CN106477047B - A kind of aerial howitzer launch craft - Google Patents
A kind of aerial howitzer launch craft Download PDFInfo
- Publication number
- CN106477047B CN106477047B CN201611046827.1A CN201611046827A CN106477047B CN 106477047 B CN106477047 B CN 106477047B CN 201611046827 A CN201611046827 A CN 201611046827A CN 106477047 B CN106477047 B CN 106477047B
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- China
- Prior art keywords
- clip
- support arm
- epivalve
- gun
- aircraft
- 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.)
- 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
- 238000005266 casting Methods 0.000 claims description 3
- 238000011010 flushing procedure Methods 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
- 239000007787 solid Substances 0.000 description 3
- 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
- 230000005540 biological transmission Effects 0.000 description 1
- 210000005069 ears Anatomy 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 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; Bombs 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 fields, and in particular to a kind of aerial howitzer launch craft.The present invention will fold aircraft and be organically combined with grenade launcher, and convenient for folding, being easy to dismount, a kind of aerial fire support device of transport 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 structure, selects moulding material, can effectively reduce the own cost of the weapon device, has great application value.
Description
Technical field
The invention belongs to aircraft manufacture fields, and in particular to a kind of aerial howitzer launch craft.
Background technology
Rotor craft is a kind of structure novel, the course of new aircraft that manipulation is simple, stability is high, it has vertical rise
Unique flight function such as drop, hovering and motor-driven avoidance, can more preferably complete aerial mission in a smaller space.
But at present in the prior art, but few people combine grenade launcher and rotor craft, give full play to
Rotor craft landing requirement is low, and individual soldier's firepower of soldier is greatly improved, provides aerial fire support.
Invention content
For this purpose, technical problem to be solved by the present invention lies in the bottleneck for overcoming the prior art, it is a kind of aerial to propose
Howitzer launch craft.
In order to solve the above technical problems, the invention discloses a kind of aerial grenade launcher aircraft, the aircraft packet
Include grenade launcher, body, shock absorption buffering mechanism；There are one body upper plates for setting above the body, and there are one lower section settings
Body lower plate；The shock absorption buffering mechanism is arranged in 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 solid across the guide rod
Reservation, direction and the body are axially parallel；The kicker pass through the guide rod, setting the preceding clip epivalve with it is described
Between fixed seat.
Preferably, the shock absorption buffering mechanism also includes preceding clip hypovalve, rear clip epivalve, rear clip hypovalve；Before described
Clip hypovalve is fastened by bolt and the preceding clip epivalve, to clamp the gun barrel；Clip hypovalve passes through spiral shell after described
Bolt is fastened with the rear clip epivalve, to clamp the gun barrel.
Preferably, a card slot being engaged with the preceding clip hypovalve is additionally provided on the gun barrel.
Preferably, the grenade launcher also includes that bullet rouses, and bullet drum is arranged 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, there are one the openings for casting shell case for bullet drum lower section setting.The bullet drum is connect with gun body, is pacified
Mounted in the centre of body lower plate and body upper plate, towards body above, in this way in percussion shell case shed downwards do not interfere with it is winged
The flight of row device.
Preferably, the body also includes power battery, support arm, support arm rotary bending piece, holder；
The support arm rotary bending piece is connected and fixed 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 holder is connect with the body lower plate.
Preferably, the aircraft further includes percussion lock, the percussion lock include driving steering engine, trigger shaft, connecting rod,
Steering engine disk, percussion fixed seat；
The percussion fixed seat is connected with the gun body by bolt, and the steering engine is connected in the percussion fixed seat；
The steering engine disk is bolted with the steering engine, and is connect 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.
It is similar with common unmanned plane, the power plant 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 capacity reduces to a certain extent
It picks up down, charges after electricity at upper cover plate velcro one by battery can be fixed.Electron speed regulator receives flight controller
Instruction after can control the size of current of flow direction motor, and then the rotating speed of motor is controlled, to control flight.Add on lower cover
Work goes out several apertures, and electron speed regulator is mounted 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, provides movement required power for full machine.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 fastened by four semicircular anchor ears
In the end of carbon pipe support arm.Cable laying is used for transmission electric current and control instruction between upper and lower cover plates and in each carbon pipe support arm.
The above technical solution of the present invention has the following advantages over the prior art：The present invention will fold aircraft and howitzer
Transmitter organically combines, and convenient for folding, being easy to dismount, a kind of aerial fire support dress of transport easy to carry is provided for soldier
It sets.By designing effective shock absorption buffering mechanism, can be very good to ensure fire accuracy.The aerial howitzer launch craft structure
Simply, moulding material is selected, the own cost of the weapon device can be effectively reduced；With great application value.
Description of the drawings
In order to make the content of the present invention more clearly understood, it below according to specific embodiments of the present invention and combines
Attached drawing, the present invention 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 moved back backward；
Fig. 6 be aircraft described in embodiment 1 grenade launcher forward it is multiple 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 implementation mode
Embodiment 1 is as shown in Figure 1, 2, 3, and present embodiment discloses a kind of aerial howitzer launch crafts of six axis；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 include power battery 1, support arm 2, support arm rotary bending piece 3, body lower plate 4, holder 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
13, rear clip epivalve 14, rear clip hypovalve 21；
Percussion lock includes driving steering engine 16, trigger shaft 17, connecting rod 18, steering engine disk 19, percussion fixed seat 20.
There are one body upper plates 7 for setting above the body, and there are one body lower plates 4 for lower section setting；The damping, buffering
Device is arranged in 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 23 above the gun barrel, and with it is described
Gun body 15 connects；For the bullet drum 23 through the body lower plate 4 among body upper plate 7, the center of the bullet drum 23 is in institute
State the top of body center.
There are one the openings for casting shell case for 23 lower section setting of the bullet drum.The bullet drum 23 is connect with gun body 15, peace
Mounted in the centre of body lower plate 4 and body upper plate 7, towards body above, in percussion, shell case is shed do not interfere with downwards in this way
The flight of aircraft.
The preceding clip hypovalve 12 is fastened by bolt and the preceding clip epivalve 11, to clamp the gun barrel 22；
Clip hypovalve 21 is fastened by bolt and the rear clip epivalve 14 after described, to clamp the gun barrel 22；
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
The axial direction of body is parallel；The kicker 10 passes through the guide rod 13, setting solid in the preceding clip epivalve 12 and the guide rod
Between reservation 9.
A card slot being engaged with the preceding clip hypovalve 12 is additionally provided on the gun barrel 22.
The support arm rotary bending piece 3 is connected and fixed by bolt and the body lower plate 4, the body upper plate 7；The support arm
2 are connect 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
Histogram is to being turned round；The holder 5 is connect with the body lower plate 4.
The percussion fixed seat 20 is connected with the gun body 15 by bolt, and the steering engine 16 is connected in the percussion and fixes
On seat 20；The steering engine disk 19 is bolted with the steering engine 16, and is connect by optical axis with the connecting rod；The percussion
Bar 17 is connect with the connecting rod 18 by optical axis.
As shown in Figure 4,5, after soldier confirms target, one arming signal of grenade launcher, driving steering engine 16 is given to work,
Steering engine 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, waits for bullet drum 23 and body lower plate 4, the back edge of body upper plate 7
Back seat collide in place.At this point, as shown in fig. 6, kicker 10 releases energy, gun body 15, gun barrel 22, bullet drum 23 are driven together forward
It is multiple into it is multiple into place to wait for that bullet drum 23 is collided with body lower plate 4, the back edge of body upper plate 7.
As shown in fig. 7, soldier is in transport, rotating shaft that can be by support arm 2 around support arm rotary bending piece 3 folds, and makes
It obtains size to greatly reduce, the transporter for being conducive to soldier assembles, and improves weapon using flexible.
Embodiment 2 is as shown in Fig. 8,2,3, and the invention discloses a kind of aerial howitzer launch crafts of four axis, it includes pomegranate
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 power battery 1, support arm 2, support arm rotary bending piece 3, body lower plate
4, holder 5, body supporting structure 6, body upper plate 7, rain visor 8, damping, buffering system include leader fixed 9, kicker
10, preceding clip epivalve 11, preceding clip hypovalve 12, guide rod 13, rear clip epivalve 14, rear clip hypovalve 21, trigger system include to drive
Dynamic steering engine 16, trigger shaft 17, connecting rod 18, steering engine disk 19, percussion fixed seat 20.
As shown in figure 4, after soldier confirms target, one arming signal of grenade launcher, driving steering engine 16 is given to work, rudder
Machine disk 19 makes 17 cocking of trigger shaft by connecting rod 18, realizes percussion.Gun body 15, gun barrel 22, bullet drum 23 kick work
Under, together to recoil, kicker 10 compresses storing energy, waits for bullet drum 23 and body lower plate 4, the back edge phase of body upper plate 7
Touch back seat in place.At this point, as shown in figure 5, kicker 10 releases energy, drive gun body 15, gun barrel 22, bullet drum 23 are multiple forward together
Into it is multiple into place to wait for that bullet drum 23 and body lower plate 4, the back edge of body upper plate 7 are collided.
As shown in figure 9, soldier is in transport, rotating shaft that can be by support arm 2 around support arm rotary bending piece 3 folds, and makes
It obtains size to greatly reduce, the transporter for being conducive to soldier assembles, and improves weapon using flexible.
Obviously, the above embodiments are merely examples for clarifying the description, and does not limit the embodiments.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 variation or
It changes.There is no necessity and possibility to exhaust all the enbodiments.And it is extended from this it is obvious variation or
It changes still within the protection scope of the invention.
Claims (7)
1. a kind of aerial howitzer launch craft, which is characterized in that the aircraft includes that grenade launcher, body, damping are slow
Flushing device；There are one body upper plates for setting above the body, and there are one body lower plates for lower section setting；The shock absorption buffering mechanism
It is arranged in the lower section of the body lower plate；
The body is multi-rotor aerocraft body；The body also includes power battery, support arm, support arm rotary bending piece, holder；Institute
Support arm rotary bending piece is stated to be connected and fixed by bolt and the body lower plate, the body upper plate；The support arm turns with the support arm
Folding piece is connected by optical axis, and optical axis is parallel with vertical direction, and the support arm can be turned round around the optical axis in vertical direction；
The holder is connect with 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 nose threads of the preceding clip epivalve and the guide rod are connected and fixed, and the guide rod passes through described leader fixed, side
To axially parallel with the body；The kicker passes through the guide rod, is arranged in the preceding clip epivalve and the fixed seat
Between.
2. aircraft according to claim 1, which is characterized in that the shock absorption buffering mechanism also include preceding clip hypovalve, after
Clip epivalve, rear clip hypovalve；The preceding clip hypovalve is fastened by bolt and the preceding clip epivalve, thus by the gun barrel
It clamps；Clip hypovalve is fastened by bolt and the rear clip epivalve after described, to clamp the gun barrel.
3. aircraft according to claim 2, which is characterized in that be additionally provided on the gun barrel under one and the preceding clip
The card slot of valve occlusion.
4. aircraft according to claim 3, which is characterized in that the grenade launcher also includes that bullet rouses, and the bullet drum is set
It sets above the gun barrel, and is connect 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, which is characterized in that there are one for casting shell case for bullet drum lower section setting
Opening.
6. aircraft according to claim 5, which is characterized in that the aircraft further includes percussion lock, the percussion dress
It sets comprising driving steering engine, trigger shaft, connecting rod, steering engine disk, percussion fixed seat；
The percussion fixed seat is connected with the gun body by bolt, and the steering engine is connected in the percussion fixed seat；It is described
Steering engine disk is bolted with the steering engine, and is connect by optical axis with the connecting rod；The trigger shaft is logical with the connecting rod
Cross optical axis connection.
7. aircraft according to claim 6, which is characterized in that the axis of the gun body and the body axis of aircraft are flat
Row.
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 CN106477047A (en) | 2017-03-08 |
| CN106477047B true 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 |
|---|---|
| CN (1) | CN106477047B (en) |
Families Citing this family (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 |
| CN107702593A (en) * | 2017-09-14 | 2018-02-16 | 牟正芳 | A kind of automatic fire control system 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 |
| CN207701666U (en) * | 2017-09-30 | 2018-08-07 | 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 |
| CN108423188B (en) * | 2018-05-15 | 2024-05-17 | 南京理工大学 | Unmanned aerial vehicle cloud deck mechanism for mounting firearms |
| 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 |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6250197B1 (en) * | 1999-02-16 | 2001-06-26 | Paul H. Sanderson | Sponson tow-plate-mounted helicopter armament apparatus and associated methods |
| 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 |
| 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
- 2016-11-23 CN CN201611046827.1A patent/CN106477047B/en not_active Expired - Fee Related
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| Publication number | Publication date |
|---|---|
| CN106477047A (en) | 2017-03-08 |
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Granted publication date: 20180727 |