on the same plane, and the support lug (5) and the second mounting groove (7) are arranged on the same plane.
3. The connecting device for connecting be used for between missile wing and projectile body of claim 1, characterized in that, first mounting groove (51) and round pin shaft hole (6) have been seted up on journal stirrup (5), be equipped with second mounting hole (9) on fixed block (15), fixed block (15) block sets up in first mounting groove (51), second mounting hole (9) correspond round pin shaft hole (6) set up, just wear to be equipped with round pin axle piece (12) in second mounting hole (9) with round pin shaft hole (6).
4. The device for connecting a missile wing and a missile body according to claim 3, wherein the end of the pin member (12) is provided with a split pin (13), and the pin member (12) is fixedly arranged in the second mounting hole (9) and the pin shaft hole (6) through the split pin (13).
5. The device for connecting a missile wing and a missile according to claim 1, wherein the fixed block (15) is provided with a third mounting hole (10), the missile body (1) is provided with a counter bore (8), the counter bore (8) penetrates through the missile body (1) and is communicated with the second mounting groove (7), and the counter bore (8) is arranged corresponding to the third mounting hole (10).
6. The device for connecting a missile wing and a missile body according to claim 6, wherein fastening screws (14) are arranged in the counter-sunk hole (8) and the third mounting hole (10), and the protruding block (11) is fixed in the second mounting groove (7) by sequentially penetrating through the counter-sunk hole (8) and the third mounting hole (10) through the fastening screws (14).
7. The device for connection between a missile wing and a missile according to claim 1, wherein the thickness of the fixed block (15) is less than that of the missile wing body (2), and the cross-sectional shape of the support lug (5) is set to be the same as the cross-sectional shape of the fixed block (15).
8. The device for connecting a missile wing and a missile body according to claim 1, wherein the cross section of the convex block (11) is in a rectangular structure, and the cross section of the second installation groove (7) is in the same shape as the cross section of the convex block (11).
9. A projectile incorporating a connection means for a projectile wing to a projectile body as claimed in any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111226605.9A CN113899252A (en) | 2021-10-21 | 2021-10-21 | Connecting device for missile wing and missile body and missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111226605.9A CN113899252A (en) | 2021-10-21 | 2021-10-21 | Connecting device for missile wing and missile body and missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113899252A true CN113899252A (en) | 2022-01-07 |
Family
ID=79193019
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111226605.9A Pending CN113899252A (en) | 2021-10-21 | 2021-10-21 | Connecting device for missile wing and missile body and missile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113899252A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0174082A1 (en) * | 1984-07-23 | 1986-03-12 | Judd Engineering Limited | Projectile stabilising fin unit |
| JPH06101997A (en) * | 1992-09-17 | 1994-04-12 | Nissan Motor Co Ltd | Stabilizing wing fixing structure for missile |
| CN103047908A (en) * | 2012-12-12 | 2013-04-17 | 江西洪都航空工业集团有限责任公司 | Fusion structure of missile wing connection lug channel and missile body |
| CN107990792A (en) * | 2017-12-28 | 2018-05-04 | 北京威标至远科技发展有限公司 | A kind of rotatable tail gear |
| CN109612347A (en) * | 2018-11-23 | 2019-04-12 | 江西洪都航空工业集团有限责任公司 | A kind of missile wing quick-disassembly structure |
| CN208897306U (en) * | 2018-09-29 | 2019-05-24 | 四川长虹电器股份有限公司 | Unmanned aerial vehicle body and wing fast assembling-disassembling connection structure |
| CN111366043A (en) * | 2020-03-23 | 2020-07-03 | 上海机电工程研究所 | Missile wing connecting structure suitable for releasing thermal stress |
| CN213414200U (en) * | 2020-11-13 | 2021-06-11 | 北京海利天梦科技有限公司 | Unmanned aerial vehicle ready-package wing |
-
2021
- 2021-10-21 CN CN202111226605.9A patent/CN113899252A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0174082A1 (en) * | 1984-07-23 | 1986-03-12 | Judd Engineering Limited | Projectile stabilising fin unit |
| JPH06101997A (en) * | 1992-09-17 | 1994-04-12 | Nissan Motor Co Ltd | Stabilizing wing fixing structure for missile |
| CN103047908A (en) * | 2012-12-12 | 2013-04-17 | 江西洪都航空工业集团有限责任公司 | Fusion structure of missile wing connection lug channel and missile body |
| CN107990792A (en) * | 2017-12-28 | 2018-05-04 | 北京威标至远科技发展有限公司 | A kind of rotatable tail gear |
| CN208897306U (en) * | 2018-09-29 | 2019-05-24 | 四川长虹电器股份有限公司 | Unmanned aerial vehicle body and wing fast assembling-disassembling connection structure |
| CN109612347A (en) * | 2018-11-23 | 2019-04-12 | 江西洪都航空工业集团有限责任公司 | A kind of missile wing quick-disassembly structure |
| CN111366043A (en) * | 2020-03-23 | 2020-07-03 | 上海机电工程研究所 | Missile wing connecting structure suitable for releasing thermal stress |
| CN213414200U (en) * | 2020-11-13 | 2021-06-11 | 北京海利天梦科技有限公司 | Unmanned aerial vehicle ready-package wing |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20220107 |