CN106477047A - A kind of aerial howitzer launch craft - Google Patents
A kind of aerial howitzer launch craft Download PDFInfo
- Publication number
- CN106477047A CN106477047A CN201611046827.1A CN201611046827A CN106477047A CN 106477047 A CN106477047 A CN 106477047A CN 201611046827 A CN201611046827 A CN 201611046827A CN 106477047 A CN106477047 A CN 106477047A
- Authority
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- China
- Prior art keywords
- aircraft
- clip
- support arm
- epivalve
- gun
- 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.)
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Links
- 230000003139 buffering effect Effects 0.000 claims abstract description 15
- 238000010521 absorption reaction Methods 0.000 claims abstract description 11
- 230000035939 shock Effects 0.000 claims abstract description 11
- 238000009527 percussion Methods 0.000 claims description 23
- 230000003287 optical effect Effects 0.000 claims description 15
- 238000005452 bending Methods 0.000 claims description 11
- 238000013016 damping Methods 0.000 claims description 5
- 239000007787 solid Substances 0.000 claims description 4
- 238000005266 casting Methods 0.000 claims description 3
- 230000007306 turnover Effects 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 239000000463 material Substances 0.000 abstract description 2
- 238000000465 moulding Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 9
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 241000219991 Lythraceae Species 0.000 description 1
- 235000014360 Punica granatum Nutrition 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Classifications
-
- 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
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
- B64D1/06—Bomb releasing; Bomb doors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
- B64C1/063—Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A25/00—Gun mountings permitting recoil or return to battery, e.g. gun cradles; Barrel buffers or brakes
- F41A25/10—Spring-operated systems
- F41A25/12—Spring-operated systems using coil springs
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Abstract
The invention belongs to aircraft manufacture field, and in particular to a kind of aerial howitzer launch craft.The present invention will fold aircraft and organically combine with grenade launcher, be easy to fold, be easy to dismounting, be that soldier provides a kind of aerial fire support device of the transport that is easy to carry.By designing effective shock absorption buffering mechanism, can be very good to ensure fire accuracy.The aerial howitzer launch craft simple structure, from moulding material, can effectively reduce the cost taken by themselves of the weapon device, with great using value.
Description
Technical field
The invention belongs to aircraft manufacture field, and in particular to a kind of aerial howitzer launch craft.
Background technology
Rotor craft is the course of new aircraft that a kind of structure is novel, manipulation is simple, stability is high, and it has vertical rising
Unique flight function such as drop, hovering and motor-driven avoidance, can more preferably complete aerial mission in less space.
But, in current prior art, but grenade launcher and rotor craft are combined by few people, are given full play to
Rotor craft landing requirement is low, individual soldier's firepower of soldier is greatly improved, provides aerial fire support.
Content of the invention
For this purpose, the technical problem to be solved is to overcome the bottleneck of prior art, a kind of aerial so as to propose
Howitzer launch craft.
For solving above-mentioned technical problem, the invention discloses a kind of aerial grenade launcher aircraft, the aircraft bag
Include grenade launcher, body, shock absorption buffering mechanism；A body upper plate is provided with above the body, and lower section is provided with one
Body lower plate；The shock absorption buffering mechanism is arranged on the lower section of the body lower plate；
The grenade launcher includes gun body, gun barrel, and the gun body is set in outside the gun barrel；
The shock absorption buffering mechanism includes leader fixed, kicker, guide rod, front clip epivalve；Described leader fixed
It is fixed in the body lower plate；
The front clip epivalve threadeds fixation with the rear and front end of the guide rod, and the guide rod is solid through the guide rod
Reservation, direction are axially in parallel with the body；The kicker pass through the guide rod, be arranged on the front clip epivalve with described
Between fixed seat.
Preferably, the shock absorption buffering mechanism also includes front clip hypovalve, rear clip epivalve, rear clip hypovalve；Before described
Clip hypovalve is fastened with the front clip epivalve by bolt, so as to clamp the gun barrel；The rear clip hypovalve passes through spiral shell
Bolt is fastened with the rear clip epivalve, so as to clamp the gun barrel.
Preferably, a draw-in groove being engaged with the front clip hypovalve is additionally provided with the gun barrel.
Preferably, the grenade launcher is also roused comprising bullet, and bullet drum is arranged on above the gun barrel, and with the rifle
Body connects；In the middle of the body lower plate and body upper plate, the center of the bullet drum is in the body center to the bullet drum
Top.
Preferably, the bullet drum lower section is provided with an opening for casting shell case.The bullet drum is connected with gun body, peace
Be mounted in the centre of body lower plate and body upper plate, towards above body, so percussion when shell case shed downwards do not interfere with winged
The flight of row device.
Preferably, the body also includes electrokinetic cell, support arm, support arm rotary bending piece, support；
The support arm rotary bending piece is connected with the body lower plate, the body upper plate by bolt；The support arm with
The support arm rotary bending piece is connected by optical axis, and optical axis is parallel with vertical direction, and the support arm can be around the optical axis in vertically side
To being turned round；The support is connected with the body lower plate.
Preferably, the aircraft also includes percussion lock, the percussion lock comprising drive steering wheel, trigger shaft, connecting rod,
Steering wheel disk, percussion fixed seat；
The percussion fixed seat is connected by bolt with the gun body, and the steering wheel is connected in the percussion fixed seat；
The steering wheel disk is bolted with the steering wheel, and is connected by optical axis with the connecting rod；The trigger shaft and the company
Bar is connected by optical axis.
Preferably, parallel by the axis of bolt gun body and the body axis of aircraft.
Similar with common unmanned plane, the power set of this aircraft include electron speed regulator, motor, cable, screw,
Flight control assemblies etc..Battery is connected with upper cover plate by VELCRO, used as the power supply of full machine.The loop fastener structures of VELCRO make
Obtaining user can easily carry out dismounting and the installation of battery, when battery electric quantity reduces to a certain extent, can be straight by battery
Access down, once by can fix battery at the upper cover plate VELCRO after charging electricity.Electron speed regulator receives flight controller
Instruction after can control the size of current of flow direction motor, and then the rotating speed of controlled motor, so as to control flight.Add on lower cover
Work goes out some apertures, and electron speed regulator is arranged in the space between lower cover and upper cover plate, is fixed on lower cover by band.
Motor drives propeller rotational as last executing agency, is that full machine provides the power required for motion.Motor is solid by motor cabinet
It is associated on each carbon pipe support arm：Motor is fastened by bolts on motor cabinet, and motor cabinet is by four semicircular anchor ear fastenings
End in carbon pipe support arm.Cable laying between upper and lower cover plates and each carbon pipe support arm in, for transmitting electric current and control instruction.
The technique scheme of the present invention has advantages below compared to existing technology：The present invention will fold aircraft and howitzer
Transmitter is organically combined, and is easy to fold, is easy to dismounting, is the aerial fire support dress that soldier provides a kind of transport that is easy to carry
Put.By designing effective shock absorption buffering mechanism, can be very good to ensure fire accuracy.The aerial howitzer launch craft structure
Simply, the cost taken by themselves of the weapon device from moulding material, can effectively be reduced；With great using value.
Description of the drawings
In order that present disclosure is more likely to be clearly understood, the specific embodiment below according to the present invention is simultaneously combined
Accompanying drawing, the present invention is further detailed explanation, wherein
Fig. 1 is the general structure schematic diagram of aircraft described in embodiment 1；
Fig. 2 is the shock absorption buffering mechanism schematic diagram of aircraft described in embodiment 1；
Fig. 3 is the percussion lock schematic diagram of aircraft described in embodiment 1；
Fig. 4 is the percussion lock operating diagram of aircraft described in embodiment 1；
Fig. 5 is that the schematic diagram for moving back made backward by the grenade launcher of aircraft described in embodiment 1；
Fig. 6 be the grenade launcher of aircraft described in embodiment 1 answer forward into schematic diagram；
Fig. 7 is the schematic diagram of the folded state of aircraft described in embodiment 1；
Fig. 8 is the general structure schematic diagram of aircraft described in embodiment 2；
Fig. 9 is the schematic diagram of the folded state of aircraft described in embodiment 2.
Specific embodiment
Embodiment 1 as shown in Figure 1, 2, 3, present embodiment discloses a kind of aerial howitzer launch craft of six axle；It includes
Grenade launcher, body, shock absorption buffering mechanism, four part of percussion lock composition, wherein, grenade launcher includes gun body 15, rifle
Pipe 22, bullet drum 23；
Body comprising electrokinetic cell 1, support arm 2, support arm rotary bending piece 3, body lower plate 4, support 5, body supporting structure 6,
Body upper plate 7, rain visor 8；
Shock absorption buffering mechanism is comprising leader fixed 9, kicker 10, front clip epivalve 11, front clip hypovalve 12, guide rod
13rd, rear clip epivalve 14, rear clip hypovalve 21；
Percussion lock is comprising driving steering wheel 16, trigger shaft 17, connecting rod 18, steering wheel disk 19, percussion fixed seat 20.
A body upper plate 7 is provided with above the body, and lower section is provided with a body lower plate 4；The damping, buffering
Device is arranged on the lower section of the body lower plate 4；
The gun body 15 is set in outside the gun barrel 22, and bullet drum is arranged on 23 above the gun barrel, and with described
Gun body 15 connects；In the middle of the body lower plate 4 with body upper plate 7, the center of the bullet drum 23 is in institute to the bullet drum 23
State the top of body center.
23 lower section of the bullet drum is provided with an opening for casting shell case.The bullet drum 23 is connected with gun body 15, peace
The centre of body lower plate 4 and body upper plate 7 is mounted in, towards above body, shell case is shed downwards and do not interfered with so in percussion
The flight of aircraft.
The front clip hypovalve 12 is fastened with the front clip epivalve 11 by bolt, so as to clamp the gun barrel 22；
The rear clip hypovalve 21 is fastened with the rear clip epivalve 14 by bolt, so as to clamp the gun barrel 22；
Described leader fixed 9 are fixed in the body lower plate 4；The front clip epivalve 11, the rear clip epivalve
14 threaded fixation with the rear and front end of the guide rod 13, and the guide rod 13 passes through described leader fixed 9, direction with described
Body axially in parallel；The kicker 10 passes through the guide rod 13, is arranged on the front clip epivalve 12 solid with the guide rod
Between reservation 9.
A draw-in groove being engaged with the front clip hypovalve 12 is additionally provided with the gun barrel 22.
The support arm rotary bending piece 3 is connected with the body lower plate 4, the body upper plate 7 by bolt；The support arm
2 are connected by optical axis with the support arm rotary bending piece 3, and optical axis is parallel with vertical direction, and the support arm 2 can be around the optical axis perpendicular
Nogata is to being turned round；The support 5 is connected with the body lower plate 4.
The percussion fixed seat 20 is connected by bolt with the gun body 15, and the steering wheel 16 is connected in the percussion and fixes
On seat 20；The steering wheel disk 19 is bolted with the steering wheel 16, and is connected by optical axis with the connecting rod；The percussion
Bar 17 is connected by optical axis with the connecting rod 18.
As shown in Figure 4,5, after soldier confirms target, to one arming signal of grenade launcher, steering wheel 16 is driven to work,
Steering wheel disk 19 makes 17 cocking of trigger shaft by connecting rod 18, realizes percussion.Gun body 15, gun barrel 22, bullet drum 23 are in kick
Under effect, together to recoil, kicker 10 compresses storing energy, treats bullet drum 23 and body lower plate 4, the back edge of body upper plate 7
Back seat of colliding puts in place.Now, as shown in fig. 6, kicker 10 releases energy, gun body 15, gun barrel 22, bullet drum 23 are driven together forward
Enter again, treat that bullet drum 23 and the back edge of body lower plate 4, body upper plate 7 collide again to enter to put in place.
As shown in fig. 7, support arm 2 can be folded around the gyroaxis of support arm rotary bending piece 3, be made in transport by soldier
Obtain size to greatly reduce, the transporter beneficial to soldier is assembled, improve weapon and use flexibility.
As shown in Fig. 8,2,3, the invention discloses a kind of aerial howitzer launch craft of four axle, it includes pomegranate to embodiment 2
Ball emitter, multi-rotor aerocraft body, damping, buffering system, four part of trigger system composition, wherein, grenade launcher includes
Gun body 15, gun barrel 22, bullet drum 23, multi-rotor aerocraft body include electrokinetic cell 1, support arm 2, support arm rotary bending piece 3, body lower plate
4th, support 5, body supporting structure 6, body upper plate 7, rain visor 8, damping, buffering system is comprising leader fixed 9, kicker
10th, front clip epivalve 11, front clip hypovalve 12, guide rod 13, rear clip epivalve 14, rear clip hypovalve 21, trigger system is comprising drive
Dynamic steering wheel 16, trigger shaft 17, connecting rod 18, steering wheel disk 19, percussion fixed seat 20.
As shown in figure 4, after soldier confirms target, to one arming signal of grenade launcher, driving steering wheel 16 to work, rudder
Machine disk 19 passes through connecting rod 18, makes 17 cocking of trigger shaft, realizes percussion.Gun body 15, gun barrel 22, bullet drum 23 are in the work of kick
With under, together to recoil, kicker 10 compress storing energy, treat bullet drum 23 with body lower plate 4, the back edge phase of body upper plate 7
Touch back seat to put in place.Now, as shown in figure 5, kicker 10 releases energy, drive gun body 15, gun barrel 22, bullet drum 23 multiple forward together
Enter, treat that bullet drum 23 and the back edge of body lower plate 4, body upper plate 7 collide again to enter to put in place.
As shown in figure 9, support arm 2 can be folded around the gyroaxis of support arm rotary bending piece 3, be made in transport by soldier
Obtain size to greatly reduce, the transporter beneficial to soldier is assembled, improve weapon and use flexibility.
Obviously, above-described embodiment is only intended to clearly illustrate example, and the not restriction to embodiment.Right
For those of ordinary skill in the art, can also make on the basis of the above description other multi-forms change or
Change.There is no need to be exhaustive to all of embodiment.And the obvious change thus extended out or
Change among still in the protection domain of the invention.
Claims (8)
1. a kind of aerial grenade launcher aircraft, it is characterised in that the aircraft includes grenade launcher, body, damping
Buffer unit；A body upper plate is provided with above the body, and lower section is provided with a body lower plate；The damping, buffering dress
Put the lower section for being arranged on the body lower plate；
The grenade launcher includes gun body, gun barrel, and the gun body is set in outside the gun barrel；
The shock absorption buffering mechanism includes leader fixed, kicker, guide rod, front clip epivalve；The leader fixed fixation
In the body lower plate；
The front clip epivalve threadeds fixation with the rear and front end of the guide rod, and the guide rod is fixed through the guide rod
Seat, direction are axially in parallel with the body；The kicker passes through the guide rod, is arranged on the front clip epivalve solid with described
Between reservation.
2. aircraft according to claim 1, it is characterised in that the shock absorption buffering mechanism also comprising front clip hypovalve, after
Clip epivalve, rear clip hypovalve；The front clip hypovalve is fastened by bolt and the front clip epivalve, so as to by the gun barrel
Clamping；The rear clip hypovalve is fastened with the rear clip epivalve by bolt, so as to clamp the gun barrel.
3. aircraft according to claim 2, it is characterised in that be additionally provided with the gun barrel one with the front clip under
The draw-in groove of lobe occlusion.
4. aircraft according to claim 3, it is characterised in that the grenade launcher is also roused comprising bullet, and the bullet drum sets
Put above the gun barrel, and be connected with the gun body；The bullet drum is in the middle of the body lower plate and body upper plate, described
Top of the center of bullet drum in the body center.
5. aircraft according to claim 4, it is characterised in that the bullet drum lower section is provided with for casting shell case
Opening.
6. aircraft according to claim 5, it is characterised in that the body is also comprising electrokinetic cell, support arm, support arm turnover
Part, support；
The support arm rotary bending piece is connected with the body lower plate, the body upper plate by bolt；The support arm with described
Support arm rotary bending piece is connected by optical axis, and optical axis is parallel with vertical direction, and the support arm can enter around the optical axis in vertical direction
Row revolution；The support is connected with the body lower plate.
7. aircraft according to claim 6, it is characterised in that the aircraft also includes percussion lock, the percussion dress
Put comprising driving steering wheel, trigger shaft, connecting rod, steering wheel disk, percussion fixed seat；
The percussion fixed seat is connected by bolt with the gun body, and the steering wheel is connected in the percussion fixed seat；Described
Steering wheel disk is bolted with the steering wheel, and is connected by optical axis with the connecting rod；The trigger shaft is logical with the connecting rod
Cross optical axis connection.
8. aircraft according to claim 7, it is characterised in that the axis of the gun body is put down with the body axis of aircraft
OK.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611046827.1A CN106477047B (en) | 2016-11-23 | 2016-11-23 | A kind of aerial howitzer launch craft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611046827.1A CN106477047B (en) | 2016-11-23 | 2016-11-23 | A kind of aerial howitzer launch craft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106477047A true CN106477047A (en) | 2017-03-08 |
| CN106477047B CN106477047B (en) | 2018-07-27 |
Family
ID=58274309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611046827.1A Expired - Fee Related CN106477047B (en) | 2016-11-23 | 2016-11-23 | A kind of aerial howitzer launch craft |
Country Status (1)
| Country | Link |
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| CN (1) | CN106477047B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107021224A (en) * | 2017-04-28 | 2017-08-08 | 深圳市轻准科技有限公司 | Hang down and throw howitzer unmanned plane |
| CN107380451A (en) * | 2017-09-01 | 2017-11-24 | 牟正芳 | A kind of rotor armed drones |
| CN107543449A (en) * | 2017-09-14 | 2018-01-05 | 牟正芳 | A kind of rotor armed drones for carrying automatic grenade launcher |
| CN107588679A (en) * | 2017-10-27 | 2018-01-16 | 牟正芳 | A kind of land and air double-used automatic grenade launcher |
| CN107702593A (en) * | 2017-09-14 | 2018-02-16 | 牟正芳 | A kind of automatic fire control system of rotor armed drones |
| CN108327897A (en) * | 2018-03-09 | 2018-07-27 | 深圳市轻准科技有限公司 | Equip with arms unmanned helicopter |
| CN108423188A (en) * | 2018-05-15 | 2018-08-21 | 南京理工大学 | A kind of unmanned plane cradle head mechanism of carry firearms |
| CN108945462A (en) * | 2018-06-11 | 2018-12-07 | 易瓦特科技股份公司 | Power load-bearing emitter for unmanned plane |
| WO2019061775A1 (en) * | 2017-09-30 | 2019-04-04 | 深圳市大疆创新科技有限公司 | Vibration isolation mechanism and shooting robot having vibration isolation function |
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| US6286411B1 (en) * | 1999-02-16 | 2001-09-11 | Paul H. Sanderson | Apparatus for operatively supporting a machine gun |
| CN202508282U (en) * | 2011-12-31 | 2012-10-31 | 李墉 | Helicopter with guided missiles |
| CN205098467U (en) * | 2015-10-20 | 2016-03-23 | 黄耀辉 | Arms unmanned aerial vehicle |
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| CN206235241U (en) * | 2016-11-23 | 2017-06-09 | 深圳市轻准科技有限公司 | A kind of aerial howitzer launch craft |
| CN206634214U (en) * | 2016-11-23 | 2017-11-14 | 深圳市轻准科技有限公司 | A kind of aerial howitzer launch craft |
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2016
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| US6286411B1 (en) * | 1999-02-16 | 2001-09-11 | Paul H. Sanderson | Apparatus for operatively supporting a machine gun |
| CN202508282U (en) * | 2011-12-31 | 2012-10-31 | 李墉 | Helicopter with guided missiles |
| US20160214713A1 (en) * | 2014-12-19 | 2016-07-28 | Brandon Cragg | Unmanned aerial vehicle with lights, audio and video |
| CN205098467U (en) * | 2015-10-20 | 2016-03-23 | 黄耀辉 | Arms unmanned aerial vehicle |
| CN206235241U (en) * | 2016-11-23 | 2017-06-09 | 深圳市轻准科技有限公司 | A kind of aerial howitzer launch craft |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107021224A (en) * | 2017-04-28 | 2017-08-08 | 深圳市轻准科技有限公司 | Hang down and throw howitzer unmanned plane |
| CN107380451A (en) * | 2017-09-01 | 2017-11-24 | 牟正芳 | A kind of rotor armed drones |
| CN107543449A (en) * | 2017-09-14 | 2018-01-05 | 牟正芳 | A kind of rotor armed drones for carrying automatic grenade launcher |
| CN107702593A (en) * | 2017-09-14 | 2018-02-16 | 牟正芳 | A kind of automatic fire control system of rotor armed drones |
| WO2019061775A1 (en) * | 2017-09-30 | 2019-04-04 | 深圳市大疆创新科技有限公司 | Vibration isolation mechanism and shooting robot having vibration isolation function |
| CN109937314B (en) * | 2017-09-30 | 2021-12-03 | 深圳市大疆创新科技有限公司 | Vibration isolation mechanism and shooting robot with vibration isolation function |
| CN109937314A (en) * | 2017-09-30 | 2019-06-25 | 深圳市大疆创新科技有限公司 | Vibration isolating mechanism, the shooting robot with vibration isolation function |
| CN107588679A (en) * | 2017-10-27 | 2018-01-16 | 牟正芳 | A kind of land and air double-used automatic grenade launcher |
| CN108327897A (en) * | 2018-03-09 | 2018-07-27 | 深圳市轻准科技有限公司 | Equip with arms unmanned helicopter |
| CN108423188A (en) * | 2018-05-15 | 2018-08-21 | 南京理工大学 | A kind of unmanned plane cradle head mechanism of carry firearms |
| CN108423188B (en) * | 2018-05-15 | 2024-05-17 | 南京理工大学 | Unmanned aerial vehicle cloud deck mechanism for mounting firearms |
| CN108945462A (en) * | 2018-06-11 | 2018-12-07 | 易瓦特科技股份公司 | Power load-bearing emitter for unmanned plane |
| CN108945462B (en) * | 2018-06-11 | 2021-05-28 | 易瓦特科技股份公司 | A power bearing emitter for unmanned aerial vehicle |
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| Publication number | Publication date |
|---|---|
| CN106477047B (en) | 2018-07-27 |
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