CN206235241U - A kind of aerial howitzer launch craft - Google Patents
A kind of aerial howitzer launch craft Download PDFInfo
- Publication number
- CN206235241U CN206235241U CN201621268388.4U CN201621268388U CN206235241U CN 206235241 U CN206235241 U CN 206235241U CN 201621268388 U CN201621268388 U CN 201621268388U CN 206235241 U CN206235241 U CN 206235241U
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- gun
- lower plate
- epivalve
- clip
- gun barrel
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Abstract
The utility model belongs to aircraft manufacture field, and in particular to a kind of aerial howitzer launch craft.The aircraft includes body, shock absorption buffering mechanism, grenade launcher；Body top is provided with a body upper plate, and lower section is provided with a body lower plate；Shock absorption buffering mechanism is arranged on the lower section of the body lower plate；The grenade launcher includes gun body, gun barrel, bullet drum, and the gun body is set in outside the gun barrel, and the bullet drum is arranged on the gun barrel top, and is connected with the gun body；In the middle of the body lower plate and body upper plate, the center of the bullet drum is in the top of the body center to the bullet drum.The bullet drum is connected with gun body, and installed in body lower plate and the centre of body upper plate, towards body top, so in percussion, shell case sheds downwards the flight for not interfering with aircraft.The aerial howitzer launch craft simple structure, from moulding material, can effectively reduce the cost taken by themselves of the weapon device, with 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 rising
Unique flight function such as drop, hovering and motor-driven avoidance, can more preferably complete aerial mission in less space.
But, it is current in the prior art, but few people combine grenade launcher and rotor craft, give full play to
Rotor craft landing requirement is 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 grenade launcher, it includes grenade launcher, machine
Body, shock absorption buffering mechanism, the part of percussion lock four composition, wherein, grenade launcher includes gun body, gun barrel, bullet drum, and body is included
Electrokinetic cell, support arm, support arm rotary bending piece, body lower plate, support, body supporting structure, body upper plate, rain visor, damping are delayed
Flushing device includes leader fixed, kicker, preceding clip epivalve, preceding clip hypovalve, guide rod, rear clip epivalve, rear clip hypovalve,
Percussion lock includes driving steering wheel, trigger shaft, connecting rod, steering wheel disk, percussion fixed seat.
Preferably, the preceding clip hypovalve is engaged with the draw-in groove of gun barrel, is clamped gun barrel with preceding clip epivalve by bolt,
Clip hypovalve is clamped gun barrel with rear clip epivalve by bolt afterwards, and the axis of gun body is parallel with the body axis of aircraft.Institute
State bullet drum to be connected with gun body, installed in body lower plate and the centre of body upper plate, towards body top, the shell case so in percussion
Shed the flight for not interfering with aircraft downwards.
Preferably, the body lower plate and body upper plate, fixation is bolted with body supporting structure.The branch
Arm rotary bending piece is connected by bolt with body lower plate, body upper plate.The support arm is connected with support arm rotary bending piece by optical axis,
Optical axis is parallel with vertical direction, and support arm can be turned round around optical axis in vertical direction.The support passes through with body lower plate
Connection, and it is easy to dismounting.The electrokinetic cell is connected by VELCRO, band and body lower plate with body upper plate.
Preferably, the shock absorption buffering mechanism is fixed in the body lower plate of body by leader fixed.Card before described
Hoop epivalve, rear clip epivalve are threadedly coupled fixation with the rear and front end of guide rod, and guide rod passes through leader fixed, direction and axis
To parallel.The kicker passes through guide rail, between preceding clip epivalve and fixed seat.
It is more highly preferred to, the percussion fixed seat is fixed together with gun body by bolt, and steering wheel is connected in percussion and fixes
On seat.The steering wheel disk is bolted with steering wheel, and is connected by optical axis with connecting rod.The trigger shaft passes through light with connecting rod
Axle is connected.
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, used as the power supply of full machine.The loop fastener structures of VELCRO make
Obtaining user can easily carry out the dismounting and installation of battery, when battery electric quantity is reduced to a certain extent, can be straight by battery
Access down, charge after electricity at upper cover plate VELCRO once by can fix battery.Electron speed regulator receives flight controller
Instruction after can control the size of current of flow direction motor, and then controlled motor rotating speed, 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.Electricity
Machine drives propeller rotational as last executing agency, the power required for providing motion for full machine.Motor is connected 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 between upper and lower cover plates and each carbon pipe support arm in, for transmitting electric current and control instruction.
Above-mentioned technical proposal of the present utility model has advantages below compared to existing technology：Flight described in the utility model
The bullet drum of device is connected with gun body, installed in body lower plate and the centre of body upper plate, towards body top, so in percussion
When shell case shed the flight for not interfering with aircraft downwards.The aerial howitzer launch craft simple structure, from moulding material,
The cost taken by themselves of the weapon device can effectively be reduced；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, the utility model is described in further detail, 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 for moving back backward；
Fig. 6 be aircraft described in embodiment 1 grenade launcher 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, the part of percussion lock four composition, wherein, grenade launcher includes gun body 21, 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 includes leader fixed 9, kicker 10, preceding clip epivalve 11, preceding clip hypovalve 12, guide rod
13rd, rear clip epivalve 14, rear clip hypovalve 15；
Percussion lock includes driving steering wheel 16, trigger shaft 17, connecting rod 18, steering wheel disk 19, percussion fixed seat 20.
The body top is provided with a body upper plate 7, 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 grenade launcher includes gun body 21, gun barrel 22, bullet drum 23, the gun body
21 are set in outside the gun barrel 22, and the bullet drum 23 is arranged on the top of the gun barrel 22, and is connected with the gun body 21；It is described
In the middle of the body lower plate 4 with body upper plate 7, the center of the bullet drum 23 is in the upper of the body center to bullet drum 23
Side.
The lower section of the bullet drum 23 is provided with an opening for casting shell case.
The preceding clip hypovalve 12 is fastened by bolt with the preceding clip epivalve 11, so as to the gun barrel 22 be clamped；
The rear clip hypovalve 15 is fastened by bolt with the rear clip epivalve 14, so as to 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 the fixed seat of the guide rod 13, direction and institute
State body axially in parallel；The kicker 10 is sheathed on outside the guide rod 13, be arranged on the preceding clip epivalve 12 with it is described
Between fixed seat 9.
A draw-in groove being engaged with the preceding clip hypovalve is additionally provided with the gun barrel 22.
The support arm rotary bending piece 3 is connected by bolt with 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 21 by bolt, 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 with the connecting rod 18 by optical axis.
As shown in Figure 4,5, after soldier confirms target, give grenade launcher one arming signal, drive steering wheel 16 to work,
Steering wheel disk 19 makes the cocking of trigger shaft 17 by connecting rod 18, realizes percussion.Gun body 21, gun barrel 22, bullet drum 23 are in kick
Under effect, together to recoil, the compression storing energy of kicker 10 treats bullet drum 23 and body lower plate 4, the back edge of body upper plate 7
Back seat collide in place.Now, as shown in fig. 6, kicker 10 releases energy, gun body 21, gun barrel 22, bullet drum 23 are driven together forward
Enter again, treat that bullet drum 23 is collided with body lower plate 4, the back edge of body upper plate 7 and enter again in place.
As shown in fig. 7, soldier is in transport, gyroaxis that can be by support arm 2 around support arm rotary bending piece 3 is folded, and is made
Obtain size to greatly reduce, beneficial to the transporter assembling of soldier, improve weapon and use flexibility.
As shown in Fig. 8,2,3, the utility model discloses a kind of aerial howitzer launch craft of four axle, it is wrapped embodiment 2
Grenade launcher, multi-rotor aerocraft body, shock absorption buffering mechanism, the part of percussion lock four composition are included, wherein, grenade launcher
Comprising gun body 21, gun barrel 22, bullet drum 23；
Aircraft body includes electrokinetic cell 1, support arm 2, support arm rotary bending piece 3, body lower plate 4, support 5, body support knot
Component 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 15；
Percussion lock includes driving steering wheel 16, trigger shaft 17, connecting rod 18, steering wheel disk 19, percussion fixed seat 20.
The body top is provided with a body upper plate 7, 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 grenade launcher includes gun body 21, gun barrel 22, bullet drum 23, the gun body
21 are set in outside the gun barrel 22, and the bullet drum 23 is arranged on the gun barrel top, and is connected with the gun body 21；The bullet
In the middle of the body lower plate 4 with body upper plate 7, the center of the bullet drum 23 is in the top of the body center to drum 23.
The lower section of the bullet drum 23 is provided with an opening for casting shell case.
The preceding clip hypovalve 12 is fastened by bolt with the preceding clip epivalve 11, so as to the gun barrel 22 be clamped；
The rear clip hypovalve 15 is fastened by bolt with the rear clip epivalve 14, so as to 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 the fixed seat of the guide rod 13, direction and institute
State body axially in parallel；The kicker 10 pass through the guide rail, be arranged on the preceding clip epivalve 12 and the fixed seat 9 it
Between.
A draw-in groove being engaged with the preceding clip hypovalve is additionally provided with the gun barrel 22.
The support arm rotary bending piece 3 is connected by bolt with 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 21 by bolt, 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 with the connecting rod 18 by optical axis.
As shown in figure 4, after soldier's confirmation target, giving grenade launcher one arming signal, steering wheel 16 is driven to work, rudder
Machine disk 19 makes the cocking of trigger shaft 17 by connecting rod 18, realizes percussion.The work of gun body 21, gun barrel 22, bullet drum 23 in kick
Under, together to recoil, the compression storing energy of kicker 10 treats bullet drum 23 with body lower plate 4, the back edge phase of body upper plate 7
Touch back seat in place.Now, as shown in figure 5, kicker 10 releases energy, drive gun body 21, gun barrel 22, bullet drum 23 multiple forward together
Enter, treat that bullet drum 23 is collided with body lower plate 4, the back edge of body upper plate 7 and enter again in place.
As shown in figure 9, soldier is in transport, gyroaxis that can be by support arm 2 around support arm rotary bending piece 3 is folded, and is made
Obtain size to greatly reduce, beneficial to the transporter assembling of soldier, improve weapon and use flexibility.
Obviously, above-described embodiment is only intended to clearly illustrate example, and not to the restriction of implementation method.It is 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 and unable to be exhaustive to all of implementation method.And the obvious change thus extended out or
Among the protection domain that variation is created still in the utility model.
Claims (7)
1. a kind of aerial grenade launcher aircraft, it is characterised in that the aircraft includes body, shock absorption buffering mechanism, pomegranate
Ball emitter；
The body top is provided with a body upper plate, and lower section is provided with a 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, bullet drum, and the gun body is set in outside the gun barrel, and the bullet drum is set
Above the gun barrel, and it is connected with the gun body；
In the middle of the body lower plate and body upper plate, the center of the bullet drum is in the upper of the body center to the bullet drum
Side.
2. aircraft according to claim 1, it is characterised in that the bullet drum lower section is provided with for casting shell case
Opening.
3. aircraft according to claim 2, it is characterised in that the shock absorption buffering mechanism includes preceding clip epivalve, preceding card
Hoop hypovalve, rear clip epivalve, rear clip hypovalve；The preceding clip hypovalve is fastened by bolt with the preceding clip epivalve, so that
The gun barrel is clamped；The rear clip hypovalve is fastened by bolt with the rear clip epivalve, so as to the gun barrel be clamped.
4. aircraft according to claim 3, it is characterised in that the shock absorption buffering mechanism is also comprising leader fixed, multiple
Enter spring, guide rod；It is described leader fixed to be fixed in the body lower plate；The preceding clip epivalve, the rear clip epivalve with
The rear and front end threaded connection of the guide rod is fixed, the guide rod through described leader fixed, direction and the body axial direction
It is parallel；The kicker passes through the guide rail, is arranged between the preceding clip epivalve and the fixed seat.
5. aircraft according to claim 4, it is characterised in that be additionally provided with the gun barrel one with the preceding clip under
The draw-in groove of valve occlusion.
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 with 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 by optical axis with the connecting rod；The trigger shaft is logical with the connecting rod
Cross optical axis connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621268388.4U CN206235241U (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 |
|---|---|---|---|
| CN201621268388.4U CN206235241U (en) | 2016-11-23 | 2016-11-23 | A kind of aerial howitzer launch craft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206235241U true CN206235241U (en) | 2017-06-09 |
Family
ID=58980930
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621268388.4U Active CN206235241U (en) | 2016-11-23 | 2016-11-23 | A kind of aerial howitzer launch craft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206235241U (en) |
Cited By (2)
| 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 |
| CN108195227A (en) * | 2018-03-14 | 2018-06-22 | 南京理工大学 | A kind of gun clamping device with spring bumper for being assemblied in unmanned plane |
-
2016
- 2016-11-23 CN CN201621268388.4U patent/CN206235241U/en active Active
Cited By (3)
| 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 |
| CN108195227A (en) * | 2018-03-14 | 2018-06-22 | 南京理工大学 | A kind of gun clamping device with spring bumper for being assemblied in unmanned plane |
| CN108195227B (en) * | 2018-03-14 | 2023-07-28 | 南京理工大学 | Gun clamping mechanism with spring buffer device assembled on unmanned aerial vehicle |
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