CN206634214U - A kind of aerial howitzer launch craft - Google Patents
A kind of aerial howitzer launch craft Download PDFInfo
- Publication number
- CN206634214U CN206634214U CN201621268124.9U CN201621268124U CN206634214U CN 206634214 U CN206634214 U CN 206634214U CN 201621268124 U CN201621268124 U CN 201621268124U CN 206634214 U CN206634214 U CN 206634214U
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- China
- Prior art keywords
- clip
- support arm
- epivalve
- gun
- aircraft
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- 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.)
- Expired - Fee Related
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- 230000003139 buffering effect Effects 0.000 claims abstract description 15
- 238000010521 absorption reaction Methods 0.000 claims abstract description 12
- 230000035939 shock Effects 0.000 claims abstract description 12
- 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 4
- 230000001934 delay Effects 0.000 claims 1
- 238000011010 flushing procedure Methods 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 230000007306 turnover Effects 0.000 claims 1
- 238000010276 construction Methods 0.000 abstract description 2
- 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
- 230000005611 electricity Effects 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
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 210000005069 ears Anatomy 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The utility model belongs to aircraft manufacture field, and in particular to a kind of aerial howitzer launch craft.The utility model will fold aircraft and be organically combined with grenade launcher, be easy to fold, be easy to dismount, a kind of aerial fire support device for the transport that is easy to carry is provided for soldier.By designing effective shock absorption buffering mechanism, can be very good to ensure fire accuracy.The aerial howitzer launch craft is simple in construction, from moulding material, can effectively reduce the cost taken by themselves of the weapon device, have great application value.
Description
Technical field
The utility model 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 rise
Unique flight functions such as drop, hovering and motor-driven avoidance, can more preferably complete aerial mission in less space.
But at present in the prior art, but few people combine grenade launcher and rotor craft, give full play to
Rotor craft landing requires low, individual soldier's firepower of soldier is greatly improved, there is provided aerial fire support.
Utility model content
Therefore, technical problem to be solved in the utility model is the bottleneck for overcoming prior art, so as to propose one kind
Aerial howitzer launch craft.
In order to solve the above technical problems, the utility model discloses a kind of aerial grenade launcher aircraft, the flight
Device includes grenade launcher, body, shock absorption buffering mechanism；A body upper plate is provided with above the body, 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, preceding clip epivalve；It is described leader fixed
It is fixed in the body lower plate；
The preceding clip epivalve is threadedly coupled fixation with the rear and front end of the guide rod, and the guide rod is consolidated through the guide rod
Reservation, direction and the body are axially in parallel；The kicker passes through the guide rod, be arranged on the preceding clip epivalve with it is described
Between fixed seat.
Preferably, the shock absorption buffering mechanism is also comprising preceding clip hypovalve, rear clip epivalve, rear clip hypovalve；Before described
Clip hypovalve is fastened by bolt and the preceding clip epivalve, so as to which the gun barrel be clamped；Clip hypovalve passes through spiral shell after described
Bolt fastens with the rear clip epivalve, so as to which the gun barrel be clamped.
Preferably, a neck being engaged with the preceding 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；For the bullet drum among the body lower plate and body upper plate, the center of the bullet drum is in the body center
Top.
Preferably, the bullet drum lower section is provided with an opening for being used to cast shell case.The bullet drum is connected with gun body, is pacified
Mounted in body lower plate and the centre of body upper plate, towards body above, so in percussion shell case shed downwards do not interfere with it is winged
The flight of row device.
Preferably, the body is also comprising electrokinetic cell, support arm, support arm rotary bending piece, support；
The support arm rotary bending piece is connected by bolt and the body lower plate, the body upper plate；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 vertical side
To being turned round；The support is connected with the body lower plate.
Preferably, the aircraft also includes percussion lock, the percussion lock include driving steering wheel, trigger shaft, connecting rod,
Steering wheel disk, percussion fixed seat；
The percussion fixed seat is connected with the gun body by bolt, and the steering wheel is connected in the percussion fixed seat；
The steering wheel disk is bolted with the steering wheel, and is connected with the connecting rod by optical axis；The trigger shaft and the company
Bar is connected by optical axis.
Preferably, it is parallel by the axis of bolt gun body and the body axis of aircraft.
It is similar with common unmanned plane, the power set of this aircraft include electron speed regulator, motor, cable, propeller,
Flight control assemblies etc..Battery is connected by VELCRO with upper cover plate, the power supply as full machine.The loop fastener structures of VELCRO make
The disassembly and installation of battery can easily be carried out by obtaining user, can be straight by battery when battery electric quantity reduces to a certain extent
Access down, charge after electricity at upper cover plate VELCRO one and fix battery by can.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 by band on lower cover.Electricity
Machine drives propeller rotational, the power required for motion is provided for full machine as last executing agency.Motor connects firmly by motor cabinet
On each carbon pipe support arm：Motor is fastened by bolts on motor cabinet, and motor cabinet is fastened on by four semicircular anchor ears
The end of carbon pipe support arm.Cable laying is between upper and lower cover plates and in each carbon pipe support arm, for transmitting electric current and control instruction.
Above-mentioned technical proposal of the present utility model has advantages below compared with prior art：The utility model will be folded and flown
Device organically combines with grenade launcher, is easy to fold, is easy to dismount, a kind of air fire for the transport that is easy to carry is provided for soldier
Assisting system.By designing effective shock absorption buffering mechanism, can be very good to ensure fire accuracy.The aerial howitzer transmitting flight
Device is simple in construction, from moulding material, can effectively reduce the cost taken by themselves of the weapon device；With great application value.
Brief description of the drawings
In order that content of the present utility model is more likely to be clearly understood, below according to specific implementation of the present utility model
Example and with reference to accompanying drawing, is described in further detail to the utility model, 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 grenade launcher of aircraft described in embodiment 1 makes the schematic diagram moved back backward；
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.
Embodiment
As shown in Figure 1, 2, 3, present embodiment discloses a kind of aerial howitzer launch craft of six axles for embodiment 1；It includes
Grenade launcher, body, shock absorption buffering mechanism, the part of percussion lock four composition, wherein, grenade launcher includes gun body 15, rifle
Pipe 22, bullet drum 23；
Body include 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 includes leader fixed 9, kicker 10, preceding clip epivalve 11, preceding clip hypovalve 12, guide rod
13rd, rear clip epivalve 14, rear clip hypovalve 21；
Percussion lock includes 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, 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 it is described
Gun body 15 connects；For the bullet drum 23 among the body lower plate 4 and body upper plate 7, the center of the bullet drum 23 is in institute
State the top of body center.
The lower section of bullet drum 23 is provided with an opening for being used to cast shell case.The bullet drum 23 is connected with gun body 15, peace
Mounted in body lower plate 4 and the centre of body upper plate 7, towards body top, shell case, which is shed downwards, so in percussion does not interfere with
The flight of aircraft.
The preceding clip hypovalve 12 is fastened by bolt and the preceding clip epivalve 11, so as to which the gun barrel 22 be clamped；
Clip hypovalve 21 is fastened by bolt and the rear clip epivalve 14 after described, so as to which the gun barrel 22 be clamped；
Described leader fixed 9 are fixed in the body lower plate 4；The preceding clip epivalve 11, the rear clip epivalve
14 are threadedly coupled 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 it is described
Body it is axially in parallel；The kicker 10 passes through the guide rod 13, is arranged on the preceding clip epivalve 12 and consolidates with the guide rod
Between reservation 9.
A neck being engaged with the preceding clip hypovalve 12 is additionally provided with the gun barrel 22.
The support arm rotary bending piece 3 is connected by bolt and the body lower plate 4, the body upper plate 7；The support arm
2 are connected with the support arm rotary bending piece 3 by optical axis, 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 with the gun body 15 by bolt, and the steering wheel 16 is connected in the percussion and fixed
On seat 20；The steering wheel disk 19 is bolted with the steering wheel 16, and is connected with the connecting rod by optical axis；The percussion
Bar 17 is connected with the connecting rod 18 by optical axis.
As shown in Figure 4,5, after soldier confirms target, give grenade launcher one arming signal, driving steering wheel 16 works,
Steering wheel disk 19 makes the cocking of trigger shaft 17 by connecting rod 18, realizes percussion.Gun body 15, gun barrel 22, bullet drum 23 are in kick
Under effect, storing energy is compressed, treats bullet drum 23 and body lower plate 4, the back edge of body upper plate 7 to recoil, kicker 10 together
Back seat collide 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 collides again to enter in place with body lower plate 4, the back edge of body upper plate 7.
As shown in fig. 7, gyroaxis of the support arm 2 around support arm rotary bending piece 3 can be folded, made in transport by soldier
Obtain size to greatly reduce, assembled beneficial to the transporter of soldier, improve weapon using flexible.
Embodiment 2 is as shown in Fig. 8,2,3, and the utility model discloses a kind of aerial howitzer launch craft of four axles, and it is wrapped
Grenade launcher, multi-rotor aerocraft body, damping, buffering system, the part of trigger system four composition are included, wherein, grenade launcher
Comprising gun body 15, gun barrel 22, bullet drum 23, multi-rotor aerocraft body includes 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, damping, buffering system include leader fixed 9, answered
Enter spring 10, preceding clip epivalve 11, preceding clip hypovalve 12, guide rod 13, rear clip epivalve 14, rear clip hypovalve 21, trigger system bag
The steering wheel 16 containing driving, trigger shaft 17, connecting rod 18, steering wheel disk 19, percussion fixed seat 20.
As shown in figure 4, after soldier confirms target, give grenade launcher one arming signal, driving steering wheel 16 works, rudder
Machine disk 19 makes the cocking of trigger shaft 17, realizes percussion by connecting rod 18.Gun body 15, gun barrel 22, bullet drum 23 kick work
Under, storing energy is compressed, treats bullet drum 23 and body lower plate 4, the back edge phase of body upper plate 7 to recoil, kicker 10 together
Touch back seat 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 collides again to enter in place with body lower plate 4, the back edge of body upper plate 7.
As shown in figure 9, gyroaxis of the support arm 2 around support arm rotary bending piece 3 can be folded, made in transport by soldier
Obtain size to greatly reduce, assembled beneficial to the transporter of soldier, improve weapon using flexible.
Obviously, above-described embodiment is only intended to clearly illustrate example, and is not the restriction to embodiment.It is right
For those of ordinary skill in the art, can also make on the basis of the above description it is other it is various forms of change or
Change.There is no necessity and possibility to exhaust all the enbodiments.And the obvious change thus extended out or
Among the protection domain that variation is created still in the utility model.
Claims (8)
1. a kind of aerial howitzer launch craft, it is characterised in that the aircraft delays including grenade launcher, body, damping
Flushing device；A body upper plate is provided with above the body, lower section is provided with a body lower plate；The shock absorption buffering mechanism
It 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, preceding clip epivalve；The leader fixed fixation
In the body lower plate；
The preceding clip epivalve is threadedly coupled fixation with the rear and front end of the guide rod, and the guide rod is fixed through the guide rod
Seat, direction and the body are axially in parallel；The kicker passes through the guide rod, be arranged on the preceding clip epivalve with it is described solid
Between reservation.
2. aircraft according to claim 1, it is characterised in that the shock absorption buffering mechanism also comprising preceding clip hypovalve, after
Clip epivalve, rear clip hypovalve；The preceding clip hypovalve is fastened by bolt and the preceding clip epivalve, so as to by the gun barrel
Clamp；Clip hypovalve is fastened by bolt and the rear clip epivalve after described, so as to which the gun barrel be clamped.
3. aircraft according to claim 2, it is characterised in that be additionally provided with the gun barrel under one and the preceding clip
The neck of valve occlusion.
4. aircraft according to claim 3, it is characterised in that the grenade launcher is also roused comprising bullet, and the bullet drum is set
Put above the gun barrel, and be connected with the gun body；The bullet drum is described among the body lower plate and body upper plate
The center of bullet drum is in the top of the body center.
5. aircraft according to claim 4, it is characterised in that the bullet drum lower section is provided with one and is used to cast 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 by bolt and the body lower plate, the body upper plate；The support arm with it is 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 with the gun body by bolt, and the steering wheel is connected in the percussion fixed seat；It is described
Steering wheel disk is bolted with the steering wheel, and is connected with the connecting rod by optical axis；The trigger shaft leads to the connecting rod
Cross optical axis connection.
8. aircraft according to claim 7, it is characterised in that the axis of the gun body and the body axis of aircraft are put down
OK.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621268124.9U CN206634214U (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 |
|---|---|---|---|
| CN201621268124.9U CN206634214U (en) | 2016-11-23 | 2016-11-23 | A kind of aerial howitzer launch craft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206634214U true CN206634214U (en) | 2017-11-14 |
Family
ID=60261590
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621268124.9U Expired - Fee Related CN206634214U (en) | 2016-11-23 | 2016-11-23 | A kind of aerial howitzer launch craft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206634214U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106477047A (en) * | 2016-11-23 | 2017-03-08 | 深圳市轻准科技有限公司 | A kind of aerial howitzer launch craft |
-
2016
- 2016-11-23 CN CN201621268124.9U patent/CN206634214U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106477047A (en) * | 2016-11-23 | 2017-03-08 | 深圳市轻准科技有限公司 | A kind of aerial howitzer launch craft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171114 |