CN111591446A - Bullet shooting mechanism and unmanned aerial vehicle - Google Patents
Bullet shooting mechanism and unmanned aerial vehicle Download PDFInfo
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- CN111591446A CN111591446A CN202010380627.XA CN202010380627A CN111591446A CN 111591446 A CN111591446 A CN 111591446A CN 202010380627 A CN202010380627 A CN 202010380627A CN 111591446 A CN111591446 A CN 111591446A
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- cabin
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- missile
- bomb
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- 230000007246 mechanism Effects 0.000 title claims abstract description 55
- 238000003860 storage Methods 0.000 claims abstract description 17
- 239000002775 capsule Substances 0.000 claims description 10
- 239000002905 metal composite material Substances 0.000 claims description 5
- 229910052755 nonmetal Inorganic materials 0.000 claims description 5
- 239000011347 resin Substances 0.000 claims description 5
- 229920005989 resin Polymers 0.000 claims description 5
- 238000009434 installation Methods 0.000 abstract description 6
- 108010066057 cabin-1 Proteins 0.000 description 9
- 230000002349 favourable effect Effects 0.000 description 8
- 238000000034 method Methods 0.000 description 7
- 238000007689 inspection Methods 0.000 description 5
- 230000006378 damage Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000005457 optimization Methods 0.000 description 4
- 230000005484 gravity Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 208000004350 Strabismus Diseases 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 2
- 208000014674 injury Diseases 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
-
- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C19/00—Hand fire-extinguishers in which the extinguishing substance is expelled by an explosion; Exploding containers thrown into the fire
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- Public Health (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The embodiment of the invention discloses a bullet shooting mechanism and an unmanned aerial vehicle, which comprise: the missile cabin comprises a missile cabin body, a steering engine mounting frame, a missile cabin cover, a rocker arm, an elastic connecting assembly and a missile body; the cartridge comprises a shell and a storage space enclosed by the shell; the projectile body is positioned in the storage space; the steering engine is connected with the missile cabin through a steering engine mounting frame; the bomb cabin cover is movably connected with the bomb cabin through an elastic connecting assembly; the elastic connecting assembly and the steering engine mounting rack are both arranged at the end parts of the same side of the missile cabin; the rocker arm is connected with the steering engine; when a throwing signal is received, the steering engine drives the rocker arm to be separated from the elastic cabin cover; after receiving the reset signal, the steering engine drives the rocker arm to be clamped with the elastic cabin cover; the surface of the shell is provided with lightening holes with a through structure. Through the scheme of the embodiment of the invention, the problem that the existing bullet shooting mechanism is complex in structure is at least partially solved, and the aim of simple structure and installation form is fulfilled.
Description
Technical Field
The invention relates to a projectile shooting mechanism and an unmanned aerial vehicle.
Background
With the rapid development of science and technology, in recent years, the application development of unmanned aerial vehicles to various industries is increasingly wide. At present, the application of unmanned aerial vehicles has been related to the fields of aerial photography, agriculture and forestry plant protection, geological exploration, power inspection, oil and gas pipeline inspection, highway accident management, forest fire prevention inspection, polluted environment inspection, emergency rescue and rescue, emergency rescue and relief, coastline inspection and the like.
Along with the gradual perfection of unmanned aerial vehicle application, there has more demand to the unmanned aerial vehicle that has the function of throwing bomb in the flight process, for example use at throwing aggressive weapon unmanned aerial vehicle such as the fire control unmanned aerial vehicle of throwing the fire extinguishing bomb. A projectile shooting mechanism having a projectile shooting function is widely used.
However, the existing bullet shooting mechanism has the problem of complex structure.
In addition, in order to satisfy the functional needs of throwing the bullet, current bullet mechanism of throwing still has the heavy, the big problem of the operation degree of difficulty of weight.
Disclosure of Invention
In view of this, the embodiment of the invention provides a projectile shooting mechanism and an unmanned aerial vehicle, which at least partially solve the problem that the existing projectile shooting mechanism is complex in structure.
In a first aspect, an embodiment of the present invention provides a projectile shooting mechanism, including: the missile cabin comprises a missile cabin body, a steering engine mounting frame, a missile cabin cover, a rocker arm, an elastic connecting assembly and a missile body; the cartridge comprises a shell and a storage space enclosed by the shell; the projectile body is positioned in the storage space; the steering engine is connected with the missile cabin through the steering engine mounting frame; the bomb cabin cover is movably connected with the bomb cabin through the elastic connecting assembly; the elastic connecting assembly and the steering engine mounting rack are both arranged at the end parts of the same side of the missile cabin; the rocker arm is connected with the steering engine; after receiving a throwing signal, the steering engine drives the rocker arm to be separated from the capsule cover; after receiving a reset signal, the steering engine drives the rocker arm to be clamped with the elastic cabin cover; the surface of the shell is provided with lightening holes of a through structure.
The bomb cabin cover is clamped through the rocker arm, and the bomb body is locked inside the bomb cabin. After the steering engine receives the throwing signal, the steering engine drives the rocker arm to be separated from the bomb cabin cover, the rocker arm is opened, the bomb body presses the bomb cabin cover open through self gravity, and the bomb body falls out of the bomb cabin. The elastic connecting assembly is used for restoring the elastic cabin cover. And then, when the steering engine receives a reset signal, the steering engine drives the rocker arm to be clamped with the elastic cabin cover.
In addition, the lightening holes of the through structure are arranged on the surface of the shell, so that the whole weight of the throwing mechanism is lightened, and the structure optimization and the carrying are facilitated.
According to a specific implementation manner of the embodiment of the invention, the elastic connecting assembly comprises a spring hinge and a hinge mounting block; the bomb cabin cover is connected with the spring hinge; the spring hinge is connected with the bomb compartment through the hinge mounting block.
The bullet cabin cover is connected with the bullet cabin through the spring hinge, the structure is simple, the purpose that the bullet body falls out of the bullet cabin after the rocker arm is separated from the bullet cabin cover can be effectively achieved, and meanwhile, the bullet cabin cover is convenient to reset.
The spring hinge is one of elastic structures for realizing recovery deformation, and can ensure that the hinge drives the automatic reset of the bomb bay cover after all the bomb bodies fall out of the bomb bay, reduce the increase of accessories to a certain extent and reduce the whole weight of the elastic mechanism.
According to a specific implementation of the embodiment of the invention, the surface area of the pod cover is smaller than the cross-sectional area of the storage space in the projectile launching direction.
By adopting the structure, the structure of the bomb cabin cover is optimized on the premise that the bomb body cannot leak out when the rocker arm is in a locked state, the weight of the bomb cabin cover is reduced, and the restoration of the spring hinge is facilitated.
According to a specific implementation manner of the embodiment of the invention, the spring hinge is connected with the hinge mounting block through a bolt.
The spring hinge and the hinge mounting block which are connected through the bolts are of detachable structures, are easy to operate and easy to realize, and are beneficial to installation, replacement and maintenance of the elastic mechanism.
According to a specific implementation manner of the embodiment of the invention, the magazine is of a cylindrical structure.
The bullet cabin of cylinder structure is favorable to reducing the windage of unmanned aerial vehicle at the flight in-process, simultaneously because it does not have outstanding arris limit, can reduce the risk of colliding with damage or personnel's injury.
According to a specific implementation manner of the embodiment of the invention, the lightening holes are of a circular structure; the passing area of the lightening hole is smaller than the maximum cross-sectional area of the projectile body.
By adopting the structure, the throwing route of the projectile body can be limited, the projectile body is prevented from leaking from the lightening hole, and the storage of the projectile body before throwing is ensured to be more controllable.
According to a specific implementation manner of the embodiment of the invention, the number of the lightening holes is multiple; the plurality of lightening holes are uniformly distributed on the shell.
The evenly distributed of lightening hole can make the focus of mechanism of throwing bullet more regular, installs in unmanned aerial vehicle back, guarantees whole focus and does not squint, is favorable to unmanned aerial vehicle's normal flight.
According to a specific implementation mode of the embodiment of the invention, the missile cabin and the steering engine mounting frame are made of non-metal composite materials.
The non-metal composite material is adopted, so that the high-strength high-plasticity combined ball has the characteristics of high strength, high plasticity and low density, and is further favorable for reducing the weight of a throwing mechanism.
According to a specific implementation mode of the embodiment of the invention, the missile cabin is bonded with the steering engine mounting frame by resin.
The resin bonding mode is simple to operate, other structures are not needed, and optimization of the whole structure and weight reduction are facilitated.
In a second aspect, an embodiment of the present invention provides an unmanned aerial vehicle, including a body, and the projectile shooting mechanism as described in any one of the above; the projectile throwing mechanism is arranged on the machine body.
The projectile shooting mechanism and the unmanned aerial vehicle provided by the embodiment of the invention comprise: the missile cabin comprises a missile cabin body, a steering engine mounting frame, a missile cabin cover, a rocker arm, an elastic connecting assembly and a missile body; the cartridge comprises a shell and a storage space enclosed by the shell; the projectile body is positioned in the storage space; the steering engine is connected with the missile cabin through a steering engine mounting frame; the bomb cabin cover is movably connected with the bomb cabin through an elastic connecting assembly; the elastic connecting component and the steering engine mounting rack are both arranged at the end parts of the same side of the missile cabin; the rocker arm is connected with the steering engine; when a throwing signal is received, the steering engine drives the rocker arm to be separated from the elastic cabin cover; after receiving the reset signal, the steering engine drives the rocker arm to be clamped with the elastic cabin cover; the surface of the shell is provided with lightening holes with a through structure, so that the problem that the existing bullet throwing mechanism is complex in structure is at least partially solved, and the purpose of simple structure and installation form is achieved.
Compared with the prior art, the invention has the following advantages:
firstly, the structural design is simpler, the process difficulty is greatly reduced, and the production cost is reduced.
Secondly, the overall safety and reliability of the mechanism are higher.
Thirdly, the whole structure is light in weight and convenient to carry.
Fourthly, can directly add the bullet after unmanned aerial vehicle returns to landing, need not do other operations, reduce operating time, increase efficiency.
Fifthly, the unmanned aerial vehicle with the fixed wings, the multi-axis unmanned aerial vehicle, the unmanned helicopter and the like can be used.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic overall structure diagram of an embodiment of the present invention;
FIG. 2 is a schematic diagram illustrating a state in which a rocker arm is engaged with a magazine cover according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of an embodiment of the present invention with the rocker arm disengaged from the magazine lid;
FIG. 4 is a top view of an embodiment of the present invention;
FIG. 5 is a schematic perspective view of an embodiment of the present invention;
FIG. 6 is a front view of an embodiment of the present invention; and
fig. 7 is a rear view of an embodiment of the present invention.
Reference numerals
1 Cartridge magazine
2 steering engine
3 steering engine mounting bracket
4 Cartridge chamber cover
5 spring hinge
6 hinge mounting block
7 rocking arm
8 lightening holes
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
It should be noted that, in the case of no conflict, the features in the following embodiments and examples may be combined with each other; moreover, all other embodiments that can be derived by one of ordinary skill in the art from the embodiments disclosed herein without making any creative effort fall within the scope of the present disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
In a first aspect, and with reference to fig. 1-7, a preferred embodiment of the projectile mechanism of the present invention is shown. FIG. 1 is a schematic diagram of the overall structure of an embodiment of the present invention; FIG. 2 is a schematic diagram illustrating a state in which a rocker arm is engaged with a magazine cover according to an embodiment of the present invention; FIG. 3 is a schematic illustration of a state in which the rocker arm is disengaged from the magazine lid in an embodiment of the invention; FIG. 4 is a top view of an embodiment of the present invention; FIG. 5 is a schematic perspective view of an embodiment of the present invention; FIG. 6 is a front view of an embodiment of the present invention; fig. 7 is a rear view of an embodiment of the present invention.
This embodiment bullet shooting mechanism includes: the missile cabin comprises a missile cabin 1, a steering engine 2, a steering engine mounting frame 3, a missile cabin cover 4, a rocker arm 7, an elastic connecting assembly and a missile body; the cartridge 1 comprises a shell and a storage space enclosed by the shell; the projectile body is positioned in the storage space; the steering engine 2 is connected with the capsule 1 through a steering engine mounting frame 3; the bomb cabin cover 4 is movably connected with the bomb cabin 1 through an elastic connecting assembly; the elastic connecting component and the steering engine mounting rack 3 are both arranged at the end part of the same side of the bomb cabin 1; the rocker arm 7 is connected with the steering engine 2; after receiving a throwing signal, the steering engine 2 drives the rocker arm 7 to be separated from the capsule cover 4; after receiving the reset signal, the steering engine 2 drives the rocker arm 7 to be clamped with the spring cabin cover 4; the surface of the shell is provided with lightening holes 8 of a through structure.
The bomb compartment cover 4 is clamped through the rocker arm 7, and the bomb body is locked inside the bomb compartment 1. After the steering engine 2 receives the projectile shooting signal, the steering engine 2 drives the rocker arm 7 to be separated from the projectile cabin cover 4, the rocker arm 7 is opened, the projectile body presses open the projectile cabin cover 4 through self gravity, and the projectile body falls out of the projectile cabin 1. The magazine lid 4 is reset under the action of the elastic connection assembly. Then, when the steering engine 2 receives a reset signal, the steering engine 2 drives the rocker arm 7 to be clamped with the elastic cabin cover 4. The lightening holes 8 of the through structure are formed in the surface of the shell, so that the whole weight of the bullet throwing mechanism is lightened, and the structure optimization and carrying are facilitated.
Secondly, in the projectile mechanism of the embodiment, the elastic connecting assembly comprises a spring hinge 5 and a hinge mounting block 6; the bomb cabin cover 4 is connected with a spring hinge 5; the spring hinge 5 is connected with the capsule 1 through a hinge mounting block 6.
Make the capsule lid 4 be connected with capsule 1 through spring hinge 5, simple structure can effectively realize falling out the mesh of capsule 1 when rocking arm 7 breaks away from the back body with capsule lid 4, is convenient for reset capsule lid 4 simultaneously.
The spring hinge 5 is one of elastic structures for realizing recovery deformation, and can ensure that after all the bullets fall out of the bullet cabin 1, the hinge drives the bullet cabin cover 4 to automatically reset, the increase of accessories is reduced to a certain degree, and the overall weight of the elastic mechanism is reduced.
In the projectile launching mechanism of the present embodiment, the surface area of the magazine cover 4 is smaller than the cross-sectional area of the storage space in the projectile launching direction.
By adopting the structure, the structure of the bomb compartment cover 4 is optimized on the premise that the bomb body cannot leak out when the rocker arm 7 is in a locked state, the weight of the bomb compartment cover 4 is reduced, and the spring hinge 5 is favorably reset.
In the projectile mechanism of the present embodiment, the spring hinge 5 and the hinge mounting block 6 are connected by bolts.
The spring hinge 5 and the hinge mounting block 6 which are connected through the bolts are of detachable structures, are easy to operate and easy to realize, and are favorable for mounting, replacing and maintaining the elastic mechanism.
In the projectile shooting mechanism of the present embodiment, the magazine 1 has a cylindrical structure.
The bullet cabin 1 of cylinder structure is favorable to reducing the windage of unmanned aerial vehicle at the flight in-process, simultaneously because it does not have outstanding edge, can degrade the risk of colliding with damage or personnel's injury.
Furthermore, in the projectile shooting mechanism of the present embodiment, the lightening hole 8 is a circular structure; the passage area of the lightening holes 8 is smaller than the maximum cross-sectional area of the projectile body.
By adopting the structure, the throwing route of the projectile body can be limited, the projectile body is prevented from leaking from the lightening hole 8, and the storage of the projectile body before throwing is ensured to be more controllable.
In the projectile shooting mechanism of the present embodiment, there are a plurality of lightening holes 8; a plurality of lightening holes 8 are evenly distributed in the shell.
The evenly distributed of lightening hole 8 can make the focus of mechanism of throwing bullet more regular, installs in unmanned aerial vehicle back, guarantees that whole weight center does not squint, is favorable to unmanned aerial vehicle's normal flight.
In addition, in this embodiment's bullet shooting mechanism, bullet cabin 1 and steering wheel mounting bracket 3 are non-metallic composite.
The non-metal composite material is adopted, so that the high-strength high-plasticity combined ball has the characteristics of high strength, high plasticity and low density, and is further favorable for reducing the weight of a throwing mechanism.
In addition, in the projectile shooting mechanism of the embodiment, the projectile cabin 1 and the steering engine mounting frame 3 are bonded by resin.
The resin bonding mode is simple to operate, other structures are not needed, and optimization of the whole structure and weight reduction are facilitated.
Referring again to fig. 1 to 7, during the projectile firing:
controlling a signal of the steering engine 2, driving the rocker arm 7 to rotate towards the outer side, so that the locking limit of the bomb compartment cover 4 is cancelled, and at the moment, a bomb body presses the bomb compartment cover 4 to be opened by means of self gravity to fall out of the bomb compartment 1;
when the projectile body falls out of the projectile cabin 1, the projectile cabin cover 4 rebounds by means of the elastic force of the spring hinge 5, the steering engine 2 is controlled to send a signal at the moment, the rocker arm 7 of the steering engine 2 returns to the initial position, and therefore the projectile cabin cover 4 is longitudinally limited and locked, and the resistance of the aircraft in the air is reduced;
after the plane returns to the landing after the bomb is thrown, the bomb can be added again without other operations, thereby reducing the operation time and improving the efficiency.
It should be noted that, in the invention, the missile compartment and the steering engine mounting rack are made of non-metal composite materials, and other materials can be selected according to the weight of the missile body and the environment requirement, for example, when the weight of the missile body is large, the missile compartment and the steering engine mounting rack can be made of 6061-T6 weldable aluminum alloy, so that the missile requirement is further ensured.
In addition, the connection mode of the hinge and the hinge mounting block can be other modes besides the bolt connection mode, for example, the hinge and the hinge mounting block can be inserted, and the hinge mounting block can be effectively fixed.
Besides the cylindrical body, the structure of the bullet cabin can be other structures, such as a rectangular parallelepiped cylindrical structure, as long as the bullet cabin can accommodate bullets and is favorable for flying.
In addition, the shape of the lightening hole can be round, and other structures such as square can be adopted, so long as the lightening hole can lighten the weight of the bullet cabin and is convenient to carry.
In addition, the lightening hole can be arranged at other positions besides the shell of the bullet cabin, such as a bullet cabin cover, so long as the overall mass of the bullet throwing mechanism is favorably reduced and the loading and the throwing of the bullet bodies can be ensured.
In summary, the material selection of the missile compartment and the installation frame of the steering engine, the connection mode of the hinge and the hinge installation block, the structure selection of the missile compartment, the shape selection of the lightening hole and the arrangement position of the lightening hole are all within the protection scope of the invention as long as the concept of controlling the throwing-out of the missile body and locking the missile compartment cover by controlling the opening and closing of the steering engine is adopted.
The bullet shooting mechanism of the embodiment of the invention comprises: the missile cabin comprises a missile cabin body, a steering engine mounting frame, a missile cabin cover, a rocker arm, an elastic connecting assembly and a missile body; the cartridge comprises a shell and a storage space enclosed by the shell; the projectile body is positioned in the storage space; the steering engine is connected with the missile cabin through a steering engine mounting frame; the bomb cabin cover is movably connected with the bomb cabin through an elastic connecting assembly; the elastic connecting assembly and the steering engine mounting frame are both arranged at the end parts of the same side of the bomb compartment; the rocker arm is connected with the steering engine; when a throwing signal is received, the steering engine drives the rocker arm to be separated from the spring cabin cover; after receiving the reset signal, the steering engine drives the rocker arm to be clamped with the elastic cabin cover; the surface of the shell is provided with the weight reducing hole with a through structure, and at least part of the weight reducing hole solves the problem that the existing bullet throwing mechanism is complex in structure, so that the purpose of simple structure and installation form is achieved.
Compared with the prior art, the embodiment of the invention has the following advantages:
firstly, the structural design is simpler, the process difficulty is greatly reduced, and the production cost is reduced.
Secondly, the overall safety and reliability of the mechanism are higher.
Thirdly, the lightening holes are formed in the bullet cabin, so that the weight of the whole mechanism is further lightened, the whole weight is light, and the bullet cabin is convenient to carry.
Fourthly, can directly add the bullet after unmanned aerial vehicle returns to landing, need not do other operations, reduce operating time, increase efficiency.
Fifthly, the unmanned aerial vehicle with the fixed wings, the multi-axis unmanned aerial vehicle, the unmanned helicopter and the like can be used.
In a second aspect, an embodiment of the present invention provides an unmanned aerial vehicle, including a body and a projectile shooting mechanism; the bullet feeding mechanism is arranged on the machine body; the structure, principle and effect of the projectile mechanism are the same as those of the above embodiments, and are not described in detail here.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a bullet shooting mechanism for unmanned aerial vehicle, its characterized in that includes: the missile cabin comprises a missile cabin body, a steering engine mounting frame, a missile cabin cover, a rocker arm, an elastic connecting assembly and a missile body;
the cartridge comprises a shell and a storage space enclosed by the shell;
the projectile body is positioned in the storage space;
the steering engine is connected with the missile cabin through the steering engine mounting frame;
the bomb cabin cover is movably connected with the bomb cabin through the elastic connecting assembly;
the elastic connecting assembly and the steering engine mounting rack are both arranged at the end part of the same side of the missile cabin;
the rocker arm is connected with the steering engine;
after receiving a throwing signal, the steering engine drives the rocker arm to be separated from the capsule cover;
after receiving a reset signal, the steering engine drives the rocker arm to be clamped with the elastic cabin cover;
the surface of the shell is provided with lightening holes of a through structure.
2. The projectile mechanism of claim 1,
the elastic connecting assembly comprises a spring hinge and a hinge mounting block;
the bomb cabin cover is connected with the spring hinge;
the spring hinge is connected with the bomb compartment through the hinge mounting block.
3. The projectile mechanism of claim 2,
the surface area of the bomb compartment cover is smaller than the cross-sectional area of the storage space in the projectile launching direction.
4. The projectile mechanism of claim 3,
the spring hinge and the hinge mounting block are connected through bolts.
5. The projectile mechanism of claim 4,
the bullet cabin is of a cylindrical structure.
6. The projectile mechanism of claim 5,
the lightening holes are of circular structures;
the passing area of the lightening hole is smaller than the maximum cross-sectional area of the projectile body.
7. The projectile mechanism of claim 6,
the number of the lightening holes is multiple;
the plurality of lightening holes are uniformly distributed on the shell.
8. The projectile mechanism of claim 7,
the missile cabin and the steering engine mounting frame are made of non-metal composite materials.
9. The projectile mechanism of claim 8,
the missile cabin is bonded with the steering engine mounting frame through resin.
10. An unmanned aerial vehicle is characterized in that,
comprising a body, and a projectile launching mechanism as claimed in any one of claims 1 to 9;
the projectile throwing mechanism is arranged on the machine body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010380627.XA CN111591446A (en) | 2020-05-08 | 2020-05-08 | Bullet shooting mechanism and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010380627.XA CN111591446A (en) | 2020-05-08 | 2020-05-08 | Bullet shooting mechanism and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111591446A true CN111591446A (en) | 2020-08-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010380627.XA Pending CN111591446A (en) | 2020-05-08 | 2020-05-08 | Bullet shooting mechanism and unmanned aerial vehicle |
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| Country | Link |
|---|---|
| CN (1) | CN111591446A (en) |
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2020
- 2020-05-08 CN CN202010380627.XA patent/CN111591446A/en active Pending
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