CN102121512B - Crossing and folding wing transmission device - Google Patents
Crossing and folding wing transmission device Download PDFInfo
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- CN102121512B CN102121512B CN 201010602705 CN201010602705A CN102121512B CN 102121512 B CN102121512 B CN 102121512B CN 201010602705 CN201010602705 CN 201010602705 CN 201010602705 A CN201010602705 A CN 201010602705A CN 102121512 B CN102121512 B CN 102121512B
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Abstract
The invention relates to a crossing and folding wing transmission device which comprises a gear box body, missile wing main joints with teeth, a left missile wing, a right missile wing, half gears, a transmission gear, a driving gear set and a driving connecting rod, wherein two sides of the gear box body are provided with the missile wing main joints with teeth; sockets of the missile wing main joints with teeth are respectively connected with the left missile wing and the right missile wing; the lift missile wing is meshed with the transmission gear through the half gears of the missile wing main joints with teeth; the transmission gear is further meshed with a lower gear of the driving gear set; the right missile wing is meshed with an upper gear of the driving gear set through the half gears of the missile wing main joints with teeth; and power is transmitted to the driving connecting rod through a joint by a power source, further the driving gear set is driven, thus the synchronous rotation of the left missile wing and the right missile wing is realized. The crossing and folding wing transmission device has the advantages that the gear transmission device is modularized, the transmission is steady, and the impact force to an elastomer is tiny; the transmission gap and the clearance are less, during the process of the expanding of the missile wing and the changing of a sweep back angle, the synchronism is good, and the device has no locking action and no time delay.
Description
Technical field
The present invention relates to the folding wing device, particularly relate to cross folding wing transmission device.
Background technique
Day by day complicated along with war environment, traditional guided missile is almost constant because of geometrical shape, exposes many defectives, shows as: unit space projectile storage and transportation amount is few, changes the target of attack ability, be difficult to attack terminal implement certain motor-driven.And present advanced long-range missile mostly is in-line, high aspect ratio missile wing layout, requires the guided missile missile wing can be controlled at initial segment, cruise section, target search section and terminal guidance section, presents different aerodynamic configuration structures.
To the few problem of unit space projectile storage and transportation amount, all adopted missile wing folding and expanding technology both at home and abroad, but its unfolded mechanism particular content is unexposed, and its existence folds and launches fully two positions fully.And the linkage mechanism of domestic general employing because it need attach independent locking mechanism, without automatic unlocking function, can not be converted into the sweepback angle continuous variable; Have and use simple oscillating guidebar mechanism, every missile wing needs individual drive, and independent mechanism is set, poor synchronization in two missile wing rotary courses.At present used slip covering, the wing internal hydraulic pressure driving mechanism of aircraft regulated the adaptive wing technologies such as camber, also because of the thriving type thinner thickness of Missile Body, without space mounting.
Summary of the invention
The present invention is directed to above-mentioned prior art situation, and design a kind of gear drive, purpose are provided is to make a word layout missile wing can realize cross folding, be folded in the bomb body fully before storing, the emission; Make guided missile in limited space, only need to drive two missile wing synchronous backward rotations by a drive unit, realize that missile wing is folding, launch, change the missile wing sweepback angle.
The present invention is achieved through the following technical solutions above-mentioned purpose, cross folding wing transmission device, comprise: be provided with axis hole and corresponding with the swivel nut that is equipped with in the gear box cover axis hole at the bottom of the gear housing, a side is provided with a flat surface in the gear housing, in flat surface one axis hole swivel nut is housed; Driving cluster gear forms with lower gear by cogging, and the lower gear of driving cluster gear is provided with the drive link mounting hole; Gear housing two sides all are equipped with band tooth missile wing major joint, are provided with socket with an end of tooth missile wing major joint, and the other end is provided with half tooth, socket respectively with left missile wing be connected missile wing and be connected, thrust ball bearing and lining all are housed in the axis hole that half tooth is provided with; In driving gear and the driving cluster gear axis hole selfaligning ball bearing is housed all; Rotating shaft one end is provided with screw rod; Rotating shaft is passed thrust ball bearing, the lining that is equipped with in the half tooth axis hole with tooth missile wing major joint that connects right missile wing and is installed on swivel nut on the gear housing inner platform over glaze hole, and be locked by self-locking nut and screw rod, right missile wing is connected with a joggle by half tooth and the cogging of driving cluster gear with tooth missile wing major joint; Rotating shaft is passed thrust ball bearing, the lining that is equipped with in the half tooth axis hole with tooth missile wing major joint that connects left missile wing and is installed on swivel nut on the gear box cover, and be locked by self-locking nut and screw rod, left missile wing is connected with a joggle by half tooth and the driving gear with tooth missile wing major joint; Driving gear further is connected with a joggle with the lower gear of driving cluster gear; Driving gear and driving cluster gear are passed respectively the selfaligning ball bearing that is equipped with in its axis hole by rotating shaft and are installed on the swivel nut of gear box cover, and are locked by self-locking nut and screw rod; Drive link one end passes the opening that gear housing is provided with and is connected with the drive link mounting hole, and the other end is equipped with joint.
The described rotating shaft the other end also is provided with interior hexagonal blind hole.
Described swivel nut outer ring is provided with outside thread, and an end inner ring is provided with shoulder hole, and the other end is the recess shape and periphery is provided with the spanner draw-in groove.
Described socket with tooth missile wing major joint is provided with mounting hole.
Described gear housing also is provided with tapped hole, connects and to use through hole, and four jiaos are provided with the connecting pin sheet, establishes in it in axis hole of flat surface and is provided with screw thread.
Described thrust ball bearing is installed in the two ends axis hole of half tooth.
Described selfaligning ball bearing is installed on respectively in the two ends axis hole of driving gear, driving cluster gear.
Transmission part is assembled in the gear housing, package unit uses bolt to be connected by gear housing connecting pin sheet and body, can adjust tie point and connecting bolt number according to different Missile Body wing load situations, both sides band tooth missile wing major joint is in order to connect a left side, right missile wing, be designed with simultaneously the part helical teeth, also can be changed to straight-tooth according to actual stand under load, the number of teeth is according to the actual maximum translation-angle design of missile wing, actuation gear is divided into, lower gear, rotate synchronously, drive respectively left, right missile wing rotates around the shaft, and the actuation gear lower gear connects drive link, in order to accept the driving force of a cover drive unit.
The joint input point that technical solution of the present invention arranges by the drive link end, drive in order to accept drive unit, the linear reciprocating motion of drive unit is converted into rotatablely moving of driving cluster gear, driving cluster gear cogs and drives right side band tooth missile wing major joint and rotate around the shaft, the driving cluster gear lower gear orders about the driving gear rotation, driving gear drives left side band tooth missile wing major joint and rotates around the shaft, reaches that left and right sides missile wing is folding, expansion and sweepback angle change.
The present invention program's advantage: the gear drive modularization, simple and reliable, folding easy accessibility; In the transmission process, stable drive is little to ballistic impact power; Drive gap and movable play are little, and missile wing launches, changes in the process of sweepback angle, and synchronism is good, without stuck action delay.By repacking, can be applicable to various word missile wing layout Missile Body wingfold and launch, become sweepback angle control.
Description of drawings
Fig. 1 is structural representation of the present invention.
Fig. 2 be among Fig. 1 A-A to generalized section.
Fig. 3 be among Fig. 1 A to schematic representation.
Fig. 4 be among Fig. 1 B to schematic representation.
Fig. 5 is the cross-sectional view of Fig. 1 shaft 4.
Fig. 6 is the cross-sectional view of swivel nut 5 among Fig. 1.
Fig. 7 is with the perspective view of tooth missile wing major joint 3 among Fig. 1.
Fig. 8 is the perspective view of driving cluster gear 6 among Fig. 1.
Fig. 9 is the perspective view of Fig. 1 middle gear casing 8.
Among the figure: the left missile wing of 1-, the right missile wing of 2-, 3-band tooth missile wing major joint, 31-socket, 32-half tooth, 33-mounting hole, 4-rotating shaft, hexagonal blind hole in the 41-, 42-screw rod, 5-swivel nut, the 51-outside thread, 52-shoulder hole, 53-spanner draw-in groove, the 6-driving cluster gear, 61-cogs, the 62-lower gear, 63-drive link mounting hole, 7-driving gear, 8-gear housing, 81-tapped hole, 82-connect uses through hole, 83-opening, 84-connecting pin sheet, 85-axis hole, 9-drive link, the 10-joint, 11-gear box cover, 12-lining, the 13-self-locking nut, 14-selfaligning ball bearing, 15-thrust ball bearing.
Embodiment
The invention will be further described below in conjunction with the embodiment of accompanying drawing, referring to Fig. 1-Fig. 4, cross folding wing transmission device, comprise: 8 ends of gear housing, be provided with axis hole 85 and corresponding with the swivel nut 5 that is equipped with in gear box cover 11 axis holes, a side is provided with a flat surface in the gear housing 8, in flat surface one axis hole 85 swivel nut 5 is housed; Driving cluster gear 6 by cog 61 and lower gear 62 form, the lower gear 62 of driving cluster gear 6 is provided with drive link mounting hole 63; Gear housing 8 two sides all are equipped with band tooth missile wing major joint 3, end with tooth missile wing major joint 3 is provided with socket 31, the other end is provided with half tooth 32, socket 31 respectively with left missile wing 1 be connected missile wing 2 and be connected, thrust ball bearing 15 and lining 12 all are housed in the axis hole that half tooth 32 is provided with; In driving gear 7 and driving cluster gear 6 axis holes selfaligning ball bearing 14 is housed all; Rotating shaft 4 one ends are provided with screw rod 42; Rotating shaft 4 is passed thrust ball bearing 15, the lining 12 that is equipped with in half tooth, 32 axis holes with tooth missile wing major joint 3 that connect right missile wing 2 and is installed on swivel nut 5 on the gear housing 8 inner platform over glaze holes 85, and be locked by self-locking nut 13 and screw rod 42, right missile wing 2 is by 61 being connected with a joggle with cogging of half tooth 32 of tooth missile wing major joint 3 and driving cluster gear 6; Rotating shaft 4 is passed thrust ball bearing 15, the lining 12 that is equipped with in half tooth, 32 axis holes with tooth missile wing major joint 3 that connect left missile wing 1 and is installed on swivel nut 5 on the gear box cover 11, and be locked by self-locking nut 13 and screw rod 42, left missile wing 1 is connected with a joggle with driving gear 7 by half tooth 32 with tooth missile wing major joint 3; Driving gear 7 further is connected with a joggle with the lower gear 62 of driving cluster gear 6; Driving gear 7 and driving cluster gear 6 are passed respectively the selfaligning ball bearing 14 that is equipped with in its axis hole and the swivel nut 5 that is installed on gear box cover 11 by rotating shaft 4, and are locked by self-locking nut 13 and screw rod 42; Drive link 9 one ends pass the opening 83 that gear housing 8 is provided with and are connected with drive link mounting hole 63, and the other end is equipped with joint 10.
Referring to Fig. 5, described rotating shaft 4 the other ends also are provided with interior hexagonal blind hole 41.
Referring to Fig. 6, described swivel nut 5 outer rings are provided with outside thread 51, one end inner rings and are provided with shoulder hole 52, and the other end is the recess shape and periphery is provided with spanner draw-in groove 53.
Referring to Fig. 7, described socket 31 with tooth missile wing major joint 3 is provided with mounting hole 33.
Referring to Fig. 9, described gear housing 8 also is provided with tapped hole 81, connect with 82, four jiaos of through holes and be provided with connecting pin sheet 84, establishes in it in axis hole 85 of flat surface and is provided with screw thread.
Referring to Fig. 2, described thrust ball bearing 15 is installed on the two ends in half tooth, 32 axis holes.
Referring to Fig. 2, described selfaligning ball bearing 14 is installed on respectively the two ends in driving gear 7, driving cluster gear 6 axis holes.
Embodiment:
Shown in accompanying drawing 1～2, transmission device of the present invention comprises: gear box cover 11, gear housing 8, driving cluster gear 6, driving gear 7, selfaligning ball bearing 14, thrust ball bearing 15, lining 12, swivel nut 5, self-locking nut 13, rotating shaft 4, band tooth missile wing major joint 3 and drive link 9, wherein be with tooth missile wing major joint 3 one ends to be provided with half tooth 32, be used for transmission, the other end is provided with socket 31 and mounting hole 33, is used for being connected with missile wing.Left missile wing 1 is connected with a joggle with driving gear 7 by half tooth 32 with tooth missile wing major joint 3, driving gear 7 further is connected with a joggle with the lower gear 62 of driving cluster gear 6, right missile wing 2 is by 61 being connected with a joggle with cogging of half tooth 32 of tooth missile wing major joint 3 and driving cluster gear 6, rotating shaft 4 one ends are provided with screw rod 42, be provided with interior hexagonal blind hole 41 in rotating shaft 4 the other ends, be used for assembling and positioning.Lining 12 adopts copper material, internal diameter and rotating shaft 4 are Spielpassung, external diameter is interference fit with band tooth missile wing major joint 3, when bearing larger radial force, can resiliently deformable, prevent that bearing is stuck, do not affect gear transmission, for reducing the frictional force of lining 12 and rotating shaft 4, open spiral groove on the surface within it.Referring to Fig. 6, swivel nut 5 outsides are provided with screw thread 51, respectively with the axis hole of gear box cover 11 and being threaded of gear housing 8 inner platform face upper shaft holes 85, swivel nut 5 one ends are the recess shape, periphery is provided with the spanner draw-in groove 53 of boss-shaped, so that regulate the screw thread degree of tightness, swivel nut 5 the other end inside are provided with shoulder hole 52, macropore and rotating shaft 4 are Spielpassung, avoid rotating shaft to become the beam type force transferring structure, thereby guarantee the stationarity of rotating shaft 4 power transmissions, rotating shaft 4 pass aperture and above self-locking nut 13 is arranged, be used for fixed rotating shaft 4.Wherein be pressed in the play that to regulate thrust ball bearing 15 with swivel nut 5 on the tooth missile wing major joint 3, prevent that it is stuck; The swivel nut 5 that is pressed on driving gear 7 and the driving cluster gear 6 then is used for being fixed selfaligning ball bearing 14.Referring to Fig. 8, driving cluster gear 6 is divided into and cogs 61 and lower gear 62 two-part, decided by concrete technology, divide two sections to process by two gear assemblings or a gear, and gear teeth face is staggered up and down, staggered tolerance can be controlled, thereby guarantee the synchronism of left missile wing 1 and right missile wing 2 folding and expandings, adopt simultaneously this mode can eliminate the gear transmission jump, realize the missile wing cross folding, such as Fig. 3.Driving cluster gear 6 Dedendum surfaces are provided with the mounting hole 63 of drive link 9, in order to accept the driving force of a cover drive unit.Referring to Fig. 9, have tapped hole 81 and axis hole 85 is all corresponding supporting with gear box cover 11 at gear housing 8, gear housing 8 and gear box cover 11 are fixedly connected with by screw, the concrete quantity of tapped hole 81 can be born outer carrying according to gear housing 8 and be decided, gear housing 8 bottom surfaces also are provided with the opening 83 that a drive link 9 is connected with driving cluster gear 6 lower ends simultaneously, its four jiaos also are provided with connecting pin sheet 84, can open to connect to be convenient to be connected with other structures with through hole 82.
Installation of the present invention:
1) installation with tooth missile wing major joint 3, driving gear 7 and driving cluster gear 6 of left missile wing 1 connection:
Lining 12 is packed in half tooth, 32 axis holes with tooth missile wing major joint 3 that are connected with left missile wing 1, the thrust ball bearing 15 of in half tooth, 32 1 end axis holes, packing into, be respectively charged into selfaligning ball bearing 14 at driving gear 7 and driving cluster gear 6 one ends, rotating shaft 4 is packed in the axis hole 85 of gear housing 8, the band tooth missile wing major joint 3 that will be connected with left missile wing 1, driving gear 7, driving cluster gear 6 is respectively charged in each self-corresponding rotating shaft 4, again thrust ball bearing 15 is packed in half tooth, 32 the other end axis holes, selfaligning ball bearing 14 is respectively charged into the other end of driving gear 7 and driving cluster gear 6.
2) installation with tooth missile wing major joint 3 of right missile wing 2 connections:
Lining 12 is packed in half tooth, 32 axis holes with tooth missile wing major joint 3 that are connected with right missile wing 2, enter thrust ball bearing 15 in that half tooth, 32 two ends axis holes are in-built, half tooth 32 with tooth missile wing major joint 3 that connects right missile wing 2 is docked with 61 engagements that cog of driving cluster gear 6, and half tooth, 32 axis holes are aimed at the axis hole 85 of gear housing 8 flat surface, cover gear box cover 11, rotating shaft 4 is inserted in axis hole corresponding to gear box covers 11 and gear housing 8 and half tooth, 32 axis holes with tooth missile wing major joint 3.
3) with swivel nut 5 respectively corresponding rotating shaft 4 separately be screwed in gear box cover 11 and the gear housing 8, regulate with swivel nut 5 corresponding on the tooth missile wing major joint 3, screw swivel nut 5 corresponding on driving gear 7 and the driving cluster gear 6, self-locking nut 13 is screwed in the screw rod 42 of rotating shaft 4 and tightens up, screw is screwed in the tapped hole 81 again, make gear box cover 11 and gear housing 8 be connected and fixed so far transmission device installation.
As can be seen from Figure 1, after mechanism received instruction, power source arrived drive link 9 by joint 10 with transmission of power, and then drove driving cluster gear 6 rotations, 6 minutes upper lower gears of driving cluster gear, and synchronously rotation.Lower gear drives driving gear 7 and rotates, and then the band tooth missile wing major joint 3 that driving is connected with left missile wing 1 rotates i.e. left missile wing 1 rotation.Meanwhile, driving cluster gear 6 cogs and drives band tooth missile wing major joint 3 rotations that are connected with right missile wing 2, i.e. right missile wing 2 rotations.After missile wing was deployed into the precalculated position, power source was received instruction, quit work, and missile wing is locked, and launched to put in place.In flight course, if need to change the sweepback angle, then only need again to the power source firing order.
Claims (2)
1. cross folding wing transmission device, it is characterized in that, comprise: gear housing [8] end, be provided with axis hole [85] and corresponding with the swivel nut [5] that is equipped with in gear box cover [11] axis hole, and a side is provided with a flat surface in the gear housing [8], and swivel nut [5] is housed in flat surface one axis hole [85]; Driving cluster gear [6] is comprised of cog [61] and lower gear [62], and the lower gear [62] of driving cluster gear [6] is provided with drive link mounting hole [63]; Gear housing [8] both sides all are equipped with band tooth missile wing major joint [3], one end of band tooth missile wing major joint [3] is provided with socket [31], the other end is provided with half tooth [32], the described socket [31] of both sides respectively with left missile wing [1] be connected missile wing [2] and be connected, thrust ball bearing [15] and lining [12] all are housed in the axis hole that half tooth [32] is provided with; In driving gear [7] and driving cluster gear [6] axis hole selfaligning ball bearing [14] is housed all; Rotating shaft [4] one ends are provided with screw rod [42]; Rotating shaft [4] is passed thrust ball bearing [15], the lining [12] that is equipped with in half tooth [32] axis hole of the band tooth missile wing major joint [3] that connects right missile wing [2] and is installed on swivel nut [5] on gear housing [8] the inner platform over glaze hole [85], and be locked by self-locking nut [13] and screw rod [42], right missile wing [2] is connected with a joggle by half tooth [32] of band tooth missile wing major joint [3] and cog [61] of driving cluster gear [6]; Rotating shaft [4] is passed thrust ball bearing [15], the lining [12] that is equipped with in half tooth [32] axis hole of the band tooth missile wing major joint [3] that connects left missile wing [1] and is installed on swivel nut [5] on the gear box cover [11], and be locked by self-locking nut [13] and screw rod [42], left missile wing [1] is connected with a joggle with driving gear [7] by half tooth [32] of band tooth missile wing major joint [3]; Driving gear [7] further is connected with a joggle with the lower gear [62] of driving cluster gear [6]; The selfaligning ball bearing [14] that is equipped with in driving gear [7] and driving cluster gear [6] axis hole and the swivel nut [5] that is installed on gear box cover [11] are passed respectively in rotating shaft [4], and are locked by self-locking nut [13] and screw rod [42]; Drive link [9] one ends pass the opening [83] that gear housing [8] is provided with and are connected with drive link mounting hole [63], and the other end is equipped with joint [10].
2. cross folding wing transmission device according to claim 1 is characterized in that, all rotating shafts [4] the other end also is provided with interior hexagonal blind hole [41].
3, cross folding wing transmission device according to claim 1 is characterized in that, all swivel nuts [5] outer ring is provided with outside thread [51], and an end inner ring is provided with shoulder hole [52], and the other end is the recess shape and periphery is provided with spanner draw-in groove [53].
4, cross folding wing transmission device according to claim 1 is characterized in that, the socket [31] of both sides band tooth missile wing major joints [3] is provided with mounting hole [33].
5, cross folding wing transmission device according to claim 1 is characterized in that, described gear housing [8] also is provided with tapped hole [81], connects with through hole [82], and four jiaos are provided with connecting pin sheet [84], establishes in it in axis hole [85] of flat surface and is provided with screw thread.
6, cross folding wing transmission device according to claim 1 is characterized in that, described thrust ball bearing [15] is installed on the two ends in half tooth [32] axis hole.
7, cross folding wing transmission device according to claim 1 is characterized in that, described selfaligning ball bearing [14] is installed on respectively the two ends in driving gear [7], driving cluster gear [6] axis hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010602705 CN102121512B (en) | 2010-12-23 | 2010-12-23 | Crossing and folding wing transmission device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010602705 CN102121512B (en) | 2010-12-23 | 2010-12-23 | Crossing and folding wing transmission device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102121512A CN102121512A (en) | 2011-07-13 |
| CN102121512B true CN102121512B (en) | 2013-03-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201010602705 Active CN102121512B (en) | 2010-12-23 | 2010-12-23 | Crossing and folding wing transmission device |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9689650B2 (en) | 2012-12-18 | 2017-06-27 | Rafael Advanced Defense Systems Ltd. | Wing deployment mechanism |
| CN103837045B (en) * | 2014-02-24 | 2015-05-13 | 中国航天时代电子公司 | Foldable diamond-shaped missile wing spread system |
| CN103968002A (en) * | 2014-04-18 | 2014-08-06 | 江西洪都航空工业集团有限责任公司 | Missile wing gear transmission folding mechanism |
| CN104197791A (en) * | 2014-09-17 | 2014-12-10 | 江西洪都航空工业集团有限责任公司 | Crossing folding missile wing mechanism |
| CN107499496A (en) * | 2017-09-12 | 2017-12-22 | 江西洪都航空工业集团有限责任公司 | One kind intersects negative dihedral wing face fold mechanism |
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|---|---|---|---|---|
| US6314886B1 (en) * | 1999-02-19 | 2001-11-13 | Rheinmetall W & M Gmbh | Projectile to be fired from a weapon barrel and stabilized by a guide assembly |
| CN1515870A (en) * | 2003-01-10 | 2004-07-28 | 王启振 | Variable wing guidance bomb |
| US6880780B1 (en) * | 2003-03-17 | 2005-04-19 | General Dynamics Ordnance And Tactical Systems, Inc. | Cover ejection and fin deployment system for a gun-launched projectile |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE519764C2 (en) * | 2000-08-31 | 2003-04-08 | Bofors Defence Ab | Canardfenaggregat |
| WO2006086532A2 (en) * | 2005-02-07 | 2006-08-17 | Bae Systems Information And Electronic Systems | Three axis aerodynamic control of guided munitions |
| IL189785A (en) * | 2008-02-26 | 2013-07-31 | Elbit Systems Ltd | Foldable and deployable panel |
| KR101069246B1 (en) * | 2009-06-11 | 2011-10-04 | 국방과학연구소 | Apparatus for deploying wing and apparatus for launching flight having the same |
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- 2010-12-23 CN CN 201010602705 patent/CN102121512B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6314886B1 (en) * | 1999-02-19 | 2001-11-13 | Rheinmetall W & M Gmbh | Projectile to be fired from a weapon barrel and stabilized by a guide assembly |
| CN1515870A (en) * | 2003-01-10 | 2004-07-28 | 王启振 | Variable wing guidance bomb |
| US6880780B1 (en) * | 2003-03-17 | 2005-04-19 | General Dynamics Ordnance And Tactical Systems, Inc. | Cover ejection and fin deployment system for a gun-launched projectile |
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| CN102121512A (en) | 2011-07-13 |
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Application publication date: 20110713 Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000184 Denomination of invention: Crossing and folding wing transmission device Granted publication date: 20130327 License type: Exclusive License Record date: 20140714 |
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Effective date of registration: 20151229 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. |