CN212099349U - Bullet shooting mechanism and unmanned aerial vehicle - Google Patents
Bullet shooting mechanism and unmanned aerial vehicle Download PDFInfo
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- CN212099349U CN212099349U CN202020749093.9U CN202020749093U CN212099349U CN 212099349 U CN212099349 U CN 212099349U CN 202020749093 U CN202020749093 U CN 202020749093U CN 212099349 U CN212099349 U CN 212099349U
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- steering engine
- projectile
- missile
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Abstract
The embodiment of the utility model discloses bullet shooting mechanism and unmanned aerial vehicle, include: 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 utility model discloses the scheme, there is the problem that the structure is complicated in the current mechanism of throwing of at least partial solution, reaches the simple purpose of structure and mounting form.
Description
Technical Field
The utility model relates to a mechanism and unmanned aerial vehicle of jettisoning.
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, anti-terrorism and stability maintenance public security law enforcement, emergency rescue and rescue, emergency rescue and relief, coastline inspection and the like.
With the gradual improvement of unmanned aerial vehicle application, there are more demands to unmanned aerial vehicle that has the function of throwing bomb in the flight process, for example use at the fire control unmanned aerial vehicle of throwing the fire extinguishing bomb, for military use tactics with attacking unmanned aerial vehicle to ground, police with attacking unmanned aerial vehicle etc. throw offensive weapon unmanned aerial vehicle. 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.
SUMMERY OF THE UTILITY MODEL
In view of this, the embodiment of the utility model provides a bullet mechanism and unmanned aerial vehicle are proposed, there is the problem that the structure is complicated in the current bullet mechanism of solution at least partially.
In a first aspect, an embodiment of the present invention provides a bullet 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 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.
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 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.
According to a specific implementation manner of the embodiment of the present invention, the elastic connection assembly includes 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, can ensure that after all the elastic bodies fall out of the bomb compartment, the hinge drives the automatic reset of the bomb compartment cover, reduces the increase of accessories to a certain extent, and reduces the whole weight of the elastic mechanism.
According to the utility model discloses a concrete mode of realization, the superficial area of bullet cabin cover is less than storage space is in the ascending cross-sectional area of projectile body throw-out 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 the utility model discloses a concrete implementation mode, the spring hinge with hinge installation piece is bolted connection.
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 the utility model discloses a concrete implementation mode, the capsule is the cylinder 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 edge, can reduce the risk of colliding with damage or personnel's injury.
According to a specific implementation manner of the embodiment of the present invention, the lightening holes are circular structures; 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 present invention, the lightening holes are plural; 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 the embodiment of the utility model provides a concrete implementation mode, the bullet cabin with the steering wheel mounting bracket is 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.
According to the embodiment of the utility model provides a concrete implementation mode, the bullet cabin with the steering wheel mounting bracket bonds for the 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 a projectile shooting mechanism as described in any one of the above; the projectile throwing mechanism is arranged on the machine body.
The embodiment of the utility model provides an among bullet shooting mechanism and unmanned aerial vehicle, include: 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, 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 utility model has the advantages of as follows:
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 that other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic overall structure diagram of an embodiment of the present invention;
FIG. 2 is a schematic view of the clamping state of the rocker arm and the magazine cover in the embodiment of the present invention;
FIG. 3 is a schematic diagram of the state in which the rocker arm is separated from the magazine cover according to the embodiment of the present 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; 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
The 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. Additionally, 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, referring to fig. 1-7, a preferred embodiment of the projectile shooting mechanism of the present invention is shown. Wherein, fig. 1 is a schematic view of the overall structure of the embodiment of the present invention; FIG. 2 is a schematic view of the clamping state of the rocker arm and the magazine cover in the embodiment of the present invention; FIG. 3 is a schematic diagram of the state in which the rocker arm is separated from the magazine cover according to the embodiment of the present 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 assembly and the steering engine mounting rack 3 are both arranged at the end part of the same side of the capsule 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 elastic 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 elastic bodies fall out of the bomb bay 1, the hinge drives the automatic reset of the bomb bay cover 4, the increase of accessories is reduced to a certain extent, and the whole weight of the elastic mechanism is reduced.
Further, 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 whole focus and 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, the utility model discloses well bullet cabin and steering wheel mounting bracket except selecting non-metallic composite, according to the weight of the projectile body and the environmental requirement of locating, can also select other materials, for example when projectile body weight is great, bullet cabin and steering wheel mounting bracket can select 6061-T6 weldable aluminum alloy material, further guarantee to throw the bullet needs.
Furthermore, the utility model discloses well hinge and hinge installation piece's connected mode except selecting bolted connection, can also select other modes, for example both peg graft, as long as can effectively fix hinge and hinge installation piece can.
Furthermore, the utility model discloses the structure of well bullet cabin except the cylinder, can also be other structures, for example cuboid tubular structure, as long as can satisfy accomodate the projectile body and be favorable to the flight can.
Furthermore, the shape of the lightening hole in the utility model can be other structures besides circular, such as square, as long as the lightening weight of the bullet cabin can be reduced and the carrying is convenient.
Furthermore, the utility model discloses well lightening hole set up the position except the casing in the bullet cabin, can also be in other positions, for example bullet cabin cover, as long as be favorable to alleviateing the whole quality of bullet mechanism and can guarantee loading and throwing out of the projectile body.
To sum up, no matter be the material of bullet cabin and steering wheel mounting bracket select, the connected mode of hinge and hinge installation piece, the structure of bullet cabin select, the shape of lightening hole selects, still the position that sets up of lightening hole, as long as belong to "just can control the projectile body through the control steering wheel opens and shuts and throw out and pin the design of bullet cabin cover", all be in the protection scope of the utility model.
The embodiment of the utility model provides a bullet shooting mechanism, include: 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, 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 embodiment of the utility model provides a have following advantage:
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 embodiments of the present invention, but the protection 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 should be covered by the protection 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.
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| CN202020749093.9U CN212099349U (en) | 2020-05-08 | 2020-05-08 | Bullet shooting mechanism and unmanned aerial vehicle |
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| CN202020749093.9U CN212099349U (en) | 2020-05-08 | 2020-05-08 | Bullet shooting mechanism and unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111591446A (en) * | 2020-05-08 | 2020-08-28 | 北京壮龙无人机科技有限公司 | Bullet shooting mechanism and unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111591446A (en) * | 2020-05-08 | 2020-08-28 | 北京壮龙无人机科技有限公司 | Bullet shooting mechanism and unmanned aerial vehicle |
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