CN214792811U - Flying projectile body structure is patrolled to whole compression molding carbon-fibre composite - Google Patents
Flying projectile body structure is patrolled to whole compression molding carbon-fibre composite Download PDFInfo
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- CN214792811U CN214792811U CN202120548208.2U CN202120548208U CN214792811U CN 214792811 U CN214792811 U CN 214792811U CN 202120548208 U CN202120548208 U CN 202120548208U CN 214792811 U CN214792811 U CN 214792811U
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Abstract
The utility model discloses a carbon-fibre composite patrols and flies body structure is pressed to whole mould, including carbon fiber bullet body, warhead and bullet tail, the one end fixedly connected with warhead of carbon fiber bullet body, carbon fiber bullet body other end fixedly connected with bullet tail, be provided with advancing device on the bullet tail, advancing device comprises bullet tail rotor and electric motor, bullet tail rotor side is provided with the electric motor who is connected with its transmission, carbon fiber bullet body side has been seted up first and has been placed the chamber, first intracavity portion of placing is provided with rotatable first folding bullet wing, first folding bullet wing side fixedly connected with pivot, first chamber side of placing has been seted up the second and has been placed the chamber, the second is placed the intracavity and is provided with the second and folds the bullet wing. The utility model discloses structural design scientific and reasonable adopts the carbon fiber design, has realized the lightweight effect to the missile wing can be folded fast, convenient transportation, and the practicality is strong.
Description
Technical Field
The utility model relates to a patrol missile equipment technical field specifically is a whole compression molding carbon-fibre composite patrols missile body structure.
Background
The patrol bomb is a kind of ammunition (or sub-ammunition) which can be thrown by using existent weapon, can make patrol flight in target zone, and can undertake single or multiple tasks of monitoring, reconnaissance, battle damage assessment, aerial wireless relay and target attack. The device comprises a warhead, a guidance device, a propulsion system, a control device (including a missile wing), a stabilizing device (including a tail wing or a parachute) and the like. The related key technologies mainly comprise: inflatable flank technology, small-sized high-power engine technology, information transmission technology, multi-mode seeker, guidance, navigation and control technology, composite material technology and the like. The United states has become a leader of the development of the ammunition, which certainly draws high attention of weapon developers in other countries and becomes an important trend of the development of future ammunition fields. The patrol bombs can be thrown in various forms without improving the weapon platform. Can be independently put in, and can be used as ammunition carried by various shells to put in. The mode that the existing parts are assembled on site is adopted for the patrol missile, so that the use efficiency and safety of the patrol missile are improved. The flying bullet body is not easy to fold, occupies a large space and brings troubles to transportation. Therefore, the flying bomb structure made of the carbon fiber composite material through integral compression molding is provided.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an integral compression molding carbon-fibre composite patrols and flies bullet body structure to solve the problem that proposes in the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme: a carbon fiber composite material flying-patrol projectile body structure integrally molded through compression molding comprises a carbon fiber projectile body, a projectile head and a projectile tail, wherein the projectile head is fixedly connected to one end of the carbon fiber projectile body, the projectile tail is fixedly connected to the other end of the carbon fiber projectile body, a propelling device is arranged on the projectile tail and consists of a projectile tail rotor wing and an electric motor, the electric motor in transmission connection with the projectile tail rotor wing is arranged on the side surface of the projectile tail rotor wing, a first placing cavity is formed in the side surface of the carbon fiber projectile body, a rotatable first folding projectile wing is arranged in the first placing cavity, a rotating shaft is fixedly connected to the side surface of the first folding projectile wing, a second placing cavity is formed in the side surface of the first placing cavity, a second folding projectile wing is arranged in the second placing cavity, single-control assemblies are arranged on the side surfaces of the first folding projectile wing and the second folding projectile wing, and a connecting seat is arranged at the top of the single-control assemblies, the single control assembly consists of a first bevel gear, a second bevel gear, a connecting rod and a micro motor which are matched, and the bottom end of the rotating shaft penetrates through the connecting seat and is fixedly connected with the first bevel gear.
Preferably, the carbon fiber bullet body is of a cylindrical structure.
Preferably, the middle part of the carbon fiber bullet body is provided with a warhead.
Preferably, the second bevel gear is meshed with the first bevel gear, and the second bevel gear is fixedly connected with the connecting rod.
Preferably, one end of the connecting rod is in transmission connection with an output shaft of the micro motor through a coupler.
Preferably, a camera is installed at the bottom of the warhead, and a communication data link mechanism is installed on the other side of the camera.
Compared with the prior art, the beneficial effects of the utility model are that: the integrally molded carbon fiber composite material flying bomb structure is simple and reasonable in structural design and high in practicability, a bomb body shell is made of the selected carbon fiber composite material, the lightweight design of the bomb body structure is realized, the bomb body is selected from a multi-section modular design and is convenient to process and use, the angle and the posture of the corresponding bomb wing can be adjusted according to the situation while the folded bomb wing is folded and unfolded by arranging a plurality of remote-control single-control assemblies, so that the flying effect of the bomb body structure in the flying process is ensured, the space occupation of the bomb body can be reduced by the bomb wing in the folded design, the volume after folding is reduced, the bomb body is convenient to place, a camera and a communication data chain mechanism are arranged on the bomb, a video signal can be returned in real time in the flying process, a fighting part is arranged at the same time, the effect of 'fighting with one body' can be realized, and the fighting capacity and effect of the bomb body are improved, the integrated design of ammunition-aircraft is realized, and various functions of cruise detection, tracking attack, hovering striking and the like can be completed.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the structure flight state of the present invention;
fig. 3 is a schematic view of the structure of the single control assembly of the present invention.
In the figure: 1 carbon fiber bullet body, 11 warheads, 12 tail rotors, 13 electric motors, 14 warhead parts, 15 first placing cavities, 16 first folding missile wings, 17 rotating shafts, 18 second placing cavities, 19 second folding missile wings, 2 single-control components, 21 cameras, 22 communication data chain mechanisms, 23 connecting seats, 24 first bevel gears, 25 second bevel gears, 26 connecting rods and 27 micro motors.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-3, the present invention provides a technical solution: a carbon fiber composite material integrally molded flying bullet structure comprises a carbon fiber bullet body 1, a bullet head 11 and a bullet tail, wherein a bullet body shell is made of carbon fiber composite material, the lightweight design of the bullet body structure is realized, the bullet body is designed in a multi-section modular design and is convenient to process and use, the carbon fiber bullet body 1 is of a cylindrical structure, one end of the carbon fiber bullet body 1 is fixedly connected with the bullet head 11, the other end of the carbon fiber bullet body 1 is fixedly connected with the bullet tail, the bullet tail is provided with a propelling device, the propelling device consists of a bullet tail rotor wing 12 and an electric motor 13, the side surface of the bullet tail rotor wing 12 is provided with the electric motor 13 in transmission connection with the bullet head, the middle part of the carbon fiber bullet body 1 is provided with a fighting part 14, the side surface of the carbon fiber bullet body 1 is provided with a first placing cavity 15, a rotatable first folded bullet wing 16 is arranged in the first placing cavity 15, the side surface of the first folded bullet wing 16 is fixedly connected with a rotating shaft 17, the side surface of the first placing cavity 15 is provided with a second placing cavity 18, a second folding missile wing 19 is arranged in the second placing cavity 18, the side surfaces of the first folding missile wing 16 and the second folding missile wing 19 are respectively provided with a single control component 2, the top of the single control component 2 is provided with a connecting seat 23, the single control component 2 consists of a first bevel gear 24, a second bevel gear 25, a connecting rod 26 and a micro motor 27 which are matched, the bottom end of a rotating shaft 17 penetrates through the connecting seat 23 and is fixedly connected with the first bevel gear 24, the second bevel gear 25 is meshed with the first bevel gear 24, the second bevel gear 25 is fixedly connected with the connecting rod 26, one end of the connecting rod 26 is in transmission connection with an output shaft of the micro motor 27 through a coupler, and through the arrangement of the plurality of remote-controlled single control components 2, the folding missile wings can be folded and simultaneously adjusted in angle and posture according to the situation, so as to ensure the effect of the missile body structure in the flying process, the folding missile wing can reduce the space occupation of the missile body, the folded volume is reduced, the folding missile wing is convenient to place, a camera 21 is installed at the bottom of the warhead 11, a communication data chain mechanism 22 is installed on the other side of the camera 21, a lithium battery used for supplying power is further arranged inside the carbon fiber missile body 1, a sensor used for detecting signals and an information receiving remote control structure used for receiving signals are further arranged, the missile is provided with the camera 21 and the communication data chain mechanism 22, video signals can be transmitted back in real time in the flight process, meanwhile, the fighting part 14 is also arranged, the effect of 'observing and hitting the missile body' can be realized, the operational capacity and the effect of the missile body are improved, the integrated design of ammunition-aircraft is realized, and multiple functions of cruise detection, tracking attack, hovering and the like can be completed.
The working principle is as follows:
the flying-patrol bullet structure made of the integrally compression-molded carbon fiber composite material has the advantages that after a bullet body is reflected, a signal is sent to an information receiving device in the bullet body, the micro motor 27 drives the first folding bullet wing 16 and the second folding bullet wing 19 to simultaneously expand outwards through a transmission structure consisting of the connecting rod 26, the second bevel gear 25, the first bevel gear 24 and the rotating shaft 17, in the flying process, the angle and the flying state of the corresponding missile wing can be adjusted by remotely controlling the single control component 2 to meet the use requirement, the electric motor 13 drives the missile tail rotor 12 to rotate so as to provide pushing power, during the flight of the projectile, the camera 21 and the communication data link mechanism 22 can transmit back video signals in real time during the flight, therefore, the system monitors and checks the range of the flight area, and thus, functions of cruise detection, tracking attack, hovering striking and the like are completed.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides an integral compression molding carbon-fibre composite patrols and flies bullet body structure, includes carbon fiber bullet body (1), warhead (11) and bullet tail, its characterized in that: one end of the carbon fiber bullet body (1) is fixedly connected with a bullet head (11), the other end of the carbon fiber bullet body (1) is fixedly connected with a bullet tail, a propelling device is arranged on the bullet tail and consists of a bullet tail rotor wing (12) and an electric motor (13), the electric motor (13) in transmission connection with the bullet tail rotor wing is arranged on the side face of the bullet tail rotor wing (12), a first placing cavity (15) is formed in the side face of the carbon fiber bullet body (1), a rotatable first folding bullet wing (16) is arranged in the first placing cavity (15), a rotating shaft (17) is fixedly connected to the side face of the first folding bullet wing (16), a second placing cavity (18) is formed in the side face of the first placing cavity (15), a second folding bullet wing (19) is arranged in the second placing cavity (18), and single control assemblies (2) are arranged on the side faces of the first folding bullet wing (16) and the second folding bullet wing (19), the top of the single control assembly (2) is provided with a connecting seat (23), the single control assembly (2) is composed of a first bevel gear (24), a second bevel gear (25), a connecting rod (26) and a micro motor (27), and the bottom end of the rotating shaft (17) penetrates through the connecting seat (23) and is fixedly connected with the first bevel gear (24).
2. The integrally compression-molded carbon fiber composite material flying round bomb structure according to claim 1, wherein: the carbon fiber bullet body (1) is of a cylindrical structure.
3. The integrally compression-molded carbon fiber composite material flying round bomb structure according to claim 1, wherein: the middle part of the carbon fiber bullet body (1) is provided with a warhead (14).
4. The integrally compression-molded carbon fiber composite material flying round bomb structure according to claim 1, wherein: the second bevel gear (25) is meshed with the first bevel gear (24), and the second bevel gear (25) is fixedly connected with the connecting rod (26).
5. The integrally compression-molded carbon fiber composite material flying round bomb structure according to claim 1, wherein: one end of the connecting rod (26) is in transmission connection with an output shaft of the micro motor (27) through a coupler.
6. The integrally compression-molded carbon fiber composite material flying round bomb structure according to claim 1, wherein: the bottom of warhead (11) is installed camera (21), communication data link mechanism (22) is installed to camera (21) other side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120548208.2U CN214792811U (en) | 2021-03-17 | 2021-03-17 | Flying projectile body structure is patrolled to whole compression molding carbon-fibre composite |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202120548208.2U CN214792811U (en) | 2021-03-17 | 2021-03-17 | Flying projectile body structure is patrolled to whole compression molding carbon-fibre composite |
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| CN214792811U true CN214792811U (en) | 2021-11-19 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2796086C1 (en) * | 2022-04-11 | 2023-05-16 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-Морского Флота "Военно-морская академия им. Адмирала Флота Советского Союза Н.Г. Кузнецова" | Rocket glider with homing underwater projectile |
-
2021
- 2021-03-17 CN CN202120548208.2U patent/CN214792811U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2796086C1 (en) * | 2022-04-11 | 2023-05-16 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-Морского Флота "Военно-морская академия им. Адмирала Флота Советского Союза Н.Г. Кузнецова" | Rocket glider with homing underwater projectile |
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