CN108995809B - Unmanned aerial vehicle device of jettisoning - Google Patents
Unmanned aerial vehicle device of jettisoning Download PDFInfo
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- CN108995809B CN108995809B CN201810834037.2A CN201810834037A CN108995809B CN 108995809 B CN108995809 B CN 108995809B CN 201810834037 A CN201810834037 A CN 201810834037A CN 108995809 B CN108995809 B CN 108995809B
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- 230000007246 mechanism Effects 0.000 claims abstract description 10
- 230000005611 electricity Effects 0.000 claims description 2
- 108010066057 cabin-1 Proteins 0.000 description 78
- 230000000694 effects Effects 0.000 description 7
- 238000003780 insertion Methods 0.000 description 6
- 230000037431 insertion Effects 0.000 description 6
- 230000005484 gravity Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000011435 rock Substances 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
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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
- B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
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- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C19/00—Hand fire-extinguishers in which the extinguishing substance is expelled by an explosion; Exploding containers thrown into the fire
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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
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- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides an unmanned aerial vehicle bomb-throwing device, which belongs to the technical field of fire-fighting equipment and comprises a bomb-throwing cabin for loading fire-extinguishing bombs, wherein the bomb-throwing cabin is spliced with a body of the unmanned aerial vehicle, the top of the bomb-throwing cabin is provided with an opening, the bottom of the bomb-throwing cabin is provided with a movable bottom cover, and the bomb-throwing cabin is provided with a cover opening mechanism for opening the movable bottom cover. The invention provides an unmanned aerial vehicle bomb-throwing device, wherein a bomb-throwing cabin for throwing fire extinguishing bombs is directly inserted into an unmanned aerial vehicle body and connected with the unmanned aerial vehicle body into a whole, the fire extinguishing bombs are contained in an inner cavity of the bomb-throwing cabin, the unstable flight of the unmanned aerial vehicle caused by the shaking of the fire extinguishing bombs is avoided, a movable bottom cover is arranged at the bottom of the bomb-throwing cabin, the movable bottom cover can be opened and closed relative to the bomb-throwing cabin, and the fire extinguishing bombs are thrown after the movable bottom cover is.
Description
Technical Field
The invention belongs to the technical field of fire-fighting equipment, and particularly relates to an unmanned aerial vehicle missile throwing device.
Background
The existing fire extinguishing mode of the unmanned aerial vehicle is that the unmanned aerial vehicle hangs the fire extinguishing bomb through the suspension cable to be thrown above the fire point, and the fire extinguishing bomb has certain mass, and the suspension cable between the fire extinguishing bomb and the unmanned aerial vehicle is unstable, so that the fire extinguishing bomb is easy to shake, and the flight stability of the unmanned aerial vehicle is influenced.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle bomb throwing device to solve the technical problem that in the prior art, a fire extinguishing bomb is not stably hung.
In order to achieve the purpose, the invention adopts the technical scheme that: the utility model provides an unmanned aerial vehicle device of throwing, is including the throwing cabin that is used for loading the fire extinguishing bomb, throw the bullet cabin and peg graft with the unmanned aerial vehicle fuselage, throw the opening in cabin top, the bottom is equipped with movable bottom, throw the bullet cabin and be equipped with and be used for opening the mechanism of uncapping of activity bottom.
Further, the top of throwing the bullet cabin is equipped with the unmanned aerial vehicle fuselage or with the last plug connector of adjacent bullet cabin butt joint, the bottom of throwing the bullet cabin and unmanned aerial vehicle fuselage bottom all be equipped with the fixed sign indicating number of going up the plug connector grafting, the lateral wall of throwing the bullet cabin is equipped with and is used for connecting adjacent two the side plug connector of throwing the bullet cabin.
Further, go up the plug connector and be a plurality of setting and be in throw the picture peg at missile bay top, the picture peg all be equipped with be used for with the socket that the fixed code was pegged graft, the opening orientation of socket is unanimous.
Furthermore, the top of the side wall of each missile throwing cabin is provided with a locking pin for locking two adjacent missile throwing cabins, and the bottom of the unmanned aerial vehicle body and the bottom of the side wall of each missile throwing cabin are provided with pin holes matched with the locking pins.
Further, the locking pin is an indexing pin, and the side wall of the locking pin is provided with an anti-slip structure.
Further, the side plug-in components include tenon and tongue-and-groove mutually supporting, the tenon with the tongue-and-groove symmetry set up in throw the lateral wall of magazine.
Furthermore, the uncovering mechanism comprises a support rod arranged below the movable bottom cover and used for supporting the movable bottom cover, a servo motor arranged on the side wall of the projectile shooting cabin and used for driving the support rod, and one end of the support rod is vertically arranged at the end part of an output shaft of the servo motor.
Further, the unmanned aerial vehicle fuselage is equipped with and is used for controlling servo motor's controller, servo motor pass through the wire with the controller electricity is connected.
Further, one end of the movable bottom cover is hinged with the bottom of the side wall of the projectile shooting cabin.
Furthermore, a hinge is arranged at the edge of the movable bottom cover, one hinge arm of the hinge is fixed on the movable bottom cover, and the other hinge arm of the hinge is fixed on the inner side of the side wall of the projectile shooting cabin.
The unmanned aerial vehicle missile throwing device provided by the invention has the beneficial effects that: compared with the prior art, the unmanned aerial vehicle projectile throwing device has the advantages that the projectile throwing cabin for throwing the fire extinguishing bomb is directly inserted into the unmanned aerial vehicle body and is connected with the unmanned aerial vehicle body into a whole, the fire extinguishing bomb is contained in the inner cavity of the projectile throwing cabin, the situation that the unmanned aerial vehicle is unstable in flight due to the fact that the fire extinguishing bomb is suspended below the unmanned aerial vehicle is avoided, the movable bottom cover is arranged at the bottom of the projectile throwing cabin and can be opened and closed relative to the projectile throwing cabin, the fire extinguishing bomb is loaded into the projectile throwing cabin after the movable bottom cover is opened, then the movable bottom cover is closed, the unmanned aerial vehicle loaded with the fire extinguishing bomb flies above a fire point, the movable bottom cover is opened, the fire extinguishing bomb slides down from the projectile throwing cabin.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive exercise.
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle missile launching device provided by an embodiment of the invention;
FIG. 2 is a view taken along the line A in FIG. 1;
fig. 3 is a schematic view of vertical connection of a missile cabin of the unmanned aerial vehicle missile device provided by the embodiment of the invention;
fig. 4 is an enlarged view at B in fig. 3;
fig. 5 is a schematic diagram of transverse connection of a missile cabin of the missile launching device of the unmanned aerial vehicle provided by the embodiment of the invention;
fig. 6 is a schematic view of a bottom structure of an unmanned aerial vehicle of the unmanned aerial vehicle missile throwing device provided by the embodiment of the invention;
wherein, in the figures, the respective reference numerals:
1-a projectile shooting cabin; 2-moving the bottom cover; 3, inserting a plate; 4-fixed code; 5-fixing the lug plate; 6-locking pin; 7-index pin ear plate; 8-pin holes; 9-pin hole ear plate; 10-a support rod; 11-a servo motor; 12-a tenon; 13-mortises; 14-connecting the bottom plate; 15-fixing the bolt.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects to be solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.
It will be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship indicated in the drawings that is solely for the purpose of facilitating the description and simplifying the description, and 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 is therefore not to be construed as limiting the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "plurality" or "a plurality" means two or more unless specifically defined otherwise.
Referring to fig. 1 to 6 together, the unmanned aerial vehicle missile throwing device provided by the invention will be described. Unmanned aerial vehicle device of throwing bomb, including the cabin of throwing bomb 1 that can interconnect, the cabin of throwing bomb 1 can be pegged graft on the unmanned aerial vehicle fuselage, be connected as a whole with unmanned aerial vehicle, the cabin of throwing bomb cabin 1 is used for placing the fire extinguishing bomb, the fire extinguishing bomb is put into after throwing the cabin of bomb cabin 1, by the cabin inner wall restriction removal, throw bomb cabin 1 along with unmanned aerial vehicle take off the back, the fire extinguishing bomb can not throw bomb cabin 1 relatively and take place to rock, throw bomb cabin 1 also can not take place to rock relatively unmanned aerial vehicle, unmanned aerial vehicle's flight is stable.
Every throwing cabin 1 can only load one piece of fire extinguishing bomb, if unmanned aerial vehicle only throws one piece of fire extinguishing bomb once, fire extinguishing efficiency is very slow, so require in unmanned aerial vehicle's load capacity within range, once load the fire extinguishing bomb as much as possible, this just need to throw the cabin 1 and can interconnect, throw the cabin 1 and be pegged graft with unmanned aerial vehicle's connected mode, the same thing, the connection between throwing cabin 1 also adopts the grafting, throw the cabin 1 and peg graft mutually together, a plurality of throwing cabin 1 of pegging graft each other forms throwing cabin subassembly after connecting as a whole, one of them throwing cabin 1 in the throwing cabin subassembly pegs graft with the unmanned aerial vehicle fuselage, unmanned aerial vehicle hangs and carries and throws the above-ground of fire point after throwing cabin subassembly takes off and throws the bomb, the quantity of the fire extinguishing bomb that needs to throw is selected according to the area and the condition of fire of getting on fire size.
The structure of the projectile shooting cabin 1 is a cuboid groove body with an open top and a movable bottom cover 2 arranged at the bottom, fire extinguishing bombs are loaded into the projectile shooting cabin 1 from the opening at the top of the projectile shooting cabin 1, the movable bottom cover 2 at the bottom can also be opened, and the fire extinguishing bombs are loaded from the bottom of the projectile shooting cabin 1. The mechanism of uncapping is installed to the lateral wall below of throwing the bullet cabin 1, and after closing activity bottom 2, uncapping the mechanism and die activity bottom 2 card, prevent to dash out activity bottom 2 under the action of gravity of the bullet of putting out a fire, during the bullet of throwing, uncapping the mechanism and remove the restriction to activity bottom 2, activity bottom 2 is opened under the action of gravity of the bullet of putting out a fire, and the bullet of putting out a fire is put away from throwing the bullet cabin 1. The two projectile throwing cabins 1 can be vertically spliced, after the two projectile throwing cabins are vertically spliced, fire extinguishing bombs in the projectile throwing cabin 1 below are thrown firstly during projectile throwing, then the fire extinguishing bombs in the projectile throwing cabin 1 above are thrown, after the movable bottom cover 2 of the projectile throwing cabin 1 above is opened, the fire extinguishing bombs fall from the projectile throwing cabin 1 above, enter the projectile throwing cabin 1 below from the top opening of the projectile throwing cabin 1 below, and fall from the bottom of the projectile throwing cabin 1 below, and the projectile throwing cabin 1 below is used as a throwing channel for the fire extinguishing bombs in the projectile throwing cabin 1 above; the two projectile bays 1 can also be transversely connected, and the projectile bays 1 which are transversely connected can be used for independently throwing fire extinguishing bombs. It should be noted that, because the body of the unmanned aerial vehicle is inserted into a single missile throwing cabin 1, when the missile throwing cabin assembly comprises two missile throwing cabins 1, if a transverse connection mode is selected, one of the missile throwing cabins 1 is connected under the unmanned aerial vehicle, and the other missile throwing cabin 1 is hung on one side of the missile cabin 1 under the unmanned aerial vehicle, after the unmanned aerial vehicle takes off, the flight is unstable due to gravity center shift, and even the unmanned aerial vehicle cannot take off, so when the missile throwing cabin assembly comprises two missile throwing cabins 1, the two missile throwing cabins 1 adopt a vertical connection mode; when throwing the bullet cabin subassembly and containing three bullet cabin 1 of throwing, three bullet cabin 1 of throwing chooses for use the transverse connection mode, it pegs graft under unmanned aerial vehicle to be located middle bullet cabin 1 of throwing, all the other two are thrown bullet cabin 1 and peg graft in the middle both sides of throwing bullet cabin 1, because both sides articulate respectively and throw bullet cabin 1, so throw bullet cabin subassembly peg graft and can keep balance behind unmanned aerial vehicle below, the same reason, throw bullet cabin 1 when 1 quantity of throwing the bullet cabin that the cabin subassembly contains is more, the grafting mode of rational arrangement bullet cabin 1 of throwing, guarantee the stability of unmanned aerial vehicle flight.
Compared with the prior art, the unmanned aerial vehicle projectile throwing device provided by the invention has the advantages that the projectile throwing cabin for throwing the fire extinguishing projectiles is directly inserted into the unmanned aerial vehicle body and is connected with the unmanned aerial vehicle body into a whole, the fire extinguishing projectiles are contained in the inner cavity of the projectile throwing cabin, the phenomenon that the unmanned aerial vehicle is unstable in flight due to the fact that the fire extinguishing projectiles are suspended below the unmanned aerial vehicle is avoided, the bottom of the projectile throwing cabin is provided with the movable bottom cover, the movable bottom cover can be opened and closed relative to the projectile throwing cabin, the fire extinguishing projectiles are loaded into the projectile throwing cabin after the movable bottom cover is opened, then the movable bottom cover is closed, the unmanned aerial vehicle loaded with the fire extinguishing projectiles flies above a fire point, the movable bottom cover is opened, the fire extinguishing projectiles slide.
Further, please refer to fig. 1, fig. 2 and fig. 6 together, as a specific embodiment of the missile launching device of the unmanned aerial vehicle provided by the present invention, the missile launching cabin assembly is formed by splicing a plurality of separate missile launching cabins 1, each missile launching cabin 1 is a hollow cuboid structure, an upper connector is installed at the top of each missile launching cabin 1, a fixed weight 4 spliced with the upper connector is installed at the bottom of each missile launching cabin 1, after the upper connector and the fixed weight 4 are spliced, the two missile launching cabins 1 complete vertical connection, a connecting bottom plate 14 is installed at the bottom of the unmanned aerial vehicle body, the connecting bottom plate 14 is fixed at the bottom of the unmanned aerial vehicle body through a fixing bolt 15, the fixed weight 4 is also installed below the connecting bottom plate, and after the fixed weight 4 installed on the connecting bottom plate 14 is spliced with the upper connector at the top of each missile launching cabin 1, the splicing of each missile launching cabin 1 and. Side plug-in components are installed on the side walls of the projectile shooting cabins 1, and after the side plug-in components of the two projectile shooting cabins 1 are plugged, transverse connection of the projectile shooting cabins 1 is completed.
Further, referring to fig. 1 and 3, as a specific embodiment of the unmanned aerial vehicle missile device provided by the present invention, the upper plug connector installed at the top of the missile throwing cabin 1 is a plug board 3, the plug board 3 is four L-shaped members installed at four corners of the top of the missile throwing cabin 1, one side of the plug board 3 is bonded or connected to four top corners of the missile throwing cabin 1 through bolts, the other side is provided with a socket, one side provided with the socket is perpendicular to the side wall of the missile throwing cabin 1, the inner dimension of the socket is the same as the dimension of the fixed yard 4, the fixed yard 4 is a section of cylindrical member, the end of the fixed yard 4 is provided with a chuck, the chuck is also a section of cylinder, the diameter of the chuck is larger than that of the main body of the fixed yard 4, the fixed yard 4 can be kept fixed after being plugged with the socket, the fixed yard 4 is installed at four bottom corners of the missile throwing cabin 1, fixed sign indicating number otic placode 5 is respectively installed at four base angles in the cabin of throwing bomb 1, and fixed sign indicating number otic placode 5 also is L type spare, and fixed sign indicating number otic placode 5's one side bonds or throws four base angles in the cabin of bomb 1 through bolted connection, and fixed sign indicating number 4 is installed to the another side, and fixed sign indicating number 4 is installed the back and is thrown the lateral wall in cabin of bomb 1 and parallel, has guaranteed the grafting of fixed sign indicating number 4 and socket. Also install four fixed yards 4 on unmanned aerial vehicle's connecting bottom plate 14, the overall arrangement of fixed yard 4 is the same with the 4 overall arrangements of fixed yard of throwing the 1 bottom in bullet cabin, guarantees to throw bullet cabin 1 and unmanned aerial vehicle's accurate grafting. The four insertion plates 3 at the top of the projectile shooting cabin 1 are provided with insertion holes with the same orientation, and the four insertion holes are inserted with the fixed codes 4 together.
Preferably, referring to fig. 1 and 3, after the two missile throwing cabins 1 and the missile throwing cabin 1 and the unmanned aerial vehicle body are not firmly inserted, the missile throwing cabins 1 are easy to fall off after the unmanned aerial vehicle shakes, in order to reinforce the connection of the missile throwing cabins 1, a locking pin 6 is arranged at the top of the missile throwing cabin 1, correspondingly, a pin hole 8 is arranged at the bottom of the missile throwing cabin 1 corresponding to the position of the locking pin 6, the locking pin 6 is fixed at the top of the side wall of the missile throwing cabin 1 through a locking pin lug 7, a pin hole lug 9 is arranged at the bottom of the side wall of the missile throwing cabin 1, the pin hole 8 is arranged on the pin hole lug 9, after the two missile throwing cabins 1 are vertically inserted, the locking pin 6 is opposite to the pin hole 8, the locking pin 6 is inserted into the pin hole 8 to fix the connection of the two missile throwing cabins 1, a pin hole is also arranged at the position corresponding to the locking pin 6 on a, the locking pin 6 is just opposite to the pin hole 8, the locking pin 6 is inserted into the pin hole 8, and the missile throwing cabin 1 is fixedly connected with the unmanned aerial vehicle.
Preferably, the locking pin 6 is a dividing pin, the dividing pin can axially extend and retract, the fixing sleeve of the dividing pin 6 is bonded on the locking pin ear plate 7, the pin shaft of the dividing pin 6 extends out of a small section above the locking pin ear plate 7, when the missile throwing cabin 1 is inserted into the unmanned aerial vehicle body or two missile throwing cabins 1 are vertically inserted, the pin shaft of the dividing pin 7 is pulled downwards, the pin shaft of the dividing pin 7 is prevented from influencing the insertion process, after the insertion is completed, the pin shaft of the dividing pin 7 is loosened, the pin shaft is upwards ejected, the pin shaft is inserted into the right pin hole 8, and the fixation of the missile throwing cabin 1 and the unmanned aerial vehicle body or two missile throwing cabins. In order to prevent the pin of the index pin 7 from slipping when being pulled down, the side wall of the index pin 7 is provided with anti-slip threads.
Further, referring to fig. 1, fig. 2 and fig. 5 together, as a specific embodiment of the unmanned aerial vehicle missile device provided by the invention, the side plug-in connector installed on the side wall of the missile cabin 1 is in a mortise-tenon structure, and comprises a tenon 12 and a mortise 13 which are matched with each other, the tenon 12 and the mortise 13 are both in a long strip shape and are arranged along the height direction of the missile cabin 1, the tenon 12 and the mortise 13 are bonded or fixed on the side wall of the missile cabin 1 through bolts, the missile cabin 1 is in a cuboid structure, the tenon 12 and the mortise 13 are respectively installed on the outer sides of two opposite side walls of the missile cabin 1, the end of the tenon 12 is set to be an inverted triangle protruding head, correspondingly, an inverted triangle groove is formed in the mortise 13, when two missile cabins 1 are transversely plugged, the inverted triangle protruding head is inserted from the end of the inverted triangle groove to complete the connection of the mortise-tenon structure, in order to prevent the tenon 12 from slipping out of the lower end of the mortise 13, the lower end of the mortise 13 is closed.
Further, as a specific implementation mode of the unmanned aerial vehicle missile-launching device provided by the invention, a controller is installed on the unmanned aerial vehicle body, the controller can independently control the servo motor 11 on each missile-launching cabin 1, the controller is wirelessly connected with a remote control for operating the unmanned aerial vehicle, when a certain missile-launching cabin 1 is required to launch, an instruction is sent to the controller on the unmanned aerial vehicle body through the remote control, after the controller receives the instruction, the controller is electrified with the corresponding servo motor 11, the electrified servo motor 11 drives the support rod 10 to rotate, the support of the movable bottom cover 2 is removed, and the missile launching is completed.
The controller controls the bullet throwing of the bullet throwing cabin 1, the balance of the flight of the unmanned aerial vehicle needs to be considered, because the fire extinguishing bullet has certain mass, when the unmanned aerial vehicle takes off fully, the arrangement of the bullet throwing cabins 1 is in a balanced layout, namely when the unmanned aerial vehicle carries two bullet throwing cabins 1, the two bullet throwing cabins 1 are connected in a vertical splicing mode, when the fire extinguishing bullet is thrown, the fire extinguishing bullet in the bullet throwing cabin 1 at the lower side is thrown firstly, and then the fire extinguishing bullet in the bullet throwing cabin 1 at the upper side is thrown; when the unmanned aerial vehicle carries the three projectile cabins 1, the three projectile cabins 1 are connected in a transverse splicing mode, when a projectile is thrown, if a fire extinguishing bomb needs to be thrown, the fire extinguishing bomb in the projectile cabin 1 in the middle is firstly thrown, so that the fire extinguishing bombs in the two projectile cabins 1 at the two ends are balanced at will, the unmanned aerial vehicle flies stably, when two fire extinguishing bombs need to be thrown at one time, the fire extinguishing bombs in the projectile cabins 1 at the two ends are thrown at the same time, the fire extinguishing bomb in the projectile cabin 1 in the middle is positioned right below the unmanned aerial vehicle, and the flight of the unmanned aerial vehicle is kept stable; when more missile throwing cabins 1 are mounted, the balance condition of the unmanned aerial vehicle is considered during missile throwing according to the above mode.
Further, as a specific embodiment of the unmanned aerial vehicle missile device provided by the invention, the movable bottom cover 2 is hinged with the side wall of the missile cabin 1, and the specific hinge mode is as follows: a hinge is arranged at the edge of the movable bottom cover 2, one hinge arm of the hinge is fixed on the movable bottom cover 2 by a screw, the other hinge arm is fixed at the lower end part of the side wall of the projectile shooting cabin 1 by a screw, and the shaft of the hinge is used as a rotating shaft of the movable bottom cover 2. The cover opening mechanism at the bottom of the side wall of the projectile shooting cabin 1 can block the movable bottom cover 2 after the movable bottom cover 2 is closed, the cover opening mechanism comprises a supporting rod 10 arranged at the lower edge of the side wall of the projectile shooting cabin 1, the supporting rod 10 is positioned below the movable bottom cover 2, after the movable bottom cover 2 is closed, the supporting rod 10 supports the movable bottom cover 2 and limits the opening of the movable bottom cover 2, a servo motor 11 is arranged at the lower end part of the side wall of the projectile shooting cabin 1, one end of the supporting rod 10 is vertically connected with an output shaft of the servo motor 11, the servo motor 11 is electrified to drive the output shaft to rotate 90 degrees, the output shaft drives the supporting rod 10 to rotate 90 degrees, the supporting rod 10 is separated from the lower part of the movable bottom cover 1 after rotating, the supporting of the movable bottom cover 2 is lost, the movable bottom cover 2 is opened under the gravity action of the fire extinguishing bomb, the fire extinguishing bomb falls from the projectile shooting cabin 1 to finish, the supporting rod 10 is pushed to the lower part of the movable bottom cover 2 by hand.
After the supporting rod 10 is installed below the movable bottom cover 2, vertical connection between the upper and lower projectile shooting cabins 1 is affected, because the supporting rod 10 is clamped between the upper and lower projectile shooting cabins 1, the insertion connection of the plugboard 3 and the fixed yard 4 is affected, in order to eliminate the influence of the supporting rod 10 on the vertical connection of the projectile shooting cabins 1, a small section of downward extension is installed at the lower ends of two side walls of the plugboard 3 and the fixed yard 4 of the projectile shooting cabins to serve as two convex edges, referring to fig. 3 and 4, the lower edges of the two side walls of the upper projectile shooting cabin 1 and the upper edges of the side walls of the lower projectile shooting cabin 1, after the upper and lower projectile shooting cabins 1 are vertically inserted, a strip gap is reserved in the middle, the width of the gap is slightly larger than the thickness of the supporting rod 10.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (8)
1. Unmanned aerial vehicle device of jettisoning, its characterized in that: the fire extinguishing bomb launching device comprises a bomb throwing cabin for loading fire extinguishing bombs, wherein the bomb throwing cabin is spliced with a body of an unmanned aerial vehicle, the top of the bomb throwing cabin is provided with an opening, the bottom of the bomb throwing cabin is provided with a movable bottom cover, and the bomb throwing cabin is provided with a cover opening mechanism for opening the movable bottom cover;
the top of each projectile shooting cabin is provided with an upper plug connector butted with the unmanned aerial vehicle body or an adjacent projectile shooting cabin, the bottom of each projectile shooting cabin and the bottom of the unmanned aerial vehicle body are provided with fixed codes spliced with the upper plug connectors, and the side wall of each projectile shooting cabin is provided with a side plug connector used for connecting two adjacent projectile shooting cabins;
the side plug-in components include tenon and the tongue-and-groove of mutually supporting, the tenon with the tongue-and-groove symmetry set up in throw the lateral wall of magazine.
2. The unmanned aerial vehicle device of claim 1, characterized in that: go up the plug connector and be a plurality of setting and be in throw the picture peg at bullet cabin top, the picture peg all be equipped with be used for with the socket that fixed sign indicating number was pegged graft, the opening orientation of socket is unanimous.
3. The unmanned aerial vehicle device of claim 1, characterized in that: the lateral wall top of throwing the bullet cabin is equipped with the stop pin that is used for locking two adjacent bullet cabins of throwing, unmanned aerial vehicle fuselage bottom and the lateral wall bottom of throwing the bullet cabin all be equipped with stop pin assorted pinhole.
4. An unmanned aerial vehicle device of claim 3, wherein: the locking pin is an indexing pin, and the side wall of the locking pin is provided with an anti-skidding structure.
5. The unmanned aerial vehicle device of claim 1, characterized in that: the uncovering mechanism comprises a supporting rod arranged below the movable bottom cover and used for supporting the movable bottom cover, a servo motor arranged on the side wall of the projectile shooting cabin and used for driving the supporting rod, and one end of the supporting rod is vertically arranged at the end part of an output shaft of the servo motor.
6. An unmanned aerial vehicle device of claim 5, wherein: the unmanned aerial vehicle fuselage is equipped with and is used for control servo motor's controller, servo motor pass through the wire with the controller electricity is connected.
7. An unmanned aerial vehicle device of jettisoning of any one of claims 1-6, wherein: one end of the movable bottom cover is hinged with the bottom of the side wall of the projectile shooting cabin.
8. An unmanned aerial vehicle device of claim 7, wherein: the edge of the movable bottom cover is provided with a hinge, one hinge arm of the hinge is fixed on the movable bottom cover, and the other hinge arm of the hinge is fixed on the inner side of the side wall of the projectile shooting cabin.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810834037.2A CN108995809B (en) | 2018-07-26 | 2018-07-26 | Unmanned aerial vehicle device of jettisoning |
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|---|---|---|---|
| CN201810834037.2A CN108995809B (en) | 2018-07-26 | 2018-07-26 | Unmanned aerial vehicle device of jettisoning |
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| CN108995809A CN108995809A (en) | 2018-12-14 |
| CN108995809B true CN108995809B (en) | 2020-10-20 |
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| CN109821173A (en) * | 2019-01-28 | 2019-05-31 | 四川外国语大学重庆南方翻译学院 | The intelligence ejection fire extinguisher in the unburned house in ancient city Gu town |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2461380Y (en) * | 2001-01-18 | 2001-11-28 | 陈凤桂 | Combined goods placing case |
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| CN106585990A (en) * | 2016-11-30 | 2017-04-26 | 湖北大秀天域科技发展有限公司 | Release device applicable to unmanned aerial vehicle |
| CN108128461A (en) * | 2017-12-28 | 2018-06-08 | 深圳城际快机科技有限公司 | A kind of throwing device based on unmanned aerial vehicle platform |
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2018
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| CN2461380Y (en) * | 2001-01-18 | 2001-11-28 | 陈凤桂 | Combined goods placing case |
| US6622605B1 (en) * | 2001-01-30 | 2003-09-23 | Raytheon Company | Fail safe arming unit mechanism |
| CN106043698A (en) * | 2016-06-08 | 2016-10-26 | 青海山水生态科技有限公司 | Unmanned aerial vehicle hung type fire extinguishing bomb throwing bin and method |
| CN106347664A (en) * | 2016-11-29 | 2017-01-25 | 海鹰航空通用装备有限责任公司 | Leaflet spreading device for multi-rotor unmanned aerial vehicle and use method of leaflet spreading device |
| CN106585990A (en) * | 2016-11-30 | 2017-04-26 | 湖北大秀天域科技发展有限公司 | Release device applicable to unmanned aerial vehicle |
| CN108128461A (en) * | 2017-12-28 | 2018-06-08 | 深圳城际快机科技有限公司 | A kind of throwing device based on unmanned aerial vehicle platform |
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| CN108995809A (en) | 2018-12-14 |
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