A kind of novel four rotor wing unmanned aerial vehiclesTechnical field
The utility model relates to a kind of unmanned plane, particularly relates to a kind of novel four rotor wing unmanned aerial vehicles.
Background technology
Unmanned plane militarily can be used for scouting, supervision, trunking traffic, electronic countermeasure, firepower guidance, combat success assessment, harassing and wrecking, temptation, over the ground (sea) attack, target simulation and early warning etc.At civil area, can be used for geodesic measurement, meteorological watch, city environment detection, earth resources exploration and forest fire protection etc.Therefore, detectable, SUAV (small unmanned aerial vehicle) that is that search for also Tracking Ground Targets complies with the growth requirement of military and civilian, and have broad application prospects, especially in military field, unmanned plane has obtained large-scale development, and has the trend replacing and have people's fighter plane.In all previous fight in this year, unmanned plane is played an increasingly important role by network data chain, makes unmanned plane under the background of Modern Information based war, seem more and more important and gives prominence to.
Rotor wing unmanned aerial vehicle is easy to investigation and carries because its volume is little, but camera easily shelters from by its rotor of some unmanned planes, affect the shooting visual angle of camera, and causes rotor folding inconvenient due to the cause of camera.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of novel four rotor wing unmanned aerial vehicles, and solve traditional rotor unmanned plane and be not easy to folding and that camera visual angle is less problem, the rotor of existing unmanned plane is easy to make a mess of, and is inconvenient to technical matterss such as changing.
The technical scheme that the utility model solves the problems of the technologies described above is as follows: a kind of novel four rotor wing unmanned aerial vehicles, comprises fuselage and the camera be located on described fuselage and four rotor bars; Each described rotor bar is provided with a rotor, and the structure of each described rotor bar is identical; Each described rotor bar includes head rod, the second pipe link; One end of described head rod is fixedly connected with described fuselage, and one end of the described head rod other end and described second pipe link removably connects; Described rotor arranges on the other end of described second pipe link; And described second pipe link be provided with near one end of described head rod for by the electric signal transmission on described fuselage to the electrical connection jack on described rotor; The front rotor bar that four described rotor bars are divided into two to be in same level and another two rear rotor bars being in same level, two described front rotor bar place planes and two described rear rotor bar place planes have diff-H; Rotor bar before rotor bar and second before two described front rotor bars are divided into first, rotor bar after rotor bar and second after two described rear rotor bars are divided into first; Described rotor be divided into be located at described first before rotor before first above rotor bar, be located at described second before the second rotor above rotor bar, be located at described first after rotor and rotor after being located at second after described second below rotor bar after first below rotor bar; Four described rotor bars are all connected by rotating shaft with described fuselage; Described camera is in below two described front rotor bars.
The beneficial effects of the utility model are: because forward and backward rotor bar staggers setting, and make camera take visual angle and expand, forward and backward rotor bar folds more convenient simultaneously, makes rotor wing unmanned aerial vehicle be more conducive to investigation and carry.
Further: described fuselage side is provided with the groove that can embed two described front rotor bars, two described rear rotor bars.
The beneficial effect of above-mentioned further scheme is: forward and backward rotor bar can be embedded in groove, makes the unmanned plane volume after folding less, more firm after folding, is easy to carry.
Further, also comprise and being located on described fuselage and the secondary camera be positioned at below described rear rotor bar.
The beneficial effect of above-mentioned further scheme is: can omnibearingly take, coverage is wider.
Further, described camera, secondary camera and the removable connection of described fuselage.
The beneficial effect of above-mentioned further scheme is: can be convenient for changing or keep in repair camera.
Further, described diff-H is not less than the height of described rotor.
The beneficial effect of above-mentioned further scheme is: be convenient to the folding of rotor bar.
Further, the laser night-vision device be located on described fuselage is also comprised.
The beneficial effect of above-mentioned further scheme is: night also can well be carried out investigations.
Accompanying drawing explanation
Fig. 1 of the present utility modelly faces structural representation;
Fig. 2 is side-looking structural representation of the present utility model;
Fig. 3 is rotor bar structural representation of the present utility model;
Fig. 4 is the second pipe link structural representation of the present utility model;
Fig. 5 is the another kind of structural representation of rotor bar of the present utility model.
Detailed description of the invention
Be described principle of the present utility model and feature below in conjunction with accompanying drawing, example, only for explaining the utility model, is not intended to limit scope of the present utility model.
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5, a kind of novel four rotor wing unmanned aerial vehicles, comprise fuselage 1 and the camera 2 be located on described fuselage 1 and four rotor bars; Each described rotor bar is provided with a rotor 3, and the structure of each described rotor bar (front rotor bar 4, rear rotor bar 5) is identical; Each described rotor bar includes head rod 01, second pipe link 02; One end of described head rod 01 is fixedly connected with described fuselage 1, and one end of described head rod 01 other end and described second pipe link 02 removably connects; Described rotor 3 arranges on the other end of described second pipe link 02; And described second pipe link 02 be provided with near one end of described head rod 01 for by the electric signal transmission on described fuselage 1 to the electrical connection jack 023 on described rotor 3; The front rotor bar 4 that four described rotor bars are divided into two to be in same level and another two described front rotor bar 4 place planes of 5, two, rear rotor bar being in same level and two described rear rotor bar 5 place planes have diff-H; Rotor bar before rotor bar and second before two described front rotor bars are divided into first, rotor bar after rotor bar and second after two described rear rotor bars are divided into first; Described rotor 3 be divided into be located at described first before rotor before first above rotor bar, be located at described second before the second rotor above rotor bar, be located at described first after rotor and rotor after being located at second after described second below rotor bar after first below rotor bar; Four described rotor bars are all connected by rotating shaft with described fuselage 1; Described camera 2 is in below two described front rotor bars 4.Described fuselage 1 side is provided with the groove that can embed two described rear rotor bars 5 of described 4, two, front rotor bar.
Described head rod 01 is provided with the first pillar 011, second pillar 012; Described second pipe link 02 is provided with the first draw-in groove 201 matched with described first pillar 011, and described second pipe link 02 is provided with the second draw-in groove 022 matched with described second pillar 012.
Described second draw-in groove 022 is provided with the projection 024 preventing from departing between described head rod 01 and described second pipe link 02 near the side of described head rod 01.
Because four described rotor bars stagger setting, make described camera 2 take visual angle and expand, rotor bar folds more convenient simultaneously, makes rotor wing unmanned aerial vehicle be more conducive to investigation and carry.Time folding, embed in described groove by folding for four described rotor bars, greatly reduce the volume of unmanned plane after folding, and four described rotor bars have the protection of fuselage 1 to be not easy to fracture.It should be pointed out that the diff-H between two described front rotor bar 4 place planes and two described rear rotor bar 5 place planes is preferably not less than the height of rotor 3, otherwise be unfavorable for folding, affect folding rate.Also comprise and being located on described fuselage 1 and the secondary camera be positioned at below described rear rotor bar 5, make coverage wider.Described camera 2, secondary camera and the removable connection of described fuselage 1, be convenient to repairing and the replacing of camera.Also comprise the laser night-vision device be located on described fuselage 1, well can take investigation at night.
The foregoing is only preferred embodiment of the present utility model, not in order to limit the utility model, all within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.