CN210981015U - Small-sized universal vertical launching device for anti-unmanned aerial vehicle - Google Patents
Small-sized universal vertical launching device for anti-unmanned aerial vehicle Download PDFInfo
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- CN210981015U CN210981015U CN201920968431.5U CN201920968431U CN210981015U CN 210981015 U CN210981015 U CN 210981015U CN 201920968431 U CN201920968431 U CN 201920968431U CN 210981015 U CN210981015 U CN 210981015U
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Abstract
The utility model discloses a reverse unmanned aerial vehicle is with small-size general vertical transmitting device, including transmission platform, control box and investigation platform, its characterized in that: the outer surface of the lower end of the launching platform is movably provided with an underframe, a fluid director (thermal launching) can be selectively arranged between the underframe and the launching platform, the middle parts of the outer surfaces of the left side and the right side of the launching platform can be selectively provided with a spare battery, the upper parts of the outer surfaces of the left side and the right side of the launching platform can be selectively provided with a launching power device (cold launching) or a safety fire protection device (thermal launching), and the inside of the launching platform is movably provided with a launching tube. The transmitting device divides the components of the transmitting system into different functional devices according to functions, and the transmitting system for independent operation is composed of two or more functional devices, so that the use and maintenance are simplified, the cost is reduced, the command system is simplified, the platform generalization is realized, and the transmitting device has the advantages of strong compatibility, short transmitting preparation time, unattended capability, multiple function expansion capability, large upgrading potential and the like.
Description
Technical Field
The utility model relates to a transmitting device field specifically is anti-unmanned aerial vehicle is with small-size general vertical transmitting device.
Background
Along with the rapid popularization of unmanned aerial vehicles, more and more people or units own and use the unmanned aerial vehicles, the wide application of the unmanned aerial vehicles also puts forward new requirements on safety and security work, various unmanned aerial vehicle intercepting systems starting from the aspects of safety and anti-terrorism have appeared in the market at present, secondly, various fire extinguishing rocket bomb systems capable of quickly realizing long-distance accurate part fire extinguishing are also appeared in the market for meeting the use requirements of high-rise building fire extinguishing, forest fire fighting and the like, the current various task aircraft application systems form a system, the platforms have numerous and various types, the compatibility among the platforms is poor, information is difficult to interconnect, each subsystem in the platforms form a system, the subsystems with the same functions have no interchangeability, and the operation process is complicated.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
The utility model provides a not enough to prior art, the utility model provides a small-size general vertical transmitting device is used to anti-unmanned aerial vehicle, this small-size general vertical transmitting device is used to anti-unmanned aerial vehicle, divide the component of transmitting system into different functional device according to the function, constitute the transmitting system of independent operation by two or a plurality of functional device, simplify and use the maintenance, reduce and use and the maintenance cost, simplify the commander system, realize the platform universalization, it is strong to possess the compatibility, transmission preparation time is short, multiple usage pattern, possess unmanned on duty ability, multiple auxiliary function expansion ability, possess advantages such as upgrading potentiality. And simultaneously, according to the utility model discloses can be different according to the cold/hot transmission mode of the anti-unmanned aerial vehicle ammunition of transmission, satisfy the requirement through being equipped with different modules (launching power device and being used for cold transmission, safe firebreak device and divertor are used for hot transmission), adaptability is wide.
(II) technical scheme
In order to achieve the above purpose, the utility model discloses a following technical scheme realizes: anti unmanned aerial vehicle is with small-size general vertical transmission device, including transmission platform, control box and investigation platform, its characterized in that: the detection platform and the control box are arranged on the emission platform, the emission platform and the control box are respectively detachably connected with the detection platform, an underframe is movably arranged on the outer surface of the lower end of the emission platform, a fluid director can be selectively installed between the bottom plate and the emission platform (during thermal emission), a standby battery can be selectively installed in the middle of the outer surfaces of the left side surface and the right side surface of the emission platform, an ejection power device (during cold emission) or a safety fire protection device (during thermal emission) can be selectively installed in the upper positions of the outer surfaces of the left side surface and the right side surface of the emission platform, and an emission barrel is movably installed inside the emission platform.
Preferably, the device also comprises a supporting mechanism used for bearing the launching platform, the control box and the investigation platform, the front end and the rear end of the outer surface of the lower end of the supporting block are respectively and movably provided with a supporting leg,
preferably, the transmitting platform and the control box are respectively fixedly provided with a fixing device and a positioning hole or a positioning pin or a positioning block at the front end face and the rear end face connected with the investigation platform and the corner positions of the outer surfaces of the left side and the right side of the transmitting platform, and the outer surfaces of the two sides of the transmitting platform, the control box and the investigation platform are provided with guide grooves or guide blocks.
Preferably, a first battery pack, a first satellite and inertial positioning and orienting device and a first communicator are arranged in the control box, the first battery pack is electrically connected with the first satellite and inertial positioning and orienting device and the first communicator respectively, the first satellite and inertial positioning and orienting device is in signal connection with the first communicator, the first battery pack is connected with a satellite positioning antenna through a transmitting controller, and the first communicator is connected with a first communication antenna.
Preferably, a second battery pack, a second satellite, an inertial positioning and orienting device and a second communicator are arranged inside the investigation platform, the second battery pack is electrically connected with the first satellite, the inertial positioning and orienting device and the second communicator respectively, the first satellite, the inertial positioning and orienting device and the second communicator are in signal connection, a second communication antenna is connected to the second communicator, a detection radar is further arranged inside the investigation platform, and the detection radar is in signal connection with the second communicator.
Preferably, the second communication antenna penetrates through the interior of the investigation platform, the second communication antenna is movably connected with the second communicator, the lower end of the detection radar is movably provided with a lifting mechanism, and the lifting mechanism penetrates through the interior of the investigation platform and is movably connected with the second battery pack.
Preferably, the output end of the second battery pack is electrically connected to the second satellite, the inertial positioning and orienting device, the second communicator and the input end of the detection radar.
(III) advantageous effects
The utility model provides a reverse unmanned aerial vehicle is with small-size general perpendicular transmitting device possesses following beneficial effect:
this anti unmanned aerial vehicle is with small-size general perpendicular transmitting device divides the component of transmitting system into different functional device according to the function, constitutes the transmitting system of independent operation by two or more functional device, simplifies the use and maintains, reduces and uses and the maintenance cost, simplifies the command system, realizes the platform universalization, possesses that the compatibility is strong, transmission preparation time is short, multiple use pattern, possess unmanned on duty ability, multiple auxiliary function expansion ability, possess advantages such as upgrading potentiality.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of another embodiment of the present invention
Fig. 3 is a schematic structural view of the launching platform of the present invention;
FIG. 4 is a schematic structural view of the control box of the present invention;
FIG. 5 is a schematic structural view of the detection platform of the present invention;
fig. 6 is a schematic view of the installation, positioning and fixation of the control box and the launching platform or reconnaissance of the present invention;
FIG. 7 is a diagram of the installation, positioning and fixing of the launching platform and the control box or scout of the present invention;
in the figure: 1. a launch platform; 2. a control box; 3. a detection platform; 4. a support block; 5. a support frame; 6. A chassis; 7. a fluid director; 8. a backup battery; 9. a launch powered device or a safety fire protection device; 10. a launch canister; 11. a fixing device; 12. positioning holes or positioning pins or positioning blocks; 13. a guide slot or guide block; 201. a first battery pack; 202. a first satellite and an inertial positioning and orienting device; 203. a first communicator; 204. a first communication antenna; 205. a launch controller; 206. a satellite positioning antenna; 301. a second battery pack; 302. a second satellite and an inertial positioning and orienting device; 303. a second communicator; 304. a second communication antenna; 305. a lifting mechanism; 306. the radar is detected.
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. 1-7, the present invention provides a technical solution: a small-sized universal vertical launching device for a reverse unmanned aerial vehicle is shown in figure 1-2 and comprises a launching platform 1, a control box 2 and a detection platform 3, wherein the control box 2 is positioned between the detection platform 3 and the launching platform 1, the control box 2 and the detection platform 3 are movably connected, the detection platform 3 and the lower end position of the outer surface of one side of the launching platform 1, which is far away from the control box 2, are movably provided with a supporting mechanism 4, the front end and the rear end of the outer surface of the lower end of the supporting mechanism 4 are respectively provided with a supporting leg 5, the outer surface of the lower end of the launching platform 1 is movably provided with an underframe 6, a fluid director 7 can be selectively arranged between the underframe 6 and the launching platform 1 (during thermal launching), a standby battery 8 is movably arranged at the middle position of the outer surfaces of the left side and the right side of the launching platform 1, and the upper positions of the outer surfaces, the internal of the launching platform 1 is movably provided with a launching tube 10, the launching platform 1 is divided into four launching areas and respectively provided with a plurality of launching tubes 10, each launching area independently conducts gas during thermal launching, each launching tube 10 can be provided with a group of launching tubes 10 according to different diameters of the mission aircraft to form a combination, the leveling of the launching platform 1 can be realized through the supporting mechanism 4, the electric quantity storage is increased through the standby battery 8, and the protection plate 9 has a fireproof function;
as shown in fig. 4, a first battery pack 201 is movably mounted at the lower end inside the control box 2, a first satellite and inertial positioning and orienting device 202, a first communicator 203 and a transmitting controller 205 are movably mounted at the upper position of the first battery pack 201, a first communication antenna 204 is movably mounted on the outer surface of the upper end of the control box 2, a satellite positioning antenna 206 is movably mounted on the outer surface of the upper end of the control box 2, the first communication antenna 204 penetrates through the inside of the control box 2, the first communication antenna 204 is movably connected with the first communicator 203, the satellite positioning antenna 206 is mounted at the top of the control box 2, the satellite positioning antenna 206 is movably connected with the transmitting controller 205, and the output end of the first battery pack 201 is electrically connected with the first satellite and inertial positioning and orienting device 202 and the input end of the first communicator 203;
as shown in fig. 5, a second battery pack 301 is movably mounted at a position close to the front end at the lower end inside the detection platform 3, a second satellite and inertial positioning and orienting device 302 is movably mounted at a position close to the rear end at the lower end inside the detection platform 3, a second communicator 303 is movably mounted on the outer surface of the upper end of the second satellite and inertial positioning and orienting device 302, a second communication antenna 304 is movably mounted on the outer surface of the upper end of the detection platform 3, a detection radar 306 is movably mounted on the outer surface of the upper end of the detection platform 3, a second communication antenna 304 penetrates through the detection platform 3, the second communication antenna 304 is movably connected with the second communicator 303, a lifting mechanism 305 is movably mounted at the lower end of the detection radar 306, the lifting mechanism 305 penetrates through the interior of the detection platform 3 and is movably connected with the second battery pack 301, and the output end of the second battery pack 301 is electrically connected with the second satellite and inertial positioning and orienting device 302, The input terminals of the second communicator 303 and the detection radar 306;
as shown in fig. 6-7, the corner positions of the two outer surfaces of the launching platform 1, the control box 2 and the detection platform 3 are all fixedly provided with a fixing device 11 and a positioning hole or a positioning pin or a positioning block 12, the outer surfaces of the two sides of the launching platform 1, the control box 2 and the detection platform 3 are provided with a guide groove or a guide block 13, the outer surfaces of the two sides of the launching platform 1, the control box 2 and the detection platform 3 are provided with a fixing device 11, a positioning hole or a positioning pin or a positioning block 12 and a guide groove or a guide block 13, which can be conveniently and quickly mechanically connected with other devices, and an electrical/signal interface is left to conveniently and quickly connect with other devices electrically and signals;
through adopting above-mentioned technical scheme, with launching platform 1, control box 2 and investigation platform 3 integration as an organic whole, promoted transmission control system, location orientation, communication device reuse rate, reduce use cost, promote the flexibility of use, promoted firepower density under the prerequisite that realizes the miniaturization, can be accurate, reliable carry out machinery, electric, signal connection with transmission control system, location/communication system.
To sum up, this anti-unmanned aerial vehicle is with small-size general perpendicular emitter, utilize transmission platform 1, control box 2 and investigation platform 3 fixing base 11, locating piece 12 and guide way 13 integration are as an organic whole, transmission control system has been promoted, the location is directional, communication device reuse rate, use cost is reduced, promote and use the flexibility, simultaneously can be convenient, quick and other devices carry out mechanical connection, and it can be convenient to leave electric/signal interface, quick and other devices carry out electric and signal connection, can realize the leveling of transmission platform 1 through supporting shoe 4, through reserve battery 8 increase electric quantity deposit, launch power device (during cold emission) or safe firebreak device (during heat emission) and have the fire prevention function.
A typical usage pattern is as follows: the user passes through communication device and assigns anti-unmanned aerial vehicle task of fighting to control box 2 and launching platform 1, and task information passes through first communicator 203 and transmits for launch controller 205 through the internal data network.
After receiving the task information, the transmission controller 205 issues a scout/capture target instruction to the scout platform through the first communicator 203.
The reconnaissance platform 3 receives the instruction from the transmission controller 205 through the second communicator 303, and starts reconnaissance and searching for the target.
The reconnaissance platform 3 reconnaissance the moving direction of the unmanned aerial vehicle through the detection radar 306, and carries out observation point positioning and orientation through the second satellite and the inertial positioning and orientation device 302.
The reconnaissance platform 3 transmits information from the second communicator 303 to the transmission controller 205 through the first communicator 203 by using the second communication antenna 304, and the transmission controller 205 simultaneously locates itself by the second satellite and the inertial positioning and orienting device 202 and calculates transmission data.
The launching controller 205 transmits launching data bits to the launching platform 1 through internal data connection and issues launching instructions, the launching platform 1 launches the unmanned aerial vehicle interception equipment to intercept the unmanned aerial vehicle through the launching canister 10, the launching platform 1 is divided into four launching areas to respectively place a plurality of launching canisters 10, when a thermal launching mode is adopted, each launching area independently conducts gas discharge and guide, each launching canister 10 can place a group of launching canisters 10 to form a combination body according to different task aircraft diameters, the components of the launching system are divided into different functional devices according to functions, the launching system for independent operation is formed by two or more functional devices, the use and maintenance are simplified, the use and maintenance cost is reduced, the command system is simplified, the platform universalization is realized, the launching controller has strong compatibility, short launching preparation time, multiple use modes, unattended capability and multiple auxiliary function expansion capability, Has the advantages of upgrading potential and the like.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation. The element defined by the sentence "comprising one.. said, does not exclude the presence of additional identical elements in the process, method, article or apparatus comprising said element, the electrical elements presented therein are all electrically connected to an external master and 220V mains, and the master may be a conventionally known apparatus, such as a computer, which acts as a control.
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 (7)
1. Anti unmanned aerial vehicle is with small-size general vertical transmitting device, including launching platform (1), control box (2) and investigation platform (3), its characterized in that: investigation platform (3) with control box (2) all set up on launching platform (1), control box (2) respectively with can dismantle the connection between investigation platform (3), the lower extreme surface movable mounting of launching platform (1) has chassis (6), and movable mounting has divertor (7) between chassis (6) and launching platform (1), the left and right sides surface intermediate position movable mounting of launching platform (1) has spare battery (8), and launches power device or safe firebreak device (9) in the left and right sides surface upper portion position installation of launching platform (1), the inside movable mounting of launching platform (1) has launch section of thick bamboo (10).
2. The small-sized universal vertical launching device for an anti-unmanned aerial vehicle according to claim 1, characterized in that: still including being used for bearing launching platform (1), control box (2) and investigation platform (3) supporting mechanism (4), and supporting mechanism (4) and chassis (6) are movable mounting, and supporting mechanism (4) are installed landing leg (5) that have raising and lowering functions.
3. The small-sized universal vertical launching device for an anti-unmanned aerial vehicle according to claim 1, characterized in that: the device is characterized in that the transmitting platform (1) and the control box (2) are respectively fixedly provided with a fixing device (11) and a positioning hole or a positioning pin or a positioning block (12) at the corner positions of the outer surfaces of the front end face, the rear end face and the left side and the right side of the transmitting platform (1) which are connected with the detecting platform (3), and the outer surfaces of the two sides of the transmitting platform (1), the control box (2) and the detecting platform (3) are provided with guide grooves or guide blocks (13).
4. The small-sized universal vertical launching device for an anti-unmanned aerial vehicle according to claim 1, characterized in that: the control box (2) is internally provided with a first battery pack (201), a first satellite and inertial positioning and orientation device (202) and a first communicator (203), wherein the first battery pack (201) is electrically connected with the first satellite and inertial positioning and orientation device (202) and the first communicator (203), the first satellite and inertial positioning and orientation device (202) is in signal connection with the first communicator (203), the first battery pack (201) is connected with a satellite positioning antenna (206) through a transmitting controller (205), and the first communicator (203) is connected with a first communication antenna (204).
5. The small-sized universal vertical launching device for an anti-unmanned aerial vehicle according to claim 1, characterized in that: the detection platform is characterized in that a second battery pack (301), a second satellite, an inertial positioning and orienting device (302) and a second communicator (303) are arranged inside the detection platform (3), the second battery pack (301) is respectively electrically connected with the second satellite, the inertial positioning and orienting device (302) and the second communicator (303), the second satellite, the inertial positioning and orienting device (302) and the second communicator (303) are in signal connection, a second communication antenna (304) is connected and arranged on the second communicator (303), a detection radar (306) is further arranged inside the detection platform (3), and the detection radar (306) is in signal connection with the second communicator.
6. The small-sized universal vertical launching device for an anti-unmanned aerial vehicle according to claim 5, wherein: the second communication antenna (304) is mounted inside the investigation platform (3), the second communication antenna (304) is movably connected with the second communicator (303), the lower end of the detection radar (306) is movably provided with a lifting mechanism (305), and the lifting mechanism (305) penetrates through the inside of the investigation platform (3) and is movably connected with the second battery pack (301).
7. The small-sized universal vertical launching device for an anti-unmanned aerial vehicle according to claim 5, wherein: the output end of the second battery pack (301) is electrically connected with the input ends of the second satellite, the inertial positioning and orienting device (302), the second communicator (303) and the detection radar (306).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920968431.5U CN210981015U (en) | 2019-06-26 | 2019-06-26 | Small-sized universal vertical launching device for anti-unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920968431.5U CN210981015U (en) | 2019-06-26 | 2019-06-26 | Small-sized universal vertical launching device for anti-unmanned aerial vehicle |
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| CN210981015U true CN210981015U (en) | 2020-07-10 |
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| CN201920968431.5U Active CN210981015U (en) | 2019-06-26 | 2019-06-26 | Small-sized universal vertical launching device for anti-unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110260718A (en) * | 2019-06-26 | 2019-09-20 | 刘峰 | Anti- unmanned plane Small Universal launching tower |
-
2019
- 2019-06-26 CN CN201920968431.5U patent/CN210981015U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110260718A (en) * | 2019-06-26 | 2019-09-20 | 刘峰 | Anti- unmanned plane Small Universal launching tower |
| CN110260718B (en) * | 2019-06-26 | 2024-02-27 | 刘峰 | Anti-unmanned aerial vehicle is with small-size general vertical emission device |
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