CN201927707U - Two-position transformation mechanism of missile antenna - Google Patents
Two-position transformation mechanism of missile antenna Download PDFInfo
- Publication number
- CN201927707U CN201927707U CN2010206817615U CN201020681761U CN201927707U CN 201927707 U CN201927707 U CN 201927707U CN 2010206817615 U CN2010206817615 U CN 2010206817615U CN 201020681761 U CN201020681761 U CN 201020681761U CN 201927707 U CN201927707 U CN 201927707U
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- Prior art keywords
- antenna
- auricle
- missile
- sleeve
- push rod
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- Expired - Lifetime
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- 230000009466 transformation Effects 0.000 title abstract 10
- 239000000843 powder Substances 0.000 claims description 15
- 230000005540 biological transmission Effects 0.000 claims description 9
- 230000006835 compression Effects 0.000 claims description 8
- 238000007906 compression Methods 0.000 claims description 8
- 210000005069 ears Anatomy 0.000 claims description 6
- 238000013016 damping Methods 0.000 claims description 4
- 239000002360 explosive Substances 0.000 abstract 1
- 238000006243 chemical reaction Methods 0.000 description 5
- 229920001971 elastomer Polymers 0.000 description 4
- 239000000806 elastomer Substances 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 238000013507 mapping Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 239000011295 pitch Substances 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Abstract
The utility model relates to a two-position transformation mechanism of a missile antenna, which adopts a link mechanism based on explosive actuators to drive the antenna to change an included angle for the requirement of a transformation angle between a narrow space of a wing tip pipeline of a missile wing and the antenna so as to achieve the purpose of two-position transformation of the antenna. In the transformation mechanism, the structure is simple, the two-position transformation angle of the antenna is reliable in positioning, the dynamic response state is stable in place before transformation and after the transformation, and the two-position transformation mechanism can be applied in technical requirements for the transformation angles of various missile antennas.
Description
Technical field
The utility model relates to a kind of antenna servo mechanism, particularly relates to a kind of missile antenna dibit mapping device.
Background technology
At present, domestic guided missile image/instruction antenna is general adopts fixedly connected form to be installed on the missile wing wing tip.This type of attachment makes image/instruction antenna and bomb body axis angle keep constant, can not satisfy image/instruction transmit-receive technology requirement when guided missile is flat to fly the attack of the state commentaries on classics angle of fall.Though can satisfy the requirement of guided missile two states if the image/instruction antenna of the default angle of two covers is installed, but the not enough problem of image when having the guided missile on-hook simultaneously/instruction antenna and ground safe distance, and aerodynamic drag that guided missile is flat when flying is bigger, therefore influence the scope technical indicator, need the antenna can controlled movable, translation-angle.
General movable antenna adopts the electrical servo device, and its volume is big and need big output power.Because missile wing wing tip pipeline space is narrow and small, the electrical servo device can not satisfy the requirement of conversion antenna angle, therefore needs little, the may command conversion aerial angle mechanism of a kind of size of design.
The utility model content
The utility model provides a kind of missile antenna dibit mapping device at problems of the prior art.The utility model adopts the link mechanism driven antenna based on firer's actuator to change angle at missile wing wing tip pipeline small space and the requirement of antenna translation-angle, reaches the purpose of two positions of antenna conversion.
In order to realize the purpose of this utility model, the technical solution adopted in the utility model is:
A kind of missile antenna dibit converting means, comprise actuating unit, transmission mechanism, retaining mechanism, described actuating unit is for being installed in missile wing wing tip 1 ducted firer's actuator 2, the sleeve 23 of described firer's actuator 2 is fixed in the pipeline of missile wing wing tip 1, be set with piston cylinder 24 in the sleeve 23, piston cylinder 24 inside are divided into three parts along cross section by powder column dividing plate 22 and piston 18, part near missile wing wing tip 1 is inflammable powder column 19, be air chamber 25 between powder column dividing plate 14 and the piston 18, air chamber 25 opposite sides are piston 18, be the sliding cavity of piston between the bottom of piston 18 and sleeve 23, inflammable powder column 19 is connected with the igniter 20 that is positioned at sleeve 23 outsides, fixedlys connected with an end of the push rod 14 of the transmission mechanism that stretches into sleeve 23 bottoms in the bottom of piston 18; Transmission mechanism comprises push rod 14, one end of the other end of push rod 14 and connecting rod 3 is hinged, auricle 4 is hinged on the other end of connecting rod 3 and the antenna, auricle 4 is positioned at same plane with the axis of antenna 5 on the antenna, missile wing wing tip 1 pipeline below is fixedly connected with wing tip fork ear 8, there is auricle 6 under the antenna below of described antenna 5, under the antenna on auricle 6 and the antenna auricle 4 be positioned at same plane, auricle 6 is hinged with wing tip fork ear 8 under the described antenna; Retaining mechanism comprises shear pin 16 and locking pin 15, and the bottom of described shear pin 16 is fixed in the sleeve of missile wing wing tip 1, and the pin head of shear pin 16 is inserted in the pit-holes of push rod 14 outer surfaces; Locking pin 15 is installed in the sleeve 23, compression spring 21 is installed in the sleeve 23, one end of compression spring 21 is installed in sleeve 23 inwalls, the other end holds out against the tail end of locking pin 15, the tight push rod 14 in the pin crown of locking pin 15, auricle 4 coaxial lines on push rod 14 and connecting rod 3 and the antenna have locking slot 17 on the push rod 14, locking slot 17 is between piston 18 and locking pin.
Connecting rod 3 has the forked link of hinges for two ends, and two fork ears are told at the two ends of connecting rod 3 respectively, and auricle 4 inserts two of each end respectively and pitches between ears on the push rod auricle 9 of push rod end and the antenna, and is hinged by removable pin.Connecting rod 3 also can be for shaft-like, and two ends are hinged by pin-and-hole.
Be lined with damping pad 7 between auricle 6 and the wing tip fork ear 8 under the antenna.
The beneficial effects of the utility model are:
This mechanism structure is simple, and antenna dibit translation-angle location is reliable, and before the conversion, the conversion back dynamic response that puts in place is in stable condition, can be applicable to various missile antennas and become the angle specification requirement.
Description of drawings
Fig. 1 is structural representation of the present utility model (antenna axis and an elastomer axis parastate).
Fig. 2 is structural representation of the present utility model (antenna axis and elastomer axis is in a certain angle).
Fig. 3 is the structural representation of firer's actuator.
Fig. 4 is along the cutaway view Amplified image of A-A among Fig. 3.
Among the figure, 1 is the missile wing wing tip, and 2 is firer's actuator, 3 is connecting rod, and 4 is auricle on the antenna, and 5 is antenna, 6 is auricle under the antenna, and 7 are the damping pad, and 8 are wing tip fork ear, 9 is the push rod auricle, and 10 is first hinge bolt, and 11 is second hinge bolt, 12 is the 3rd hinge bolt, and 13 is fixing threaded hole, and 14 is push rod, 15 is locking pin, and 16 is shear pin, and 17 is locking slot, 18 is piston, 19 is inflammable powder column, and 20 is igniter, and 21 are the compression spring, 22 is the powder column dividing plate, 23 is sleeve, and 24 is piston cylinder, and 25 is air chamber.
Embodiment
Below in conjunction with drawings and Examples the utility model is further specified:
Embodiment: referring to Fig. 1, Fig. 2, Fig. 3, Fig. 4.
A kind of missile antenna dibit converting means, comprise actuating unit, transmission mechanism, retaining mechanism, described actuating unit is for being installed in missile wing wing tip 1 ducted firer's actuator 2, the sleeve 23 of described firer's actuator 2 is fixed in the pipeline of missile wing wing tip 1, be set with piston cylinder 24 in the sleeve 23, piston cylinder 24 inside are divided into three parts along cross section by powder column dividing plate 22 and piston 18, part near missile wing wing tip 1 is inflammable powder column 19, be air chamber 25 between powder column dividing plate 14 and the piston 18, air chamber 25 opposite sides are piston 18, be the sliding cavity of piston between the bottom of piston 18 and sleeve 23, inflammable powder column 19 is connected with the igniter 20 that is positioned at sleeve 23 outsides, fixedlys connected with an end of the push rod 14 of the transmission mechanism that stretches into sleeve 23 bottoms in the bottom of piston 18; Transmission mechanism comprises push rod 14, one end of the other end of push rod 14 and connecting rod 3 is hinged, auricle 4 is hinged on the other end of connecting rod 3 and the antenna, auricle 4 is positioned at same plane with the axis of antenna 5 on the antenna, missile wing wing tip 1 pipeline below is fixedly connected with wing tip fork ear 8, there is auricle 6 under the antenna below of described antenna 5, under the antenna on auricle 6 and the antenna auricle 4 be positioned at same plane, auricle 6 is hinged with wing tip fork ear 8 under the described antenna; Retaining mechanism comprises shear pin 16 and locking pin 15, and the bottom of described shear pin 16 is fixed in the sleeve of missile wing wing tip 1, and the pin head of shear pin 16 is inserted in the pit-holes of push rod 14 outer surfaces; Locking pin 15 is installed in the sleeve 23, compression spring 21 is installed in the sleeve 23, one end of compression spring 21 is installed in sleeve 23 inwalls, the other end holds out against the tail end of locking pin 15, the tight push rod 14 in the pin crown of locking pin 15, auricle 4 coaxial lines on push rod 14 and connecting rod 3 and the antenna have locking slot 17 on the push rod 14, locking slot 17 is between piston 18 and locking pin.
Connecting rod 3 has the forked link of hinges for two ends, and two fork ears are told at the two ends of connecting rod 3 respectively, and auricle 4 inserts two of each end respectively and pitches between ears on the push rod auricle 9 of push rod end and the antenna, and is hinged by removable pin.Connecting rod 3 also can be for shaft-like, and two ends are hinged by pin-and-hole.
Be lined with damping pad 7 between auricle 6 and the wing tip fork ear 8 under the antenna.
Principle of the present utility model is as follows:
At first auricle 4 on the push rod auricle 9 of the inside of firer's actuator 2 and the antenna is connected by connecting rod 3, its connected mode is for adopting the 3rd hinge bolt 12, first hinge bolt, 10 hinge bolts, and rolling bearing is closed in the assembling of hinge bolt outer cover; Then firer's actuator 2 and connecting rod 3 are packed in the missile wing wing tip 1, and adopt second hinge bolt 11 to cooperate the mode of rolling bearings to be connected auricle under the antenna 6 and wing tip fork ear 8; The sleeve of last firer's actuator is fixed on the missile wing wing tip 1 by fixing threaded hole 13.
Guided missile is in transportation, storage, carry, flight course, auricle 4 coaxial lines on push rod 14 and connecting rod 3 and the antenna, the shear pin 16 locking push rods 14 of firer's actuator 2 inside make antenna 5 be in horizontal direction, this moment, the axis and the elastomer axis of antenna 5 were in parastate, the guided missile horizontal space is less relatively, solves the problem of guided missile image/instruction antenna and ground safe distance deficiency in hooks on process; Aerodynamic drag when reducing missile flight simultaneously improves the scope index.
When guided missile flies to change the angle of fall when attacking by flat, instruction is sent in the missile-borne task engine, and electrical system provides initial firing current for the igniter 20 of firer's actuator 2, and the igniter 20 inflammable powder column 19 that detonates produces gases at high pressure and passes to piston 18 by air chamber 25; When gas pressure was excessive, shear pin 16 was cut off, the entire mechanism release.Gases at high pressure promote push rod 14 motions, and push rod 14 promotes connecting rod 3 motions, and connecting rod 3 orders about antenna 5 around 11 rotations of second hinge bolt; When antenna 5 rotate in place, the locking pin 15 of firer's actuator 2 inside falls into locking slot 17 in the effect of compression spring 21 and pins push rods 14, makes entire mechanism be in locking state.This moment antenna 5 axis and elastomer axis state in a certain angle, aerial signal is unimpeded when guaranteeing image/instruction angle of fall attack, makes the guided missile can the precision strike predeterminated target.
The utility model is not limited to above execution mode, as long as structure is identical with principle and the utility model, all drops within the protection range of the present utility model.
Claims (3)
1. missile antenna dibit converting means, comprise actuating unit, transmission mechanism, retaining mechanism, it is characterized in that: described actuating unit is for being installed in the ducted firer's actuator of missile wing wing tip (1) (2), the sleeve (23) of described firer's actuator (2) is fixed in missile wing wing tip (1) pipeline, be set with piston cylinder (24) in the described sleeve (23), piston cylinder (24) is inner to be divided into three parts along cross section by powder column dividing plate (22) and piston (18), part near missile wing wing tip (1) is inflammable powder column (19), be air chamber (25) between powder column dividing plate (14) and the piston (18), air chamber (25) opposite side is piston (18), be the sliding cavity of piston between the bottom of piston (18) and sleeve (23), inflammable powder column (19) igniter (20) outside with being positioned at sleeve (23) is connected, and fixedlys connected with an end of the push rod (14) of the transmission mechanism that stretches into sleeve (23) bottom in the bottom of piston (18); Described transmission mechanism comprises push rod (14), one end of the other end of push rod (14) and connecting rod (3) is hinged, auricle (4) is hinged on the other end of connecting rod (3) and the antenna, auricle on the antenna (4) is positioned at same plane with the axis of antenna (5), missile wing wing tip (1) pipeline below is fixedly connected with wing tip fork ear (8), there is auricle under the antenna (6) below of described antenna (5), auricle (4) is positioned at same plane on auricle under the antenna (6) and the antenna, and auricle under the described antenna (6) is hinged with wing tip fork ear (8); Described retaining mechanism comprises shear pin (16) and locking pin (15), and the bottom of described shear pin (16) is fixed in the sleeve of missile wing wing tip (1), and the pin head of shear pin (16) is inserted in the pit-holes of push rod (14) outer surface; Described locking pin (15) is installed in the sleeve (23), compression spring (21) is installed in the sleeve (23), one end of compression spring (21) is installed in sleeve (23) inwall, the other end holds out against the tail end of locking pin (15), the tight push rod in the pin crown (14) of locking pin (15), have locking slot (17) on the push rod (14), auricle (4) coaxial line on push rod (14) and connecting rod (3) and the antenna, locking slot (17) is positioned between piston (18) and the locking pin.
2. missile antenna dibit converting means according to claim 1, it is characterized in that: described connecting rod (3) has the forked link of hinges for two ends, two fork ears are told at the two ends of connecting rod (3) respectively, auricle (4) inserts respectively between two fork ears of each end on the push rod auricle (9) of push rod end and the antenna, and is hinged by removable pin.
3. missile antenna dibit converting means according to claim 2 is characterized in that: be lined with damping pad (7) between auricle under the described antenna (6) and the wing tip fork ear (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206817615U CN201927707U (en) | 2010-12-27 | 2010-12-27 | Two-position transformation mechanism of missile antenna |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206817615U CN201927707U (en) | 2010-12-27 | 2010-12-27 | Two-position transformation mechanism of missile antenna |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201927707U true CN201927707U (en) | 2011-08-10 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010206817615U Expired - Lifetime CN201927707U (en) | 2010-12-27 | 2010-12-27 | Two-position transformation mechanism of missile antenna |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201927707U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103105102A (en) * | 2012-12-10 | 2013-05-15 | 江西洪都航空工业集团有限责任公司 | Buffering and driving system of missile folding mechanism |
-
2010
- 2010-12-27 CN CN2010206817615U patent/CN201927707U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103105102A (en) * | 2012-12-10 | 2013-05-15 | 江西洪都航空工业集团有限责任公司 | Buffering and driving system of missile folding mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: JIANGXI HONGDU TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: HONGDU AVIATION INDUSTRY GROUP CO., TD., JIANGXI PROV. Effective date: 20140814 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 330000 NANCHANG, JIANGXI PROVINCE TO: 330096 NANCHANG, JIANGXI PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20140814 Address after: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee after: Jiangxi Hongdu Technology Co., Ltd. Address before: 330000 Jiangxi city of Nanchang province Qingyunpu new bridge Patentee before: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. |
|
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000161 Denomination of utility model: Two-position transformation mechanism of missile antenna Granted publication date: 20110810 License type: Exclusive License Record date: 20140709 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| EC01 | Cancellation of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000161 Date of cancellation: 20141202 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20151228 Address after: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee after: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Address before: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee before: Jiangxi Hongdu Technology Co., Ltd. |
|
| CX01 | Expiry of patent term |
Granted publication date: 20110810 |
|
| CX01 | Expiry of patent term |