CN115384774A - Investigation unmanned aerial vehicle is used in actual combat countermeasure - Google Patents
Investigation unmanned aerial vehicle is used in actual combat countermeasure Download PDFInfo
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- CN115384774A CN115384774A CN202211016051.4A CN202211016051A CN115384774A CN 115384774 A CN115384774 A CN 115384774A CN 202211016051 A CN202211016051 A CN 202211016051A CN 115384774 A CN115384774 A CN 115384774A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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- 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
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- 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
- B64D1/22—Taking-up articles from earth's surface
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- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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Abstract
The invention discloses a detection unmanned aerial vehicle for actual combat countermeasure, which comprises a body, wherein landing supports are arranged at the longitudinal two ends of the bottom of the body, a camera is arranged between the landing supports at the bottom of the body, a sealed access cover is rotatably connected at one transverse end of the top of the body, flight assemblies are arranged on the outer surfaces of the transverse sides and the outer surfaces of the longitudinal sides of the body, first rotating shafts are arranged at the transverse two ends of the body, and a first driving assembly is arranged between the first rotating shafts and the inner surface of the bottom of the body. The invention has the beneficial effects that: the unmanned aerial vehicle monitoring system can effectively avoid monitoring by enemy radars, reduce the probability of being monitored by the enemy radars and greatly improve the cruising ability of the unmanned aerial vehicle; the unmanned aerial vehicle can be effectively prevented from being drenched in rainy days, and damage caused by water entering the unmanned aerial vehicle is avoided; the system can process objects with strategic significance in time and make some striking means with strategic significance in the investigation process.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a reconnaissance unmanned aerial vehicle for actual combat countermeasure.
Background
The unmanned plane is called unmanned plane for short, and is called UAV in English, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The development of unmanned aerial vehicles in China starts in the 70 th 20 th century, and the unmanned aerial vehicles are used as target drone at the earliest. At present, civil aerial photography, line patrol, aerial survey and military investigation and attack unmanned aerial vehicles are various, and different requirements are met. Along with the development of unmanned aerial vehicle technology and the reduction of technical threshold, unmanned aerial vehicle also uses in the actual combat confrontation training of army and investigation gradually.
Chinese patent CN114044123A discloses a large-scale investigation unmanned aerial vehicle with cleaning and protecting functions, which can quickly realize shielding and containing of a supporting frame, effectively prevent rainwater from contacting with an electrical component during maintenance and repair and can generate gas to obliquely blow to a camera, effectively prevent rainwater from shielding the camera to influence investigation effect, and improve investigation quality; however, in the technical scheme of the patent, attention is paid to a camera excessively, and the aim of shooting the reconnaissance ground environment is taken as a main aim, on one hand, the reconnaissance unmanned aerial vehicle has the problem of short endurance, if the reconnaissance distance is too long or the reconnaissance time is too long, the reconnaissance unmanned aerial vehicle cannot return, but if the reconnaissance unmanned aerial vehicle returns, the effective reconnaissance aim cannot be achieved, the reconnaissance use effect is seriously affected, on the other hand, when the reconnaissance unmanned aerial vehicle needs to enter into an enemy area for reconnaissance, the reconnaissance unmanned aerial vehicle is easily monitored by an enemy radar, meanwhile, objects with strategic significance cannot be taken back and cannot be destroyed in the enemy area, and the actual use requirements in actual combat confrontation training and reconnaissance are difficult to achieve.
Disclosure of Invention
In order to solve the problems, the invention provides a detection unmanned aerial vehicle for actual combat countermeasure, which aims to: can improve investigation unmanned aerial vehicle's flight duration, avoid enemy radar monitoring, can also in time handle when the article that the investigation has strategic importance simultaneously.
The invention achieves the above purpose through the following technical scheme: the utility model provides a reconnaissance unmanned aerial vehicle for combat-chemical confrontation, includes the fuselage body, the vertical both ends in fuselage body bottom all are provided with the descending support, fuselage body bottom is located be provided with the camera between the descending support, the horizontal one end swivelling joint in fuselage body top has sealed access cover, the horizontal both sides surface of fuselage body and vertical both sides surface all are provided with flight assembly, the horizontal both ends of fuselage body all are provided with first rotation axis, first rotation axis with be provided with first drive assembly between the fuselage body bottom internal surface, the horizontal both ends below of fuselage body all is provided with the arc guard plate, the vertical both ends of arc guard plate with all set up a plurality of supporting connection boards between the first rotation axis and be connected, be provided with between the descending support and dial the material subassembly, the fuselage body is inside to be located be provided with the battery between the first drive assembly, the vertical one side of battery has set gradually control module, GPS orientation module, signal transceiver module and data storage module along transversely, and the opposite side has set gradually temperature sensor, humidity transducer, smoke transducer and self-destruction module along transversely.
Further, the flight subassembly includes fixed frame, fixed frame one end with fuselage body fixed connection, the other end have the inserting groove, the inserting groove is pegged graft and is had flexible frame, flexible frame one end with be provided with a telescoping device between the inserting groove internal surface, the other end top is provided with a rotating electrical machines, the screw is installed at a rotating electrical machines top.
Further, first drive assembly includes first fluted disc and second rotating electrical machines, first fluted disc sets up at first rotation axis surface, the second rotating electrical machines sets up fuselage body bottom internal surface, first gear is installed to the second rotating electrical machines, first gear with first fluted disc meshes mutually.
Further, the arc guard plate includes the arc body, the vertical both ends of arc body with the supporting connection board is connected, be provided with transparent observation window in the middle of the arc body, arc body circle inside surface is located the vertical both sides of transparent observation window all are provided with solar cell panel, the arc body with the transparent observation window circle outside surface all coats and has the transparent absorbing material of optics, arc body top one end is provided with the sealed pad that the rubber material was made, and the bottom slope is provided with the guide block that the polytetrafluoroethylene material was made.
Further, the group material subassembly is including setting up second rotation axis between the descending support, the second rotation axis both ends are passed the descending support is all installed and is supported the mounting panel, the second rotation axis with it is provided with a plurality of switch boards to support the mounting panel bottom all equidistance, the second rotation axis with be provided with second drive assembly between the descending between the top.
Further, second drive assembly includes second fluted disc and third rotating electrical machines, the second fluted disc sets up at second rotation axis surface, the third rotating electrical machines sets up descending support upper portion, the second gear is installed to the third rotating electrical machines, the second gear with the meshing of second fluted disc mutually.
Further, it is provided with a plurality of throwing mechanisms to support mounting panel top equidistance, throwing mechanism includes the fixed support board, fixed support board one end with the support mounting panel is connected, the fixed support board has rectangular hole, fixed support board one side is located rectangular hole below is provided with the second telescoping device, the second telescoping device passes the fixed support board installs the slip backup pad, the slip backup pad with the support mounting panel is sliding connection, slip backup pad one end is provided with the arc limiting plate, arc limiting plate one end swivelling joint has the grafting limiting plate, grafting limiting plate one end with the fixed support board plug-in connection, the fixed support board is close to arc limiting plate one side is provided with limit clamp, and the opposite side is provided with the lift backup pad, limit clamp with be located between the lift backup pad rectangular hole inboard is provided with the lift connecting plate, the lift backup pad is located all the support screw rod has been pegged graft to the second telescoping device both sides, support screw rod bottom with support mounting panel fixed connection, the support screw rod is located support mounting panel with all be provided with the spring between the lift backup pad, the support screw rod is located there is fixed regulation nut lifting support backup pad top threaded connection, the arc limiting plate is located the function bullet.
Further, a supporting bearing seat is arranged between the first rotating shaft and the machine body and between the second rotating shaft and the descending support.
Furthermore, temperature sensor, humidity transducer and smoke transducer one end all stretch out the fuselage body and install monitor.
Furthermore, the outer surface of the material poking plate and the circular inner surface of the arc limiting plate are both provided with anti-skidding protective layers supported by rubber materials.
Compared with the prior art, the invention has the beneficial effects that:
1. the investigation unmanned aerial vehicle provided by the invention not only can detect scene pictures of a target area, but also can monitor the specific environmental state of the target area, and meanwhile, the investigation unmanned aerial vehicle can be remotely controlled to self-destruct even if being paid by an enemy, so that the enemy is prevented from acquiring important data;
2. the arc-shaped protection plate rotates to the lower side of the body under the matching of the first driving assembly and the first rotating shaft, monitoring of an enemy radar can be effectively avoided through the optical transparent wave-absorbing material coated on the outer surface of the circle, the probability of being monitored by the enemy radar is reduced, the solar cell panel arranged on the inner surface of the circle can continuously charge the storage battery through absorbing solar energy, the cruising ability of the unmanned aerial vehicle is greatly improved, and meanwhile, the observation window can ensure normal detection of the camera;
3. the arc-shaped protection plate rotates to the position above the body of the unmanned aerial vehicle under the matching of the first driving assembly and the first rotating shaft, and the matched sealing gasket can effectively prevent the unmanned aerial vehicle from being exposed to rain in rainy weather and prevent the unmanned aerial vehicle from being damaged due to water inflow inside the unmanned aerial vehicle;
4. when an object with small strategic significance is encountered in the detection process, the two arc-shaped protection plates can be controlled to be clamped and taken back through the first driving assembly and the first rotating shaft, the arranged guide blocks are more convenient for clamping the object, and the object is poked and moved to the upper part of the inward surface of the arc-shaped protection plates in cooperation with the arranged poking assembly, so that the object is prevented from being dropped and deformed or damaged when being clamped between the arc-shaped protection plates for a long time;
5. when articles with large strategic significance are inconvenient to bring back or other strategic requirements are met in the investigation process, the arc-shaped protection plate is adjusted to one side of the rack body through the matching of the first driving assembly and the first rotating shaft, the second driving assembly can drive the throwing assembly to rotate to the position below the second rotating shaft, and the required strategic purpose is achieved by throwing the corresponding functional bullets through the throwing assembly;
6. put in the subassembly through control second telescoping device drive slip backup pad in the subassembly of setting and advance, the grafting limiting plate can leave fixed support plate, the function bullet also can be kept away from to the arc limiting plate, and the function bullet that carries can be put in away, the arc limiting plate through setting up, spacing clamp plate, the lift backup pad, the lift connecting plate, supporting screw, spring and fixed adjusting nut cooperate, not only can realize carrying the function bullet of different size and size, can also compress tightly spacingly to the function bullet, guarantee that it carries the stability of in-process firm.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a front view of the present invention;
FIG. 3 is a top view of the present invention;
FIG. 4 isbase:Sub>A schematic cross-sectional view taken along A-A of FIG. 2;
FIG. 5 is an enlarged view of portion B of FIG. 3;
FIG. 6 is an enlarged view of portion C of FIG. 4;
FIG. 7 is a cross-sectional schematic view of a flying assembly of the present invention;
FIG. 8 is a schematic perspective view of an arc-shaped fender according to the present invention;
fig. 9 is a schematic perspective view of the dispensing mechanism of the present invention.
In the figure: the self-destruction type aircraft comprises an aircraft body 1, a landing support 2, a camera 3, a sealed access cover 4, a flying assembly 5, a first rotating shaft 6, a first driving assembly 7, an arc-shaped protection plate 8, a support connecting plate 9, a material stirring assembly 10, a storage battery 11, a control module 12, a GPS positioning module 13, a signal transceiving module 14, a data storage module 15, a temperature sensor 16, a humidity sensor 17, a smoke sensor 18 and a self-destruction module 19, wherein the aircraft body 2 is a main body of the aircraft, and the self-destruction type aircraft is a main body of the aircraft;
501-a fixed frame, 502-an inserting groove, 503-a telescopic frame, 504-a first telescopic device, 505-a first rotating motor and 506-a propeller;
701-a first fluted disc, 702-a second rotating motor and 703-a first gear;
801-arc plate body, 802-transparent observation window, 803-solar panel, 804-sealing pad and 805-guide block;
1001-a second rotating shaft, 1002-a supporting mounting plate, 1003-a material poking plate, 1004-a second driving assembly and 1005-a throwing mechanism;
10041-a second fluted disc, 10042-a third rotating motor and 10043-a second gear;
10051-fixed supporting plate, 10052-elongated hole, 10053-second telescopic device, 10054-sliding supporting plate, 10055-arc limiting plate, 10056-inserting limiting plate, 10057-limiting pressing plate, 10058-lifting supporting plate, 10059-lifting connecting plate, 100510-supporting screw, 100511-spring, 100512-fixed adjusting nut and 100513-functional spring.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
Referring to fig. 1 to 5, a detection unmanned aerial vehicle for combat-chemical confrontation comprises a body 1, landing supports 2 are arranged at the longitudinal two ends of the bottom of the body 1, a camera 3 is arranged between the landing supports 2 at the bottom of the body 1, a sealed access cover 4 is rotatably connected to the transverse end of the top of the body 1, flight assemblies 5 are arranged on the outer surfaces of the transverse two sides and the outer surfaces of the longitudinal two sides of the body 1, first rotating shafts 6 are arranged at the transverse two ends of the body 1, first driving assemblies 7 are arranged between the first rotating shafts 6 and the inner surface of the bottom of the body 1, arc protection plates 8 are arranged below the transverse two ends of the body 1, a plurality of support connection plates 9 are arranged between the longitudinal two ends of the arc protection plates 8 and the first rotating shafts 6, a material poking assembly 10 is arranged between the landing supports 2, a storage battery 11 is arranged between the first driving assemblies 7 inside the body 1, a control module 12 is arranged on one longitudinal side of the storage battery 11 in sequence along the transverse direction, a GPS positioning module 13, a signal transceiver module 14 and a data storage module 15, a temperature sensor 16 is arranged on the other side in sequence along the transverse direction, a humidity sensor 17, a smoke sensor 18 and a self-destroying module 19.
As shown in fig. 7, the flying assembly 5 includes a fixed frame 501, one end of the fixed frame 501 is fixedly connected with the fuselage body 1, the other end is provided with an insertion groove 502, the insertion groove 502 is inserted with a telescopic frame 503, a first telescopic device 504 is arranged between one end of the telescopic frame 503 and the inner surface of the insertion groove 502, the top of the other end is provided with a first rotating motor 505, and the top of the first rotating motor 505 is provided with a propeller 506; wherein the first telescoping device 504 that sets up can drive flexible frame 503 and advance or retreat for the holistic length of control adjustment flight subassembly 5, when first telescoping device 504 drove the flexible machine 503 and advances, can control the whole centrobaric relative position of adjustment unmanned aerial vehicle, make unmanned aerial vehicle flight in-process can be more stable, when the first telescoping device 504 that sets up drove flexible machine 503 and retreats, can be convenient for first drive assembly 7 drives the arc guard plate 8 rotation smoothly under the cooperation of first rotation axis 6 and supporting connection board 9.
As shown in fig. 5, the first driving assembly 7 includes a first gear 701 and a second rotating electrical machine 702, the first gear 701 is disposed on an outer surface of the first rotating shaft 6, the second rotating electrical machine 702 is disposed on an inner surface of a bottom of the main body 1, the second rotating electrical machine 702 is mounted with a first gear 703, and the first gear 703 is engaged with the first gear 701; wherein it is rotatory to drive first gear 703 through second rotating electrical machines 702, because first gear 703 meshes with first fluted disc 701 mutually, so first fluted disc 701 follows rotatoryly, and then realize driving first rotation axis 6 rotatory, under the cooperation of supporting connection board 9, finally realize driving the rotatory state to different states of arc antiskid ribbed tile 8, wherein, second rotating electrical machines 702 chooses for use the motor that has the brake, can reduce the load that second rotating electrical machines 702 bore under the stall rotation state by a wide margin, improve second rotating electrical machines 702's life.
As shown in fig. 8, the arc-shaped protection plate 8 includes an arc-shaped plate body 801, two longitudinal ends of the arc-shaped plate body 801 are connected with the support connection plate 9, a transparent observation window 802 is arranged in the middle of the arc-shaped plate body 801, the circular inner surface of the arc-shaped plate body 801 is located at two longitudinal sides of the transparent observation window 802 and is provided with a solar cell panel 803, the circular outer surfaces of the arc-shaped plate body 801 and the transparent observation window 802 are coated with an optically transparent wave-absorbing material, a sealing pad 804 made of a rubber material is arranged at one end of the top of the arc-shaped plate body 801, and a guide block 805 made of a polytetrafluoroethylene material is obliquely arranged at the bottom of the arc-shaped plate body 801; when two arc-shaped plate bodies 801 in the unmanned aerial vehicle rotate to the position below the machine body 1 and guide blocks 805 arranged at one ends of the bottoms of the two arc-shaped plate bodies 801 are in contact with each other, an optically transparent wave-absorbing material coated on the outer surface of a circle can effectively avoid monitoring by an enemy radar, the probability of being monitored by the enemy radar is reduced, wherein the optically transparent wave-absorbing material is any one of transparent conductive high polymer or circuit simulation type wave-absorbing materials, a solar cell panel arranged on the inner surface of the circle can continuously charge a storage battery by absorbing solar energy, the cruising ability of the unmanned aerial vehicle is greatly improved, and meanwhile, a viewing window is arranged to ensure normal detection of a camera; the two arc-shaped plate bodies 801 rotate to the upper side of the machine body 1, when the sealing gaskets 804 arranged at one ends of the tops of the two arc-shaped plate bodies 801 are in mutual contact, the unmanned aerial vehicle can be prevented from being exposed to rain in rainy weather, the damage caused by water entering the interior of the unmanned aerial vehicle can be avoided, and meanwhile when the arc-shaped plate bodies 801 achieve a rain shielding effect, the unmanned aerial vehicle should stop flying and land in a relatively safe area to shield rain by matching the two arc-shaped plate bodies 801 with the sealing gaskets 804; in addition, the arc-shaped plate body 801 can also play a certain role in protecting the whole unmanned aerial vehicle, when the unmanned aerial vehicle collides, the collision with the arc-shaped plate body 801 is generated at first, so that the serious damage to important components such as the flight assembly 5 and the fuselage body 1 in the unmanned aerial vehicle is avoided, and the loss caused by collision is reduced; when meeting the article that have strategic importance less in the investigation process, can realize controlling two arc guard plates 8 through first drive assembly 7 and first rotation axis 6 and take it back in with its clamp, the guide block 805 that wherein sets up is convenient for article clamp more and is got, is convenient for further to enemy situation and carries out the analysis.
As shown in fig. 6, the kick-out assembly 10 includes a second rotating shaft 1001 disposed between the descending brackets 2, a supporting mounting plate 1002 is mounted at both ends of the second rotating shaft 1001 through the descending brackets 2, a plurality of kick-out plates 1003 are disposed at the bottom of the second rotating shaft 1001 and the supporting mounting plate 1002 at equal intervals, and a second driving assembly 1004 is disposed between the second rotating shaft 1001 and the top of the descending brackets 2; the switch plate 1003 that sets up realizes dialling to pressing from both sides the article of getting between arc guard plate 8 under second drive assembly's drive and moves for article move to 8 circles of arc guard plate on the internal surface upper portion, avoid article to add for a long time to hold and drop the deformation, press from both sides bad or the centre gripping unstability drops between arc guard plate 8.
The second driving assembly 1004 includes a second gear 10041 and a third rotary motor 10042, the second gear 10041 is disposed on the outer surface of the second rotary shaft 1001, the third rotary motor 10042 is disposed on the upper portion of the drop bracket 2, the third rotary motor 10042 is mounted with a second gear 10043, and the second gear 10043 is engaged with the second gear 10041; the third rotary motor 10042 drives the second gear 10043 to rotate, and the second gear 10043 is engaged with the second gear 10041, so that the second gear 10041 drives the second rotary shaft 1001 to rotate.
As shown in fig. 9, a plurality of dropping mechanisms 1005 are equidistantly arranged on the top of the supporting and mounting plate 1002, the dropping mechanisms 1005 include a fixed support plate 10051, one end of the fixed support plate 10051 is connected to the supporting and mounting plate 1002, the fixed support plate 10051 has a strip hole 10052, one side of the fixed support plate 10051 is located below the strip hole 10052 and is provided with a second retractor 10053, the second retractor 10053 passes through the fixed support plate 10051 and is provided with a sliding support plate 10054, the sliding support plate 10054 is slidably connected to the supporting and mounting plate 1002, one end of the sliding support plate 10054 is provided with an arc-shaped limit plate 10055, one end of the arc-shaped limit plate 10055 is rotatably connected with an insertion limit plate 10056, one end of the insertion limit plate 10056 is inserted and connected to the fixed support plate 10051, one side of the fixed support plate 10051 close to the arc-shaped limit pressure plate 10057 is provided with the lifting and mounting plate 1002, a lifting and connecting plate 10059 is located inside the strip hole 10052 between the limit pressure plate 10057 and the lifting support plate 10058, the lifting and the lifting support plate 10058 is provided with a lifting and is inserted with a supporting screw 100510, the lifting and is inserted to the lifting screw 100510 located on both sides of the second retractor 10053, the lifting support plate 100510, the lifting screw 100510 is located above the lifting and the lifting screw 10055, the lifting support plate 100510, the lifting and the lifting screw 100510 is located above the lifting screw 10055, the lifting spring 100510, the lifting adjustment spring 100510 is located above the fixed support plate 100510, the lifting screw 100510, the lifting adjustment spring 100510 is located above the lifting screw 10055, the lifting adjustment spring 10055; the second retractor device 10053 drives the sliding support plate 10054 to advance, the functional bullet 100513 is placed between the arc-shaped limit plate 10055 and the fixed support plate 10051, then the functional bullet 100513 is pressed against the limit pressure plate 10057, the inserting limit plate 10056 is perpendicular to the fixed support plate 10051, then the second retractor device 10053 is controlled to drive the sliding support plate 10054 to retreat, the inserting limit plate 10056 is connected with the fixed support plate 10051 in an inserting manner, thus the functional bullets 100513 with different sizes can be carried, and in the process of carrying in flight, the limit pressure plate 10057 can be passed through, the lifting support plate 10058, the lifting connection plate 10059, the support screw 100510, the spring 100511 and the fixed adjustment nut 100512 realize the fixed limit of the functional bullet 100513, the position stability of the functional bullet in the process of carrying in flight is ensured, meanwhile, the releasing is very convenient when the sliding support plate is performed, the arc-shaped support plate 1008 is driven to rotate to two sides of the body 1 by the first driving assembly 7, the second driving assembly 1004 to drive the releasing mechanism 1005 to rotate to the lower part of the second rotating shaft 1001, the sliding support plate 10054 is controlled without the pushing device 53, the pushing force of the fixed spring 10056 and the fixed support plate 10058 is also can be applied to the lower limit pressure plate 10056, the lower limit pressure plate 10058, the lower limit pressure plate 10056 is applied to the lower limit pressure plate 10058, the lower limit plate 10058 and the lower limit plate 10058, the fixed support plate 10058 is also can be applied conveniently; wherein the functional bomb 100513 is any one of a killer bomb, a burning bomb, a flash bomb and a tear bomb.
Supporting bearing seats are arranged between the first rotating shaft 6 and the machine body 1 and between the second rotating shaft 1001 and the descending bracket 2, so that the first rotating shaft 6 and the second rotating shaft 1001 can rotate smoothly; one ends of the temperature sensor 16, the humidity sensor 17 and the smoke sensor 18 extend out of the machine body 1 and are provided with monitoring probes, so that the environment state of a target area can be monitored more truly; the antiskid protective layer that switch board 1003 surface and arc limiting plate 10054 circle are all provided with the rubber material and support guarantees to press from both sides the integrity of getting article outward appearance, avoids shifting the in-process at article and is scratched or the fish tail surface to and further guarantee that function bullet 100513 is carrying the stability of in-process, avoid its easy production displacement.
The unmanned aerial vehicle comprises a camera 3, a storage battery 11, a GPS positioning module 13, a signal transceiving module 14, a data storage module 15, a temperature sensor 16, a humidity sensor 17, a smoke sensor 18, a self-destruction module 19, a first telescopic device 504, a first rotating motor 505, a second rotating motor 702, a solar cell panel 803, a third rotating motor 10042 and a second telescopic device 10053, wherein the camera 3, the GPS positioning module 13, the signal transceiving module 14, the data storage module 15, the temperature sensor 16, the humidity sensor 17 and the smoke sensor 18 are electrically connected with a control module 12, so that the unmanned aerial vehicle is integrally powered through the storage battery 11 and the solar cell panel 803, and the working states of the camera 3, the GPS positioning module 13, the signal transceiving module 14, the data storage module 15, the temperature sensor 16, the humidity sensor 17 and the smoke sensor 18 are received, and the first telescopic device 504, the first rotating motor 505, the second rotating motor 702, the third rotating motor 10042 and the second telescopic device 10053 are controlled, wherein the first telescopic device 504 and the second telescopic device 10053 are any one of an air cylinder, an electric telescopic rod or an electric push rod, the first rotating motor 505, the second rotating motor 702 and the third rotating motor 10042 are controlled in starting and stopping directions; the outer surface of the fixed adjusting nut 100512 is provided with anti-skidding threads, so that the operation and the adjustment are convenient, and the phenomenon of skidding in the operation and the adjustment process is avoided; fuselage body 1 and arc body 801 are made for any one material in carbon fiber or the polytetrafluoroethylene material, select according to design cost and user demand, and the purpose is in order to reduce whole weight, improves duration, and transparent observation window 802 then adopts the acrylic ester plastic material to make, guarantees the good nature in investigation effect field of vision.
The working principle is as follows: during the use, install corresponding function bullet according to the strategic demand on input mechanism earlier, then can drive unmanned aerial vehicle whole take off to go to the target area through the flight subassembly and reconnoiter, the state of flight and the reconnoiter in-process arc guard plate adjust to the below of fuselage body, the guide block that sets up until two arc guard plate bottoms contact, can avoid enemy radar monitoring through the transparent absorbing material of arc guard plate and transparent observation window outer surface setting like this in flight and reconnoiter, reduce the probability of being monitored by enemy radar, and the solar cell panel that arc guard plate internal surface set up can absorb solar energy under the sunshine, convert into the electric energy and save in the battery, for wholly supply power to unmanned aerial vehicle, improve unmanned aerial vehicle's duration, and the camera can reconnoiter through the transparent observation window that sets up, can not disturb and influence normal reconnoiter demand, when meeting the rainfall, the unmanned aerial vehicle stops flying, in the region of relative safety, adjust two arc guard plates to the top of fuselage body, when two sealed pad contact position simultaneously when unmanned aerial vehicle produces the collision, the arc guard plate that can also avoid some important parts to receive direct impact, when reducing the tactics, can pass through the control of the arc protection plate, it and can pass through the function bullet, it and can not be selected to carry out the control to pass through the back to the inner side of the back to the protection plate.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (10)
1. The utility model provides an combat ization is reconnaissance unmanned aerial vehicle for confrontation, includes fuselage body (1), the vertical both ends in fuselage body (1) bottom all are provided with descending support (2), fuselage body (1) bottom is located be provided with camera (3) between descending support (2), the horizontal one end swivelling joint in fuselage body (1) top has sealed access cover (4), its characterized in that: fuselage body (1) horizontal both sides surface and vertical both sides surface all are provided with flight assembly (5), fuselage body (1) horizontal both ends all are provided with first rotation axis (6), first rotation axis (6) with be provided with first drive assembly (7) between fuselage body (1) bottom internal surface, fuselage body (1) horizontal both ends below all is provided with arc guard plate (8), arc guard plate (8) vertical both ends with all set up a plurality of supporting connection board (9) between first rotation axis (6) and be connected, it dials material subassembly (10) to be provided with between descending support (2), fuselage body (1) is inside to be located be provided with battery (11) between first drive assembly (7), vertical one side of battery (11) is along transversely having set gradually control module (12), GPS orientation module (13), signal transceiver module (14) and data storage module (15), and the opposite side is along transversely having set gradually temperature sensor (16), humidity transducer (17), smoke transducer (18) and self-destruction module (19).
2. The investigation unmanned aerial vehicle for combat chemical defense according to claim 1, characterized in that the flying assembly (5) comprises a fixed frame (501), one end of the fixed frame (501) is fixedly connected with the body (1), the other end of the fixed frame is provided with an insertion groove (502), the insertion groove (502) is inserted with a telescopic frame (503), a first telescopic device (504) is arranged between one end of the telescopic frame (503) and the inner surface of the insertion groove (502), the top of the other end of the telescopic frame is provided with a first rotating motor (505), and the top of the first rotating motor (505) is provided with a propeller (506).
3. The unmanned aerial vehicle for investigation for combat chemical countermeasure according to claim 1, wherein the first driving assembly (7) comprises a first fluted disc (701) and a second rotating electrical machine (702), the first fluted disc (701) is disposed on the outer surface of the first rotating shaft (6), the second rotating electrical machine (702) is disposed on the inner surface of the bottom of the fuselage body (1), the second rotating electrical machine (702) is provided with a first gear (703), and the first gear (703) is engaged with the first fluted disc (701).
4. The investigation unmanned aerial vehicle for actual combat chemical confrontation of claim 1, wherein the arc-shaped protection plate (8) comprises an arc-shaped plate body (801), the longitudinal two ends of the arc-shaped plate body (801) are connected with the supporting and connecting plate (9), a transparent observation window (802) is arranged in the middle of the arc-shaped plate body (801), the circular inner surface of the arc-shaped plate body (801) is located on the longitudinal two sides of the transparent observation window (802), solar cell panels (803) are arranged on the circular outer surfaces of the arc-shaped plate body (801) and the transparent observation window (802) respectively, an optical transparent wave-absorbing material is coated on the circular outer surfaces of the arc-shaped plate body (801), a sealing pad (804) made of a rubber material is arranged at one end of the top of the arc-shaped plate body (801), and a guide block (805) made of a polytetrafluoroethylene material is obliquely arranged at the bottom of the arc-shaped plate body.
5. The unmanned aerial vehicle for investigation of actual combat chemical confrontation according to claim 1, wherein the material stirring component (10) comprises a second rotating shaft (1001) arranged between the landing brackets (2), both ends of the second rotating shaft (1001) penetrate through the landing brackets (2) and are provided with supporting mounting plates (1002), a plurality of stirring plates (1003) are arranged at the bottoms of the second rotating shaft (1001) and the supporting mounting plates (1002) at equal intervals, and a second driving component (1004) is arranged between the second rotating shaft (1001) and the top of the landing bracket (2).
6. The unmanned aerial vehicle for investigation of combat chemical defense according to claim 5, wherein the second driving assembly (1004) comprises a second fluted disc (10041) and a third rotating motor (10042), the second fluted disc (10041) is disposed on the outer surface of the second rotating shaft (1001), the third rotating motor (10042) is disposed on the upper portion of the descending support (2), the third rotating motor (10042) is installed with a second gear (10043), and the second gear (10043) is meshed with the second fluted disc (10041).
7. The unmanned aerial vehicle for investigation of combat chemical defense as claimed in claim 5, wherein the top of the supporting mounting plate (1002) is equidistantly provided with a plurality of throwing mechanisms (1005), the throwing mechanisms (1005) comprise a fixed support plate (10051), one end of the fixed support plate (10051) is connected with the supporting mounting plate (1002), the fixed support plate (10051) is provided with a long hole (10052), one side of the fixed support plate (10051) is located below the long hole (10052) and is provided with a second retractor (10053), the second retractor (10053) passes through the fixed support plate (10051) and is provided with a sliding support plate (10054), the sliding support plate (10054) is in sliding connection with the supporting mounting plate (10052), one end of the sliding support plate (10054) is provided with an arc-shaped limit plate (10055), one end of the arc-shaped limit plate (10055) is rotatably connected with an inserting limit plate (10056), one end of the inserting limit plate (10056) is inserted and connected with the fixed support plate (10051), one end of the fixed support plate (10051) is adjacent to one side of the arc-shaped limit plate (10055) is provided with an elevating limit plate (10058), the other side of the lifting limit plate (10058) is located between the lifting limit plate (10058) and the lifting limit plate (10058) is located inside the lifting support plate (10059), lifting support board (10058) are located second telescoping device (10053) both sides are all pegged graft and are had supporting screw (100510), supporting screw (100510) bottom with support mounting panel (1002) fixed connection, supporting screw (100510) are located supporting mounting panel (1002) with all be provided with spring (100511) between lifting support board (10058), supporting screw (100510) are located lifting support board (10058) top threaded connection has fixed adjusting nut (100512), arc limiting plate (10055) are located limiting pressure plate (10057) with be provided with function bullet (100513) between grafting limiting plate (10057).
8. The unmanned aerial vehicle for investigation for actual combat chemical confrontation according to claim 5, wherein supporting bearing seats are arranged between the first rotating shaft (6) and the fuselage body (1) and between the second rotating shaft (1001) and the landing support (2).
9. The unmanned aerial vehicle for investigation of actual combat chemical confrontation as claimed in claim 1, wherein one end of the temperature sensor (16), one end of the humidity sensor (17) and one end of the smoke sensor (18) extend out of the main body (1) of the unmanned aerial vehicle, and are provided with monitoring probes.
10. The unmanned aerial vehicle for investigation of actual combat chemical countermeasure according to claim 7, wherein the outer surface of the kick-out plate (1003) and the inner circular surface of the arc-shaped limit plate (10054) are both provided with anti-skid protective layers supported by rubber.
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