CN205150229U - Many rotors of multilayer airborne vehicle - Google Patents
Many rotors of multilayer airborne vehicle Download PDFInfo
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- CN205150229U CN205150229U CN201520895961.3U CN201520895961U CN205150229U CN 205150229 U CN205150229 U CN 205150229U CN 201520895961 U CN201520895961 U CN 201520895961U CN 205150229 U CN205150229 U CN 205150229U
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Abstract
The utility model discloses a many rotors of multilayer airborne vehicle, include the the central axis of the many rotors of multilayer is the multilayer rotor subassembly that sets up of co -altitude department not, every layer the rotor subassembly includes two rotors, two rotors are in it sets up to be separated by 180 degrees angles in the the central axis circumference, each of many rotors of multilayer airborne vehicle in the rotor in the the central axis circumference adjacent two the direction of rotation of rotor is opposite. The utility model discloses a many rotors of multilayer airborne vehicle can adopt big rotor blade, makes the structure small and exquisite, and the overall arrangement is compact, has improved rotor power area simultaneously, has increased the power sum load.
Description
Technical field
The utility model relates to push-button aircraft technical field, especially relevant with the many rotary wing aircraft of a kind of multilayer.
Background technology
The many autogiros of driverless operation are the one in unmanned plane, have vertical takeoff and landing and freedom of the air hovering function, are the flight optimization carriers of airflight robot.The many autogiros of driverless operation have a wide range of applications in fields such as agricultural production, power grid maintenance, goods transportation, medical aid, aerophotography, military surveillance, anti-terrorism, public security, fire-fighting, forest inspection, dangerous material detection and the disaster relief.
According to the quantity of rotor, unmanned helicopter can be divided into single autogiro and many autogiros two class.Take publication number as CN204587305U, disclosed in the Chinese utility model patent that name is called " the electronic unmanned plane of multifunctional foldable eight rotor ", eight autogiros are example, it comprises main body and eight rotors, each rotor is arranged on main body by hold-down arm, and eight rotors are M shape diffusing structure.Arrangement 8 rotors in the same plane of this eight autogiro around main body, as shown in Figure 1, rotor size is restricted greatly, cannot manufacture high-power heavy－duty aircraft.
Be CN203593162U again with publication number, disclosed in the Chinese utility model patent that name is called " coaxial eight autogiros ", eight autogiros are example, it is 90 degree, interval installation, four rotor assemblies in main body, two rotors every rotor assemblies adopt coaxial setting, and same driver train drives upper and lower two rotors simultaneously.The rotor size of this eight rotors classification is still restricted, thus cannot manufacture high-power heavy－duty aircraft.
The size of the load-carrying lift of unmanned aerial vehicle depends primarily on the factors such as rotor quantity, rotating speed, pitch, paddle size size and position and determines.Above-mentioned existing eight autogiros adopt same levels be M shape diffusing structure to arrange rotor, adjacent two rotor blade metric spaces are limited, so greatly limit many autogiros to high power development.
Therefore need to provide one to have high-power, can many rotary wing aircraft of heavy－duty.
Utility model content
For problems of the prior art, it is high-power that the purpose of this utility model is to provide one to have, can the many rotary wing aircraft of multilayer of heavy－duty.
To achieve these goals, the technical solution of the utility model is as follows:
The many rotary wing aircraft of a kind of multilayer, the multilayer rotor assemblies that the central axis differing heights place that the many rotary wing aircraft of described multilayer are included in the many rotors of described multilayer is arranged; Every layer of described rotor assemblies comprises two rotors, and be separated by described central axis circumference 180 degree of angles of described two rotors are arranged; In each described rotor of each layer, the hand of rotation of two described rotors adjacent in described central axis circumference is contrary.
The many rotary wing aircraft of a kind of multilayer, the multilayer rotor assemblies that the central axis differing heights place that the many rotary wing aircraft of described multilayer are included in the many rotors of described multilayer is arranged; Every layer of described rotor assemblies comprises two rotors, and be separated by described central axis circumference 180 degree of angles of described two rotors are arranged; In each described rotor of the many rotary wing aircraft of described multilayer, the hand of rotation of two described rotors adjacent in described central axis circumference is contrary.
The many rotary wing aircraft of multilayer of the present utility model, preferably, are also included in the umbrella post that the central axis of the many rotary wing aircraft of described multilayer is arranged.
The many rotary wing aircraft of multilayer of the present utility model, preferably, each described rotor being circumferentially uniformly distributed at described umbrella post of the many rotary wing aircraft of described multilayer.
The many rotary wing aircraft of multilayer of the present utility model, preferably, the quantity of described rotor assemblies is 2-10.
The many rotary wing aircraft of multilayer of the present utility model, preferably, neighbouring two-layer described rotor assemblies is connected to described umbrella post by a connection bracket, described connection bracket comprises two main struts and two transverse brackets, described main strut is circumferentially uniformly distributed described umbrella post, described main strut has first end and the second end, described first end is fixedly connected on described umbrella post, described transverse bracket has mid point, first installation end and the second installation end, described transverse bracket is connected to described main strut in described middle point vertical, the actuating device of described rotor is arranged on the top of described first installation end and the below of described second installation end.
The many rotary wing aircraft of multilayer of the present utility model, preferably, described main strut is inclined upwardly installation, the acute angle in a set angle between described main strut and described umbrella post.
The many rotary wing aircraft of multilayer of the present utility model, preferably, described set angle is 82.5 degree.
The many rotary wing aircraft of multilayer of the present utility model, preferably, the cross-sectional plane of described umbrella post is circle, rectangle or criss-cross.
The many rotary wing aircraft of multilayer of the present utility model, preferably, the length of each described main strut is identical.
The many rotary wing aircraft of multilayer of the present utility model, preferably, S. A. being projected on same circle or on same ellipse in the plane perpendicular to described umbrella post of each described rotor.
The many rotary wing aircraft of multilayer of the present utility model, preferably, described main strut is detachably hinged in described umbrella post, described transverse bracket is detachably hinged in described second end of described main strut, described main strut is reinforced by an angle of 90 degrees and is installed on described umbrella post with the mode of unclamping, and described transverse bracket reinforces described second end being connected to described main strut with the mode of unclamping by an angle of 90 degrees.
The many rotary wing aircraft of multilayer of the present utility model, preferably, described actuating device is electrical motor or oil machine.
The many rotary wing aircraft of multilayer of the present utility model, preferably, the quantity of described rotor is eight, be divided into four layers of rotor assemblies, the described rotor of upper two-layer described rotor assemblies is connected to described umbrella post by a described connection bracket, and the described rotor of lower two-layer described rotor assemblies is connected to described umbrella post by connection bracket described in another.
The many rotary wing aircraft of multilayer of the present utility model, preferably, belong to neighbouring two-layer described rotor assemblies respectively at the two circumferentially adjacent rotors of described umbrella post, or belong to the described rotor assemblies of top described rotor assemblies and lowermost layer respectively.
The many rotary wing aircraft of multilayer of the present utility model, preferably, described rotor is connected to described umbrella post by main strut, and described main strut has first end and the second end, described first end is fixedly connected on described umbrella post, and the actuating device of described rotor is arranged on above or below described second end.
The many rotary wing aircraft of multilayer of the present utility model, preferably, also comprise heavy support, described heavy support comprises the first square-shaped frame on described central axis of the center of gravity that is made up of four first connecting rods and the point of crossing that is made up of four second connecting rods criss-cross frame through described central axis, described first connecting rod is parallel with between second connecting rod, vertical or become miter angle, described heavy support is formed with eight for installing the installation position of the actuating device of described rotor, wherein four for upwards installing described actuating device, other four for installing described actuating device downwards, on the installation position of the superiors and undermost described actuating device, pad is provided with cushion block in order to adjust the safety distance arranged between levels.
The many rotary wing aircraft of multilayer of the present utility model, preferably, described heavy support comprises stacked and the second square-shaped frame be fixed together of the miter angle that to stagger with described first square-shaped frame, the installation position of upper two-layer described rotor is arranged on inside four angles of described first square-shaped frame, the installation position of lower two-layer described rotor is arranged on inside four angles of described second square-shaped frame, and described second connecting rod is connected to the mid point of described first connecting rod.
The many rotary wing aircraft of multilayer of the present utility model, preferably, wherein four described installation positions are formed at inside four angles of described first square-shaped frame, and other four described installation positions are formed at the end of described second connecting rod.
The many rotary wing aircraft of multilayer of the present utility model, preferably, wherein four described installation positions are formed at inside four angles of described first square-shaped frame, four described second connecting rods comprise two long connecting rods and two short connecting rods, the end of two long connecting rods is connected to described first square-shaped frame, the end vertical of two short connecting rods connects the third connecting rod isometric with described first connecting rod, and other four installation positions are formed at totally four ends of third connecting rod described in two.
The many rotary wing aircraft of multilayer of the present utility model, preferably, also comprise the gondola for loading facilities, and described gondola is arranged on the bottom of described umbrella post.
The many rotary wing aircraft of multilayer of the present utility model, preferably, also comprise the crane being arranged on described gondola both sides.
The many rotary wing aircraft of multilayer of the present utility model, preferably, the middle part of described umbrella post is provided with battery pack or oil turbine and fuel tank, and described oil turbine drives each described rotor by the gear train assembly be connected with described oil turbine mouth.
The beneficial effects of the utility model are: the many rotary wing aircraft of multilayer of the present utility model, its every layer rotor assemblies arranges that the structure of two rotors leaves the larger revolution space of rotor for, large rotor blade can be adopted, make compact structure, compact in design, improve rotor power area simultaneously, increase power and load-carrying.
And then the utility model than existing multi-rotor aerocraft, can reduce structural materials, reduce overall dimensions under the prerequisite of same power, be convenient to manufacture, deposit and transport.
Accompanying drawing explanation
Fig. 1 is the rotor rotational plan sketch of a kind of eight autogiros of prior art.
Fig. 2 is the rotor rotational plan sketch of the many rotary wing aircraft of multilayer of the utility model first embodiment.
Fig. 3 is that multilayer many rotary wing aircraft eight rotor of the utility model first embodiment arranges schematic top plan view.
Fig. 4 is the schematic top plan view of multilayer many rotary wing aircraft connection bracket of the utility model first embodiment.
Fig. 5 is the schematic front view of the many rotary wing aircraft of multilayer of the utility model first embodiment.
Fig. 6 is the connection bracket schematic diagram of the many rotary wing aircraft of multilayer of the utility model second embodiment.
Fig. 7 is the connection bracket schematic diagram of the many rotary wing aircraft of multilayer of the utility model the 3rd embodiment.
Fig. 8 is the connection bracket schematic diagram of the many rotary wing aircraft of multilayer of the utility model the 4th embodiment.
Fig. 9 is that multilayer many rotary wing aircraft four rotor of the utility model the 5th embodiment arranges schematic top plan view.
Figure 10 is umbrella post and the main strut connection diagram of the many rotary wing aircraft of multilayer of the utility model embodiment.
Figure 11 is main strut and the transverse bracket connection diagram of the many rotary wing aircraft of multilayer of the utility model embodiment.
Detailed description of the invention
In order to make technical problem to be solved in the utility model, technical scheme and beneficial effect clearly understand, below in conjunction with specific embodiment, the utility model is further elaborated.It should be pointed out that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.
Below the many rotary wing aircraft of multilayer of each embodiment of the utility model are introduced respectively.
One, the many rotary wing aircraft of the multilayer of the first embodiment
As Figure 2-Figure 5, the many rotary wing aircraft of multilayer of the utility model first embodiment are four layer of eight rotor wing unmanned aerial vehicle, and this unmanned plane comprises rotor 1 to rotor 8.As shown in Figure 2, from overlooking viewing eight rotor rotor blade top a1-a8 and each rotor 1-8, relation between umbrella post A and driver train when different layers rotates, rotor 1 and the same layer of rotor 5, in the superiors, rotor blade a1 does not contact with blade a5; Rotor 2 and the same layer of rotor 6, in third layer, rotor blade a2 does not contact with blade a6; Rotor 3 does not contact with blade a7 with a layer rotor blade a3 with rotor 7; Rotor 4 does not contact with blade a8 with a layer rotor blade a4 with rotor 8.
Therefore, four layer of eight rotor wing unmanned aerial vehicle of the present embodiment, comprise umbrella post A and eight rotor 1-8, eight rotor 1-8 divide four layers, on umbrella post A, differing heights place is arranged, every layer of rotor assemblies comprises two rotors, and two rotors of every layer are arranged at the 180 degree of angles that are circumferentially separated by of umbrella post A, and hand of rotation is identical or contrary.And all described rotor on each layer generally speaking, being circumferentially uniformly distributed of umbrella post A, also to be namely separated by 45 degree of settings, as shown in Figure 4, each rotor circumferentially arranging sequentially for set gradually from rotor 1 to rotor 8 at umbrella post A, and contrary at the hand of rotation of the two circumferentially adjacent rotors of umbrella post A, also namely the hand of rotation of rotor 1,3,5,7 is identical, be such as clickwise, and the hand of rotation of rotor 2,4,6,8 is identical, such as, be left-hand revolution.
As shown in Figure 5, upper two-layer rotor assemblies is connected to umbrella post A by " work " font connection bracket, lower two-layer rotor assemblies is connected to umbrella post A by another " work " font connection bracket, each connection bracket comprises two main struts and two transverse brackets, main strut is circumferentially uniformly distributed umbrella post A's, is 180 degree of settings of being separated by the present embodiment.
For main strut ba-b12, it has first end ba and the second end b12, first end ba is fixedly connected on umbrella post A, and transverse bracket b1-b2 has mid point b12, the first installation end b1 and the second installation end b2, transverse bracket b1-b2 is vertically connected at main strut ba-b12 at mid point b12 place, the actuating device of upper strata rotor 1 is arranged on the top of the first installation end b1, and the actuating device of lower floor's rotor 2 is arranged on the below of described second installation end b2.
In the present embodiment, adopt motor to drive the mode of rotor, each electrical motor drives a rotor, can be set to the battery pack of each motor at the middle part of umbrella post A.
But the utility model is not limited thereto, the actuating device of rotor also can be oil machine, for oil machine, can use and single be arranged on oil turbine in the middle part of umbrella post A and fuel tank, oil turbine drives each described rotor by the gear train assembly be connected with oil turbine mouth; Also each oil machine can be adopted to drive the mode of a rotor, and the position arranging oil machine is identical with the position arranging electrical motor.Oil machine can be spark ignition engine, aviation fuel machine or Methanol Engine.
In the present embodiment, each main strut is inclined upwardly installation, and the acute angle in a set angle between main strut and umbrella post A, this set angle can between 80-85, preferably 82.5 degree, and that is, the angle between main strut and horizontal surface is 7.5 degree.
As shown in Figure 4, in the present embodiment, the length of each main strut can be all identical, and also namely the identical length of main support ba-b12, ba-b34, ba-b56, ba-b78 is same.In addition, 4 transverse brackets b1-b2, b3-b4, b5-b6, b7-b8 are also identical.
S. A. being projected on same circle or on same ellipse on the horizontal surface perpendicular to umbrella post A of each rotor, to make whole eight rotor wing unmanned aerial vehicles rounded or oval.And the cross-sectional plane of umbrella post A can be circle, rectangle or criss-cross, criss cross umbrella post can manufacture with criss-cross carbon fibre material or with alloy aluminum manufacture or magnesium aluminum alloy manufacture, the connecting rod etc. that its criss cross is often all convenient to installation main strut or is attached thereto.
In the present embodiment, for convenience of installation, the folding and dismounting of four layer of eight rotor wing unmanned aerial vehicle, as shown in Figure 10 and Figure 11, main strut is detachably hinged in umbrella post A, transverse bracket is detachably hinged in the second end of main support, main strut is reinforced by an angle of 90 degrees and is installed on umbrella post A with the mode of unclamping, and transverse bracket reinforces the second end being connected to main support with the mode of unclamping by an angle of 90 degrees.Alternatively, attaching parts comprises and is fixed on 1 bearing fa on umbrella post A and hole fa1.The first end ba of main strut ba-b12 is provided with mounting hole fa1.Through mounting hole fa1, ba is fixed on fa bearing with axle.Pole fa and fa1 makes fa and ba be flexibly connected by an angle of 90 degrees up and down.Connected and fixed by shackle member fka1.Alternatively, in the middle part of transverse bracket b1 with b2, horizontal direction is connected and is equipped with 1 bearing and hole fa12.One end of pole is provided with mounting hole.Through mounting hole fa12, b12 and transverse bracket are fixed together with axle.Pole b12 and fa12 makes transverse bracket be flexibly connected at horizontal 90-degree angle.Connected and fixed by shackle member fka2.Can by umbrella post A and main strut be reinforced and unclamp method and be connected in 90-degree rotation angle up and down, main strut and transverse bracket can horizontally rotate an angle of 90 degrees and reinforce and unclamp method and be connected, and can facilitate the quick assembly and disassembly of the many rotary wing aircraft of the multilayer of the utility model embodiment.The utility model also can adopt fastener to connect, and uses instrument assembly and disassembly.
By arranging eight rotors on the present embodiment unmanned plane, the lift of aircraft can be improved; Further, when unmanned plane needs operation, main strut and transverse bracket are opened and are installed, when unmanned plane operation complete need park time, main strut and transverse bracket are rotated an angle of 90 degrees stored collapsed, like this, decrease the volume of unmanned plane, easy to carry and store.
Simultaneously with reference to figure 4 and Fig. 5, the two circumferentially adjacent rotors of umbrella post A belong to neighbouring two-layer described rotor assemblies respectively, or belong to the described rotor assemblies of top described rotor assemblies and lowermost layer respectively, for example, the adjacent rotor of the rotor of the second layer, can be the rotor of third layer and ground floor, and the adjacent rotor of the rotor of ground floor, can be the rotor of the second layer and the 4th layer.
Four layer of eight rotor wing unmanned aerial vehicle of the present embodiment, also comprises the gondola for loading facilities and crane (alighting gear) D, and described gondola is arranged on the E position, bottom of umbrella post A, and crane D is arranged in the bottom of umbrella post A both sides or equipment pod both sides.Four layer of eight rotor wing unmanned aerial vehicle of the present embodiment, also can comprise the gondola C for loading battery, gondola is arranged on the middle and lower part of umbrella post A.Can arrange damping The Cloud Terrace, pick up camera, photographic camera etc. in gondola, pick up camera is wherein such as noctovisor.
In addition, also can adopt following scheme: umbrella post A's is work suspension body communication port bottom, can hang working cradle head, The Cloud Terrace be installed photographic camera or pick up camera.
Four layer of eight rotor wing unmanned aerial vehicle of the present embodiment, due to the material of its connection bracket economize, lightweight, alleviate the deadweight of four layer of eight rotor wing unmanned aerial vehicle, therefore it can be called light hydraulic support, add every layer of rotor assemblies and comprise two rotors, that the radius of rotor can be done is larger, therefore can increase the power of four layer of eight rotor wing unmanned aerial vehicle, increase cargo capacity.Therefore, the present embodiment props up maximum rotor blade with the shortest supporting structure freely to circle in the air.
The many rotary wing aircraft of multilayer of the present utility model, its connection bracket also can be reinforced, and to increase stability and the reliability of whole body, therefore has the second to the 4th following embodiment.
Two, the many rotary wing aircraft of the multilayer of the second embodiment
The many rotary wing aircraft of multilayer of the present embodiment, remain four layer of eight rotor wing unmanned aerial vehicle, be basically the same as those in the first embodiment part, repeats no more; Here the difference of the second embodiment and the first embodiment is introduced.
As shown in Figure 6, difference is mainly that Connectable umbrella post A is not identical with the connection bracket of each rotor.The connection bracket of the present embodiment is heavy support, comprise the first square-shaped frame, the second square-shaped frame and criss-cross frame, inside four bights of the first square-shaped frame, rotor 2,4,6,8 is installed, and inside four of the second square-shaped frame bights, rotor 1,3,5,7 is installed.
The center of gravity of the first square-shaped frame, on the central axis of described four layer of eight rotor wing unmanned aerial vehicle, is made up of four first connecting rods; The point of crossing of criss-cross frame is through above-mentioned central axis, and be made up of four second connecting rods, in the present embodiment, parallel or vertical between first connecting rod with second connecting rod, second connecting rod is connected to the mid point of first connecting rod.The center of gravity of the second square-shaped frame, also on above-mentioned central axis, is made up of four connecting rods.The miter angle that staggers between first square-shaped frame and the second square-shaped frame is stacked and be fixed together.
Four are formed for upwards installing the installation position of the electrical motor of rotor 2,4,6,8 inside four bights of the first square-shaped frame, four are formed for installing the installation position of the electrical motor of rotor 1,3,5,7 downwards inside four bights of the second square-shaped frame, on the installation position of the superiors and undermost described actuating device, pad is provided with cushion block, to form minimum safe distance between adjacent layer.
In the utility model, light hydraulic support is the structure that minimal material can support, and heavy support is then the increase in the rigidity of structure, the safety of load-bearing, can strengthen stability and the reliability of the many rotary wing aircraft of the utility model multilayer.
Three, the many rotary wing aircraft of multilayer of the 3rd embodiment
The many rotary wing aircraft of multilayer of the present embodiment, remain four layer of eight rotor wing unmanned aerial vehicle, and the something in common with front two embodiments, repeats no more.
As shown in Figure 7, what the present embodiment still adopted is heavy support, and difference is mainly that the heavy support of the present embodiment only has a square-shaped frame.
The heavy support of the present embodiment, comprises the first square-shaped frame and criss-cross frame, installs rotor 2,4,6,8 inside four bights of the first square-shaped frame, and rotor 1,3,5,7 is installed in four of criss-cross frame ends.Here, the superiors' (the 4th layer) are rotors 1,5, and third layer is rotor 2,6, and the second layer is rotor 3,7, and orlop (ground floor) is rotor 4,8.
The center of gravity of the first square-shaped frame, on the central axis of described four layer of eight rotor wing unmanned aerial vehicle, is made up of four first connecting rods; The point of crossing of criss-cross frame, through above-mentioned central axis, is made up of four second connecting rods, in the present embodiment, parallel or vertical between first connecting rod with second connecting rod.
Form two inside four bights of the first square-shaped frame respectively for upwards installing the installation position of the electrical motor of rotor 2,6, two for installing the installation position of rotor 4,8 downwards.Four ends of the second connecting rod of criss-cross frame form two respectively for upwards installing the installation position of the electrical motor of rotor 1,5, and two for installing the installation position of rotor 3,7 downwards.On the installation position of the actuating device of the superiors' rotor 1,5 and orlop rotor 4,8, pad is provided with cushion block, to form minimum safe distance between adjacent layer.
The heavy support of the present embodiment, can strengthen stability and reliability, and the heavy support more material saving of ratio the second embodiment.
Four, the many rotary wing aircraft of multilayer of the 4th embodiment
The many rotary wing aircraft of multilayer of the present embodiment, remain four layer of eight rotor wing unmanned aerial vehicle, the something in common with first three embodiment, repeats no more.
As shown in Figure 8, what the present embodiment still adopted is heavy support, and difference is mainly the setting position of wherein four rotors of the heavy support of the present embodiment.
The heavy support of the present embodiment, comprises the first square-shaped frame, criss-cross frame and two third connecting rods, and the center of gravity of the first square-shaped frame, on the central axis of described four layer of eight rotor wing unmanned aerial vehicle, is made up of four first connecting rods; The point of crossing of criss-cross frame, through above-mentioned central axis, is made up of four second connecting rods, in the present embodiment, becomes miter angle between first connecting rod with second connecting rod.Inside four bights of the first square-shaped frame, rotor 1,3,5,7 is installed, four second connecting rods of criss-cross frame comprise two long connecting rods and two short connecting rods, the end of two long connecting rods is connected to the first square-shaped frame, the end vertical of two short connecting rods is connected to described third connecting rod, the first connecting rod of third connecting rod and the first square-shaped frame is isometric, other four installation positions are formed at totally four ends of two third connecting rods, for installing the electrical motor of rotor 2,4,6,8.
Here, the layered arrangement of each rotor can be as follows: the superiors' (the 4th layer) are rotors 1,5, third layer is rotor 3,7, the second layer is rotor 2,6, and orlop (ground floor) is rotor 4,8, and, also can be the superiors' (the 4th layer) be rotor 4,8, third layer is rotor 2,6, and the second layer is rotor 3,7, and orlop (ground floor) is rotor 1,5.
Four are formed for upwards installing the installation position of the electrical motor of rotor 1,3,5,7 inside four bights of the first square-shaped frame.Four ends of third connecting rod form four respectively for installing the installation position of the electrical motor of rotor 2,4,6,8 downwards.On the installation position of the actuating device of the superiors' rotor 1,5 and orlop rotor 4,8, pad is provided with cushion block, to form minimum safe distance between adjacent layer.
The heavy support of the present embodiment, can strengthen stability and reliability further.
What more than introduce is the unmanned plane of four layer of eight rotor, and rotor assemblies quantity of the present utility model can be 2-10, or more.
Five, the many rotary wing aircraft of multilayer of the 5th embodiment
The many rotary wing aircraft of multilayer of the present embodiment, be two-layer four rotor wing unmanned aerial vehicles, be basically the same as those in the first embodiment part, repeats no more.
As shown in Figure 9, what the present embodiment adopted is light hydraulic support, main strut is adopted directly to connect the mode of rotor, rotor 1-4 is connected to umbrella post A by main strut, main strut has first end and the second end, first end is fixedly connected on umbrella post A, and the actuating device of rotor is arranged on above or below the second end.Such as, the electrical motor of rotor 1,3 is arranged on the top of the second end, and the electrical motor of rotor 2,4 is arranged on the below of the second end.
To sum up, the many rotary wing aircraft of multilayer of the present utility model, the rotor assemblies of every layer arranges 2 rotors, and the paddle size of rotor is unrestricted, can easily manufacture the aerocrafts such as high-power heavy－duty unmanned plane.
The utility model has dividing of the structure design of light hydraulic support and heavy support.The rotor assemblies of every layer, the parallel same layer in left and right installs two rotors, rotor top (also namely rotor and S. A. distance end farthest) and umbrella post between leave minimum safe distance.Here minimum safe distance is the distance that rotor and periphery can not collide, also to consider rotor stressed bending time the distance that can not collide.And the spacing of neighbouring two-layer rotor equals: leave minimum safe distance space between neighbouring rotor.And in the circumference of umbrella post A, between rotor, angle equals 360 degree divided by total rotor number.But the utility model also can not arrange umbrella post, and is replaced the function of umbrella post by heavy support, and in the bottom of heavy support, the central axis of the many rotary wing aircraft of multilayer connects gondola and alighting gear etc., realizes loading function.
The utility model decreases the structural materials of 2.5 times than existing same layer eight-rotary wing aircraft, adds the rotor blade size of 2.66 times, and rotor provides power area to increase by 7.08 times.Owing to can adopt more large-area rotor, blade is overlapping, compact conformation, is applicable to many autogiros to maximization, heavily loaded future development.By umbrella post A loading, bottom umbrella post A, be provided with the gondola for loading facilities.Center of gravity entirety concentrates on below, and the many rotary wing aircraft of multilayer are had a smooth flight.Further, can quick despatch, equally can draw in and deposit by elephanta umbrella when carrying, reduce and deposit volume.
So far embodiment as herein described is construed as is to explanation of the present utility model, but not to restriction of the present utility model.Scope of the present utility model is not illustrated by above specification sheets, but is limited by the claim of patent, and the utility model is intended to comprise all corrections be equal to the meaning of patent claims and scope.
Claims (10)
1. the many rotary wing aircraft of multilayer, is characterized in that, the multilayer rotor assemblies that the central axis differing heights place that the many rotary wing aircraft of described multilayer are included in the many rotors of described multilayer is arranged; Every layer of described rotor assemblies comprises two rotors, and be separated by described central axis circumference 180 degree of angles of described two rotors are arranged; In each described rotor of the many rotary wing aircraft of described multilayer, the hand of rotation of two described rotors adjacent in described central axis circumference is contrary.
2. the many rotary wing aircraft of multilayer as claimed in claim 1, is characterized in that, be also included in the umbrella post that the central axis of the many rotary wing aircraft of described multilayer is arranged.
3. the many rotary wing aircraft of multilayer as claimed in claim 2, is characterized in that, each described rotor being circumferentially uniformly distributed at described umbrella post of the many rotary wing aircraft of described multilayer.
4. the many rotary wing aircraft of multilayer as claimed in claim 1, is characterized in that, the quantity of described rotor assemblies is 2-10.
5. the many rotary wing aircraft of multilayer as claimed in claim 3, it is characterized in that, neighbouring two-layer described rotor assemblies is connected to described umbrella post by a connection bracket, described connection bracket comprises two main struts and two transverse brackets, described main strut is circumferentially uniformly distributed described umbrella post, described main strut has first end and the second end, described first end is fixedly connected on described umbrella post, described transverse bracket has mid point, first installation end and the second installation end, described transverse bracket is connected to described main strut in described middle point vertical, the actuating device of described rotor is arranged on the top of described first installation end and the below of described second installation end.
6. the many rotary wing aircraft of multilayer as claimed in claim 5, is characterized in that, described main strut is inclined upwardly installations, is the acute angle of 82.5 degree between described main strut and described umbrella post.
7. the many rotary wing aircraft of multilayer as claimed in claim 3, it is characterized in that, also comprise heavy support, described heavy support comprises the first square-shaped frame on described central axis of the center of gravity that is made up of four first connecting rods and the point of crossing that is made up of four second connecting rods criss-cross frame through described central axis, described first connecting rod is parallel with between second connecting rod, vertical or become miter angle, described heavy support is formed with eight for installing the installation position of the actuating device of described rotor, wherein four for upwards installing described actuating device, other four for installing described actuating device downwards, on the installation position of the superiors and undermost described actuating device, pad is provided with cushion block in order to adjust the safety distance arranged between levels.
8. the many rotary wing aircraft of multilayer as claimed in claim 7, it is characterized in that, described heavy support comprises stacked and the second square-shaped frame be fixed together of the miter angle that to stagger with described first square-shaped frame, the installation position of upper two-layer described rotor is arranged on inside four angles of described first square-shaped frame, the installation position of lower two-layer described rotor is arranged on inside four angles of described second square-shaped frame, and described second connecting rod is connected to the mid point of described first connecting rod.
9. the many rotary wing aircraft of multilayer as claimed in claim 7, it is characterized in that, wherein four described installation positions are formed at inside four angles of described first square-shaped frame, and other four described installation positions are formed at the end of described second connecting rod.
10. the many rotary wing aircraft of multilayer as claimed in claim 7, it is characterized in that, wherein four described installation positions are formed at inside four angles of described first square-shaped frame, four described second connecting rods comprise two long connecting rods and two short connecting rods, the end of two long connecting rods is connected to described first square-shaped frame, the end vertical of two short connecting rods connects the third connecting rod isometric with described first connecting rod, and other four installation positions are formed at totally four ends of third connecting rod described in two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520895961.3U CN205150229U (en) | 2015-11-11 | 2015-11-11 | Many rotors of multilayer airborne vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520895961.3U CN205150229U (en) | 2015-11-11 | 2015-11-11 | Many rotors of multilayer airborne vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN205150229U true CN205150229U (en) | 2016-04-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520895961.3U Expired - Fee Related CN205150229U (en) | 2015-11-11 | 2015-11-11 | Many rotors of multilayer airborne vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270616A (en) * | 2015-11-11 | 2016-01-27 | 北京苏哈科技有限公司 | Multi-layer multi-rotor aircraft |
| WO2018172815A1 (en) * | 2017-03-22 | 2018-09-27 | Aerones, Sia | A multicopter frame |
-
2015
- 2015-11-11 CN CN201520895961.3U patent/CN205150229U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270616A (en) * | 2015-11-11 | 2016-01-27 | 北京苏哈科技有限公司 | Multi-layer multi-rotor aircraft |
| WO2018172815A1 (en) * | 2017-03-22 | 2018-09-27 | Aerones, Sia | A multicopter frame |
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