CN106871740A - The application of barrel assemblies, shell carry frame and shell carry frame on unmanned plane - Google Patents
The application of barrel assemblies, shell carry frame and shell carry frame on unmanned plane Download PDFInfo
- Publication number
- CN106871740A CN106871740A CN201710203937.2A CN201710203937A CN106871740A CN 106871740 A CN106871740 A CN 106871740A CN 201710203937 A CN201710203937 A CN 201710203937A CN 106871740 A CN106871740 A CN 106871740A
- Authority
- CN
- China
- Prior art keywords
- gun barrel
- snap ring
- end cap
- shell
- barrel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000000712 assembly Effects 0.000 title claims abstract description 38
- 238000000429 assembly Methods 0.000 title claims abstract description 38
- 239000004677 Nylon Substances 0.000 claims abstract description 29
- 229920001778 nylon Polymers 0.000 claims abstract description 29
- 238000013016 damping Methods 0.000 claims abstract description 24
- 230000005489 elastic deformation Effects 0.000 claims abstract description 5
- 239000011324 bead Substances 0.000 claims description 9
- 229910000831 Steel Inorganic materials 0.000 claims description 6
- 239000010959 steel Substances 0.000 claims description 6
- 210000004534 cecum Anatomy 0.000 claims description 3
- 230000003139 buffering effect Effects 0.000 claims description 2
- 239000000203 mixture Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 8
- 238000009434 installation Methods 0.000 description 15
- 238000010586 diagram Methods 0.000 description 3
- 230000001934 delay Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Abstract
The present invention relates to unmanned plane field, specifically provide a kind of barrel assemblies, the application of shell carry frame and shell carry frame on unmanned plane, gun barrel of the invention includes shell sleeve, snap ring, damping spring, nylon buffing pad and gun barrel end cap, the shell sleeve be used for accommodate shell body and with snap ring clamping, one end connection nylon buffing pad of the damping spring, and prop up shell sleeve through snap ring hollow bulb, the other end of damping spring accesses gun barrel end cap, it is pressurized and produces the damping spring of elastic deformation to be placed in gun barrel end cap together with nylon buffing pad, nylon buffing pad withstands on deck on chute inwall under the active force of the elastic deformation of damping spring.The clamping and disengaging of shell sleeve of the invention and snap ring, disassembly process are simple and quick；The damping spring that is provided with end cap, deck is pressed against in draw-in groove simultaneously, when continued jitters flight or carry are used aboard, it is ensured that the stability of shell sleeve and snap ring in clamping.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, more particularly to a kind of connected mode is firm, the gun barrel group of fast demountable
Part and the shell carry frame with the barrel assemblies, and the application of the shell carry frame on unmanned plane.
Background technology
Unmanned plane is the not manned aircraft manipulated using radio robot and the presetting apparatus provided for oneself, extensively
Be applied to dual-use field, for example take photo by plane, agricultural plant protection, disaster relief, mapping, electric inspection process, movies-making etc. it is each
Individual field.In order to realize unmanned plane in the use in these fields, it is necessary to install corresponding carry equipment, such as cloud on unmanned plane
Platform, gondola, megaphone, photographic equipment etc..Common, these carry equipment are arranged on unmanned plane by mounting seat.
Patent document CN205738128U discloses a kind of fast installing seat and unmanned plane, and the fast installing seat includes first
Installation portion and the second installation portion for being provided with chute, the first installation portion are provided with what is slided along its length in chute
Slide rail, so as to the first installation portion is detachably arranged on the second installation portion；First installation portion is provided with lever component,
Second installation portion is provided with the guide coordinated with lever component；Or second installation portion be provided with lever component, first installs
Portion is provided with the guide coordinated with lever component.First installation portion and the second installation portion realize detachable installation by chute,
The limit method of the first installation portion has two kinds, and lever or the guiding and stopper slot that pass through " 7 " font are promoted by cam structure
Realized with push rod spacing.
By above-mentioned mounting seat, in that context it may be convenient to which various carry equipment are arranged on unmanned plane, but above-mentioned installation
Seat is more complicated for spacing structure, in aircraft carry shell or continued jitters flight, it is impossible to solid and reliable resistance big gun
Setback-impact power after pop-off fire transmitting, use time is long, can reduce the reliability of carry, it is serious in the case of can directly lose
Effect.
The content of the invention
It is an object of the invention to provide a kind of simple structure, firm connected mode, the barrel assemblies of fast demountable and band
There is the carry frame of the barrel assemblies, with the drawbacks described above for overcoming mounting seat of the prior art to exist.
To achieve these goals, the invention provides a kind of barrel assemblies, including shell sleeve, snap ring, damping spring,
Nylon buffing pad and gun barrel end cap；Wherein, shell sleeve is used to accommodate shell body, and its top end opening, distal end faces are extended with
Deck, snap ring top is provided with the chute being engaged with deck, and deck screws in the clamping that chute realizes shell sleeve and snap ring；
It is cavity and top end opening in gun barrel end cap, damping spring one end is fixed in cavity, other end connection nylon delays
Red seat, snap ring end is fixed on gun barrel end cap top, and the nylon buffing pad is against the end of shell sleeve through snap ring endoporus
On end face, the close contact of deck and chute inwall is realized.
The nylon buffing pad includes diameter less than the abutting part of snap ring diameter of bore and with diameter greater than snap ring diameter of bore
Limiting plate, limiting plate is connected with damping spring.
Sunk screw is threadedly coupled through the through hole on snap ring with shell end cap, is pressurized and produces the damping spring of elastic deformation
It is placed in gun barrel end cap together with nylon buffing pad, meanwhile, nylon buffing pad is under the elastic force active force of damping spring by deck top
On chute inwall.
The tail end closing of chute, the tail end of chute is provided with prevents the stop screw that deck skids off chute, and deck is from chute
Head end is slipped into until the stop screw stops.
The distal end faces of the shell sleeve are rounded, and three decks are circumferentially uniformly distributed along end face, the snap ring top
It is provided with and three corresponding three sections of chutes of deck and three sections of breach.
The snap ring is also equipped with bead screw, and the steel ball of the bead screw hangs down from snap ring near the side of nylon buffing pad
Direct puncture mistake, in chute.
A kind of shell carry frame, including upper arm and above-mentioned barrel assemblies, upper arm top offer bolt hole, and bottom is provided with
The T-shape guide-track groove of one end closing, is provided with the T-shape guide rail coordinated with T-shape guide-track groove on the gun barrel end cap of barrel assemblies,
Upper arm and gun barrel end cap connected by T-shape guide rail and T-shape slot, while in the cecum and T-shape guide rail of T-shape guide-track groove
One end is provided with corresponding through hole and screwed hole, and trip bolt realizes upper arm 1 and gun barrel end cap in being threaded into hole through through hole
Be fixedly connected.
Described shell carry frame, including the planet barrel assemblies that multiple above-mentioned barrel assemblies are constituted, be connected barrel assemblies
Connected by gun barrel end cap.
Planet barrel assemblies include the four planet gun barrels for being located at the center gun barrel at center and being connected to around the gun barrel of center,
Draw-in groove is provided with the gun barrel end cap lateral wall of center gun barrel, linking arm is provided with the gun barrel end cap lateral wall of planet gun barrel,
Linking arm is stretched into draw-in groove, and attachment screw is connected through draw-in groove and linking arm with locking nut, realizes planet gun barrel and center big gun
The fixation of cylinder；The T-shape guide rail is arranged on the gun barrel end cap of the center gun barrel of planet barrel assemblies.
Application of the shell carry frame on unmanned plane, the upper arm top of shell carry frame is bolted in unmanned plane machine
Body bottom.
Compared with prior art, it is of the invention at least to have the advantages that, rotated against by shell sleeve and snap ring,
Just can easily and fast realize the clamping and disengaging of shell sleeve and snap ring, it is no longer necessary to remaining fixedly connected part, reduce zero
Number of packages amount, and clamping and disengaging process are simply firm；Relative to prior art, Fast Installation guidance mode of the invention, letter
Easy and firm threaded connection limit method can effectively ensure that carry module is relative to fixation in carry striking type carry
The main equipment of connection is more firm, reliable.
Further, while being provided with damping spring in end cap, damping spring is connected with nylon buffing pad by its one end
The end of shell sleeve is against, axial thrust is applied to shell sleeve, on the one hand, when shell sleeve and snap ring clamping, deck
On the inwall for resting firmly against chute in the presence of axial thrust, shell sleeve consolidates clamping, especially in aircraft continued jitters
During flight, the stability that shell sleeve is connected with snap ring is improve.On the other hand, when dismounting shell sleeve is needed, rotation
Shell sleeve, after deck skids off chute, shake spring is immediately by the ejection of shell sleeve, and ejection process is fast favourable.
Further, the tail end in chute is provided with stop screw, and the deck slipped into groove is encountered stop screw and stopped, and protects
Card seat is once slipped into and is just accurately positioned in chute, effectively prevents deck from excessively being rotated relative to chute and skidding off chute.
Further, shell sleeve design is rounded, and three identical decks are circumferentially uniformly distributed along end face, and snap ring top sets
Be equipped with three corresponding three sections of chutes of deck and three sections of breach, both during clamping, uniform force, single deck clamping
During failure, it is unlikely to cause shell sleeve to come off.Further increase the stability that shell sleeve is connected with snap ring.
Further, the present invention is provided with bead screw in chute, and deck is slipped over into chute, by after bead screw, glass
The steel ball of pearl screw applies axial thrust to deck so that deck is tightly slided close to chute inwall, further strengthens shell
The stability that sleeve is connected with snap ring.
Further, after the end cap of the barrel assemblies of shell carry frame of the invention is connected with upper arm by T-shape slot, then
Worn by trip bolt and fix both, connected mode is easy and effective.
Further, barrel assemblies of the invention can be assembled into planet barrel assemblies, center barrel assemblies and planet gun barrel
Connected by connecting screw and nut between component, unmanned plane can greatly be carried by a upper arm carry multiple barrel assemblies
The portability and carry quantity of shell are risen.
Brief description of the drawings
Fig. 1 is the barrel assemblies exploded perspective view of the embodiment of the present invention；
Fig. 2 is the forward structure schematic diagram of the shell carry frame of the embodiment of the present invention；
Fig. 3 is the reverse geometry schematic diagram of the shell carry frame of the embodiment of the present invention；
The front view that Fig. 4 is observed for the planet barrel assemblies of the embodiment of the present invention along shell sleeve end face；
Fig. 5 is application schematic diagram of the shell carry frame of the present invention on unmanned plane.
In accompanying drawing：1st, upper arm, 2, planet barrel assemblies, 3, trip bolt, 4, unmanned plane, 21, center barrel assemblies, 22,
Planet barrel assemblies, 23, attachment screw, 24, locking nut, 221, gun barrel end cap, 222, damping spring, 223, nylon buffering
Seat, 224, snap ring, 225, bead screw, 226, stop screw, 227, sunk screw, 228, shell sleeve.
Specific embodiment
The present invention will be further described below in conjunction with the accompanying drawings, but the purposes and purpose of these exemplary embodiments are only used
To enumerate the present invention, not constitute any type of any restriction to real protection scope of the invention, it is more non-will be of the invention
Protection domain is confined to this.
The barrel assemblies of the implementation method provided referring to Fig. 1, the present invention include that shell sleeve 228, snap ring 224, nylon delay
Red seat 223 and gun barrel end cap 221, the shell sleeve 228 are used to accommodate shell body, its top end opening, and distal end faces are in circle
Shape is simultaneously provided with three decks of evagination being uniformly distributed circumferentially；The one end relative with deck of snap ring 224 is axially extending described
Deck is engaged chute, and chute end face is U-shaped or rectangle, and opening is inwardly；Breach is formed between adjacent chute, in notch part
Through hole is provided with, the screwed hole with the openend of gun barrel end cap 221 is corresponding, snap ring 224 and gun barrel end cap 221 pass through sunk screw
227 pass through the through hole of the notch part to be threadedly coupled with the screwed hole of gun barrel end cap 221, and the deck of shell sleeve 228 can be put
Enter the breach, then slip into chute clockwise with respect to snap ring, realize the clamping of shell sleeve 228 and snap ring 224.Additionally, big gun
It is cavity and top end opening in cylinder end cap 221, damping spring 222 and nylon buffing pad 223, Buddhist nun is provided with gun barrel end cap cavity
Imperial buffing pad 223 includes diameter less than the abutting part of the diameter of bore of snap ring 224 and spacing with diameter greater than the diameter of bore of snap ring 224
Base, the abutting part and connecting portion are in the form of a column, and abutting part is the stud bump extended from the side end face of limiting plate one；Damping
The one end of spring 222 is fixed in the cavity of gun barrel end cap 221, and the limiting plate of other end connection nylon buffing pad 223, nylon delays
The contact part of red seat 223 is against in the distal end faces of shell sleeve 228 through the endoporus of snap ring 224, and now damping spring 222 is subject to
It is compressed in and elastic deformation is produced in gun barrel end cap 221, applying an axial direction to shell sleeve 228 by nylon buffing pad 223 pushes away
Power, realizes the close contact of deck and chute inwall.
Additionally, the afterbody one end in chute along clockwise direction is additionally provided with stop screw 226, stop screw 226 is from Buddhist nun
The side of imperial buffing pad axially penetrates, and is passed from chute afterbody, and deck slips into chute after running into stop screw 226 and stops sliding
It is dynamic.
During installation, snap ring is first enclosed within the contact part of nylon buffing pad, is docked with gun barrel end cap 221, and by countersunk head spiral shell
Nail 227 is fixed, then being against the end of shell sleeve 228 on the contact part of nylon buffing pad, and three deck alignments are described
Three breach of snap ring 224, and apply to be enough to overcome the thrust of damping spring elastic force, when three decks and snap ring 224 3 lack
During mouth contact, rotated clockwise relative to snap ring, deck slips into chute, until stopping at stop screw 226.Meanwhile, remove
Thrust, nylon buffing pad 223 withstands on deck on chute inwall under the elastic force of damping spring 222.
Additionally, being provided with bead screw 225 in snap ring, the steel ball of the bead screw 225 is close to nylon buffing pad from snap ring
223 side passes perpendicularly through, in chute, when deck in chute by after steel ball, steel ball applies an axle to deck
To thrust.
Additionally, as shown in Figures 2 and 3, present invention also offers a kind of shell carry frame, including by 1, center of wall built-up
Gun barrel 21 and four planet barrel assemblies 2 of the composition of planet gun barrel 22, with reference to shown in Fig. 4, outside the gun barrel end cap of center gun barrel 21
Draw-in groove is provided with the wall of side, linking arm is provided with the gun barrel end cap lateral wall of planet gun barrel 22, linking arm is stretched into draw-in groove, even
Connect screw 23 to be connected with locking nut 24 through draw-in groove and linking arm, realize the fixation of planet gun barrel 22 and center gun barrel 21；Hang
The lower end of arm 1 is provided with the T-shape guide-track groove of not insertion, and the gun barrel end cap of center gun barrel 21 is provided with leads with the lower end T-shape of upper arm 1
The T-shape guide rail that track slot coordinates, the T-shape guide rail can be inserted in the T-shape guide-track groove of upper arm lower end, while in T-shape guide rail
The cecum of groove and one end of T-shape guide rail are provided with corresponding through hole and screwed hole, and T-shape guide-track groove is inserted in T-shape guide rail
Afterwards, upper arm is fixedly connected with center gun barrel end cap by trip bolt 3.
Additionally, as described in Figure 5, application of the shell carry frame of the present invention on unmanned plane, upper arm is fixedly connected by screw
On the body of unmanned plane 4, realize that the shell carry frame of unmanned plane can be with fast assembling-disassembling.
Claims (10)
1. barrel assemblies, it is characterised in that including shell sleeve (228), snap ring (224), damping spring (222), nylon buffering
Seat (223) and gun barrel end cap (221)；Wherein, shell sleeve (228) is for accommodating shell body, its top end opening, distal end faces
Deck (229) is extended with, snap ring (224) top is provided with the chute being engaged with deck (229), and deck (229) screws in chute reality
The clamping of existing shell sleeve (228) and snap ring (224)；
It is cavity and top end opening in the gun barrel end cap (221), damping spring (222) one end is fixed in cavity, the other end
Connection nylon buffing pad (223), snap ring (224) end is fixed on gun barrel end cap (221) top, the nylon buffing pad (223)
It is against in the distal end faces of shell sleeve (228) through snap ring (224) endoporus, realizes that deck (229) is tight with chute inwall
Contact.
2. barrel assemblies according to claim 1, it is characterised in that the nylon buffing pad (223) is less than including diameter
The abutting part and the limiting plate with diameter greater than snap ring (224) diameter of bore of snap ring (224) diameter of bore, limiting plate and damping
Spring (222) is connected.
3. barrel assemblies according to claim 1, it is characterised in that sunk screw (227) is through logical on snap ring (224)
Hole is threadedly coupled with shell end cap (221), and the damping spring (222) of the generation elastic deformation that is pressurized is together with nylon buffing pad (223)
It is placed in gun barrel end cap (221), meanwhile, nylon buffing pad (223) is under the elastic force active force of damping spring (222) by deck
(229) withstand on chute inwall.
4. barrel assemblies according to claim 1, it is characterised in that the tail end closing of chute, the tail end of chute is provided with system
Only deck (229) skids off the stop screw (226) of chute, and deck (229) is slipped into up to the stop screw from the head end of chute
(226) stop.
5. barrel assemblies according to claim 1, it is characterised in that the distal end faces of the shell sleeve (228) are in circle
Shape, three decks (229) are circumferentially uniformly distributed along end face, and snap ring (224) top is provided with and three decks corresponding three
Section chute and three sections of breach.
6. barrel assemblies according to claim 1, it is characterised in that the snap ring is also equipped with bead screw (225), described
The steel ball of bead screw (225) is passed perpendicularly through from snap ring (224) near the side of nylon buffing pad (223), in chute.
7. shell carry frame, it is characterised in that including the barrel assemblies described in upper arm (1) and any one of claim 1 to 6, hangs
Arm (1) top offers bolt hole, and bottom is provided with the T-shape guide-track groove of one end closing, the gun barrel end cap (221) of barrel assemblies
On be provided with the T-shape guide rail coordinated with T-shape guide-track groove, upper arm (1) and gun barrel end cap (221) are by T-shape guide rail and " T "
Type groove is connected, while corresponding through hole and screwed hole is provided with the cecum of T-shape guide-track groove and one end of T-shape guide rail, tightly
Gu screw (3) realizes being fixedly connected for upper arm (1) and gun barrel end cap (221) in being threaded into hole through through hole.
8. shell carry frame according to claim 7, it is characterised in that the planet gun barrel including multiple barrel assemblies composition
Component (2), is connected between the barrel assemblies that are connected by gun barrel end cap (221).
9. shell carry frame according to claim 8, it is characterised in that planet barrel assemblies (2) are including positioned at center
Center gun barrel (21) and four planet gun barrels (22) being connected to around center gun barrel (21), the gun barrel end cap of center gun barrel (21)
Draw-in groove is provided with lateral wall, linking arm is provided with the gun barrel end cap lateral wall of planet gun barrel (22), linking arm stretches into draw-in groove
In, attachment screw (23) is connected through draw-in groove and linking arm with locking nut (24), realizes planet gun barrel (22) and center gun barrel
(21) fixation；The T-shape guide rail is arranged on the gun barrel end cap of center gun barrel (21) of planet barrel assemblies (2).
10. application of a kind of shell carry frame as described in any one of claim 7 to 9 on unmanned plane, it is characterised in that hang
Arm (1) top is bolted in unmanned plane organism bottom.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710203937.2A CN106871740B (en) | 2017-03-30 | 2017-03-30 | The application of barrel assemblies, shell carry frame and shell carry frame on unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710203937.2A CN106871740B (en) | 2017-03-30 | 2017-03-30 | The application of barrel assemblies, shell carry frame and shell carry frame on unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106871740A true CN106871740A (en) | 2017-06-20 |
| CN106871740B CN106871740B (en) | 2018-10-30 |
Family
ID=59160398
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710203937.2A Active CN106871740B (en) | 2017-03-30 | 2017-03-30 | The application of barrel assemblies, shell carry frame and shell carry frame on unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106871740B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444650A (en) * | 2017-07-14 | 2017-12-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of anti-sway retainer of airborne stores |
| CN107826249A (en) * | 2017-11-29 | 2018-03-23 | 浙江临航智能科技有限公司 | A kind of unmanned plane bomb droping gear |
| CN111981918A (en) * | 2020-08-25 | 2020-11-24 | 西安近代化学研究所 | Connecting device for combined warhead |
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| EP2520897B1 (en) * | 2011-05-05 | 2014-07-09 | Alenia Aermacchi S.p.A. | Aircraft provided with a launch system for launching smoke markers |
| CN204864620U (en) * | 2015-07-10 | 2015-12-16 | 深圳市森讯达电子技术有限公司 | Unmanned aerial vehicle carries extinguishing device |
| CN205533646U (en) * | 2015-12-16 | 2016-08-31 | 金龙 | Fast handler of unmanned aerial vehicle airborne equipment |
| CN206919763U (en) * | 2017-03-30 | 2018-01-23 | 西安天鹰防务科技有限公司 | Barrel assemblies, shell carry frame and unmanned plane |
-
2017
- 2017-03-30 CN CN201710203937.2A patent/CN106871740B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2520897B1 (en) * | 2011-05-05 | 2014-07-09 | Alenia Aermacchi S.p.A. | Aircraft provided with a launch system for launching smoke markers |
| CN204864620U (en) * | 2015-07-10 | 2015-12-16 | 深圳市森讯达电子技术有限公司 | Unmanned aerial vehicle carries extinguishing device |
| CN205533646U (en) * | 2015-12-16 | 2016-08-31 | 金龙 | Fast handler of unmanned aerial vehicle airborne equipment |
| CN206919763U (en) * | 2017-03-30 | 2018-01-23 | 西安天鹰防务科技有限公司 | Barrel assemblies, shell carry frame and unmanned plane |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444650A (en) * | 2017-07-14 | 2017-12-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of anti-sway retainer of airborne stores |
| CN107444650B (en) * | 2017-07-14 | 2020-07-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Anti-swing stopper for airborne suspended object |
| CN107826249A (en) * | 2017-11-29 | 2018-03-23 | 浙江临航智能科技有限公司 | A kind of unmanned plane bomb droping gear |
| CN111981918A (en) * | 2020-08-25 | 2020-11-24 | 西安近代化学研究所 | Connecting device for combined warhead |
| CN111981918B (en) * | 2020-08-25 | 2022-08-19 | 西安近代化学研究所 | Connecting device for combined warhead |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106871740B (en) | 2018-10-30 |
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Address after: 210000 two, B unit 300, Zhihui Road, Qilin science and Technology Innovation Park, Nanjing, Jiangsu. Patentee after: Nanjing Hua Jian Bao Ke Engineering Technology Co., Ltd. Address before: 210000 3 3 410, long pan Road, Xuanwu District, Nanjing, Jiangsu Patentee before: Nanjing Hua Jian Bao Ke Engineering Technology Co., Ltd. |
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| CP02 | Change in the address of a patent holder |