CN104608923A - Honeycomb-type six-rotor transport aircraft - Google Patents
Honeycomb-type six-rotor transport aircraft Download PDFInfo
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- CN104608923A CN104608923A CN201510050112.2A CN201510050112A CN104608923A CN 104608923 A CN104608923 A CN 104608923A CN 201510050112 A CN201510050112 A CN 201510050112A CN 104608923 A CN104608923 A CN 104608923A
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Abstract
The invention discloses a honeycomb-type six-rotor transport aircraft which comprises a main body honeycomb unit, compound wings and a load supporting and releasing platform connected to the lower part of the main body honeycomb unit, wherein the main body honeycomb unit and the compound wings are of orthohexagonal honeycomb shell structures; the structure is modular, and when having a fault, the aircraft can be continuously used by rapidly replacing the failed honeycomb unit. Meanwhile, according to the structure, the mass of the used material of the aircraft is lightened, and the strength of the aircraft is improved; the compound wings comprise six rotor honeycomb units; the six rotor honeycomb units are uniformly distributed at the periphery of the main honeycomb unit, each rotor honeycomb unit is connected with the main honeycomb unit, and two adjacent honeycomb units are spliced and fixedly connected and are easy to detach; and the load supporting and releasing platform is controlled to bear and release by virtue of a steering engine. The honeycomb-type six-rotor transport aircraft disclosed by the invention is modular, convenient to detach, small in transport occupied space, adaptive in load clamping and easy to operate.
Description
Technical field
The present invention relates to aircraft field, particularly a kind of cell type six rotor transporter aircraft.
Background technology
Rotor class aircraft has vertical takeoff and landing and hovering function, has consequence in military field, and in the relief of earthquake disaster, the jeopardously search of condition or the field such as to take photo by plane in the air also show huge applications potentiality, are subject to extensive concern.
The aircraft major part of current rotor class is all the four-axle aircraft adopting criss-cross or X-shaped.Six rotorcraft can change sense of motion under the condition that attitude remains unchanged aloft.Its attitude can be changed too when sense of motion is constant, can also attitude and sense of motion change simultaneously.Realize the decoupling zero to motion and attitude two aspect.Because the hold-down arm of existing aircraft and main body have connected into an entirety by Antisliding bolt, cause the physical dimension of six rotorcraft large, be not easy to transport.
On market, the structure of existing six rotorcraft forms primarily of six hold-down arms and one piece of stay bearing plate.Six hold-down arms distribute uniformly around stay bearing plate.This Flight Vehicle Structure is simple, and range of use is wide.But the aircraft of this structure is when breaking down, maintenance cycle is long and inconvenient.As unstability or the misoperation of aircraft, the stress produced during shock with ground often concentrates on single or two hold-down arms, structurally arrange that some shock absorbers are inconvenient owing to supporting arm-type six rotorcraft, the structure of buffering so many current aircraft all do not fall.Whole hold-down arm is easily fractureing in a flash of impacting.Many enterprises select whole hold-down arm to be used the material of some high strength to reach anti-object of falling, thus result in the rising of manufacturing cost.Because the connection major part of hold-down arm and stay bearing plate is all adopt Antisliding bolt, need when user keeps in repair to carry necessary instrument, attaching parts, dismantles its all parts, changes.Whole maintenance process is loaded down with trivial details, makes troubles to user.
Summary of the invention
The invention provides a kind of cell type six rotor transporter aircraft, there is difficult maintenance, the problem that not quick detachable, structural strength is low, transporting cargo specification is single in the fault that its object is to overcome the six axle multi-rotor aerocrafts existed in above-mentioned prior art, by modular honeycomb structure, make aircraft quick detachable, intensity is high, and maintenance is easily exchanged.
A kind of cell type six rotor transporter aircraft, comprises main body cellular unit, the multiple wing and the load support be connected to below main body cellular unit and release platform;
Described main body cellular unit and the multiple wing are the honeycomb shell-like structure on regular hexagon limit;
Flight control units is provided with in the middle of described main body cellular unit;
The described multiple wing comprises six rotor cellular units, and each rotor cellular unit is provided with screw propeller and brushless motor, and described screw propeller is driven by brushless motor; Described six rotor cellular units are evenly distributed on the surrounding of main body cellular unit, and each rotor cellular unit is all connected with main body cellular unit, and between adjacent rotor cellular unit, splicing is fixedly connected with;
Described load support and release platform comprise pair of support arms and clamping device, described hold-down arm and main body cellular unit hinged, the hinged place between described two hold-down arms is engaged each other by transmission gear, and described transmission gear is connected with drive element; Described clamping device is arranged on inside hold-down arm.
Described flight control units is arranged on flight and controls on stay bearing plate, and described flight is controlled stay bearing plate and is arranged on main body cellular unit by nylon stud.
Honeycomb shell-like structure not only can alleviate the weight of fuselage, and silica gel line can be placed in fuselage interior.
The position of contact point of itself and goods under the state of load of support platform and rotating shaft center's in the vertical direction of steering wheel are in a straight line (or near straight line), and the resisting moment produced by goods is like this close to zero thus realize the function of self-locking.
The joint face place of described rotor cellular unit and main body cellular unit is provided with crowning, and six sides of described main body cellular unit all offer the draw-in groove to central concave, and described crowning and described draw-in groove are connected together.
By aircraft is carried out modular design and splicing, the replacing achieving aircraft is convenient, dismantles simple effect.
Described rotor cellular unit and main body cellular unit junction are fixed by large pitch bolt, described large pitch bolt is fastened in the incomplete tapped bore that rotor cellular unit is offered through main body cellular unit, and described incomplete tapped bore refers to that tapped bore two sides are plane groove.
The employing single-start thread of large pitch bolt, according to the specification size of aircraft, the height of rotor cellular unit fuselage, ensure screw thread the number of turns in the scope that 5-8 encloses, then helical pitch is fuselage height/(5 ~ 8).
Can will be inserted in incompleted thread hole between the bolt of large pitch during installation, only need to rotate a less angle relative to incompleted thread hole and just the bolt of large pitch can be tightened.Also only needing to rotate about four during dismounting/large pitch bolt can be extracted from incomplete tapped bore once enclosing.Also the efficiency of its dismounting is accelerated in this way.
Joint face between described adjacent rotor cellular unit, wherein, a side is provided with chute, and another side is provided with the lug boss mated with chute.
Described rotor cellular unit surface is provided with snap fit, is fastened on snap fit, is connected and fixed adjacent rotor cellular unit by buckle.
Be inserted in the snap fit of two adjacent rotor cellular units by corresponding for hole longer for buckle width between centers, then 90-degree rotation just can block the position of its rotor cellular unit, thus serves fixing effect.
Described clamping device both sides are provided with plate spring, and the two ends of described plate spring are connected with the expansion link be fixed on hold-down arm by L-type pipe link.
Each hold-down arm at least comprises a set of expansion link, often overlaps expansion link and comprise two, be set in parallel in the both sides of hold-down arm respectively; The both sides of described expansion link are connected with strut bar.
Front leg support strut and rear leg support strut is respectively arranged with in hold-down arm both sides, front leg support strut and rear leg support strut move with expansion link, plate spring two ends change with the distance between the pin strut bar of front and back, thus change the curvature of plate spring, adjustment sheet spring to reach the suitable gripping power of different loads box, thus is applicable to the goods of various dissimilar size in the length of groove.
On clamping device, both sides are all provided with plate spring, and when goods clamping, plate spring will be out of shape and contact closely with the appearance profile of cargo load box.
Described drive element is steering wheel, and steering wheel is fixed on steering wheel mount pad, and described steering wheel mount pad is fixed on below main body cellular unit.
Transmission gear between described two hold-down arms is partial gear, and wherein, a partial gear is connected with the rotating shaft of described steering wheel, and another partial gear is fixed on below described main body cellular unit by L-type gear pivot shaft.
Elastomeric layer is equipped with outside described rotor cellular unit.
When aircraft unstability is born, play the effect of buffering.
Described main body cellular unit and rotor honeycomb list at least offer three well-distributed through holes.
Alleviate the weight of aircraft further.
Beneficial effect
The invention provides a kind of cell type six rotor transporter aircraft, comprise main body cellular unit, the multiple wing and the load support be connected to below main body cellular unit and release platform; Described main body cellular unit and the multiple wing are the honeycomb shell-like structure on regular hexagon limit, and this structure is conducive to the intensity that improve aircraft, alleviates the weight of the use material of aircraft because of shelly simultaneously; ; The described multiple wing comprises six rotor cellular units, and each rotor cellular unit is provided with screw propeller and brushless motor, and described screw propeller is driven by brushless motor; Described six rotor cellular units are evenly distributed on around main body cellular unit, and each rotor cellular unit is all connected with main body cellular unit, are fixedly connected with and adopt some easily detachable attaching partss as buckle, snap fit etc. between adjacent rotor cellular unit.User friendly dismounting; The elastomeric material that the surrounding of rotor cellular unit arranges serves the effect of elastic buffer too, reduces the risk that the high main body cellular unit of price is impaired; Because rotor unit is all identical, producer can the single rotor cellular unit of direct marketing, and it is for subsequent use that user can buy rotor cellular unit more, when the damage of certain rotor cellular unit when taking a flight test out of doors, directly can change this rotor cellular unit.Greatly shorten maintenance time, realize simple replacing efficiently.In the model plane flight course of some important events, the generation of accident can be successfully managed.Described load support and release platform comprise pair of support arms and clamping device, described hold-down arm and main body cellular unit hinged, engaged each other by transmission gear between described two hold-down arms, described transmission gear is connected with drive element, can two-axle interlocking be realized by a drive element, complete the support of load or the process of release; Described clamping device is arranged on inside hold-down arm, and this mechanism can clamp the load goods of different size size in certain limit.
Accompanying drawing explanation
Fig. 1 is the axis side view such as grade of aircraft of the present invention;
Fig. 2 is the structure front elevation of aircraft of the present invention;
Fig. 3 be aircraft of the present invention rotor cellular unit between connection structure schematic diagram;
Fig. 4 is the buckle connection diagram of main body cellular unit of the present invention and rotor cellular unit;
Fig. 5 is the close-up schematic view that Fig. 4 is labeled as A position, and wherein, (a) is birds-eye view, and (b) is front elevation;
Fig. 6 is large pitch bolt arrangement and scheme of installation, and wherein, (a) is the negative thread schematic diagram of main body cellular unit and rotor cellular unit, and (b) is the structural representation of large pitch bolt;
Fig. 7 is the axis side views such as the structure of load support platform of the present invention;
Fig. 8 is the structure schematic top plan view of load support platform of the present invention;
Fig. 9 is the load tray substructure figure of load support platform of the present invention;
Figure 10 is the structural representation of expansion link of the present invention;
Label declaration: 1-elastomeric layer, 2-criss-cross motor mount, the positive and negative oar of 3-ATG, 4-brushless motor, 5-oar seat, 6-nylon stud, 7-flight control units, 8-flight controls stay bearing plate, 9-buckle, 10-snap fit, 11-rotor cellular unit, 12-main body cellular unit, 13-L type gear wheel shaft, 14-partial gear hold-down arm, 15-steering wheel, 16-load goods box, 17-steering wheel mount pad, 18-Antisliding bolt, 19-large pitch bolt, 20-plate spring, 21-first expansion link, 22-second expansion link, 23-front leg support strut, 24-rear leg support strut, 25-crowning, 26-draw-in groove, 27-lug boss, 28-chute, 29-L type pipe link.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is described further.
As depicted in figs. 1 and 2, a kind of cell type six rotor transporter aircraft, comprises main body cellular unit 12, the multiple wing and the load support be connected to below main body cellular unit and release platform;
Described main body cellular unit 12 and the multiple wing are the honeycomb shell-like structure on regular hexagon limit;
Be provided with flight control units 7 in the middle of described main body cellular unit 12, also comprise the weather gauge of aircraft indispensability, receiver, electrokinetic cell and six groups of electronic governors;
The described multiple wing comprises six rotor cellular units 11, and each rotor cellular unit is provided with screw propeller and brushless motor 4, described screw propeller is driven by brushless motor 4; Described six rotor cellular units are evenly distributed on the surrounding of main body cellular unit, and each rotor cellular unit is all connected with main body cellular unit, and between adjacent rotor cellular unit, splicing is fixedly connected with;
Described screw propeller is that the positive and negative oar 3 of ATG is arranged on brushless motor by oar seat 5;
Described brushless motor 4 is arranged on criss-cross motor mount 2;
The junction of adjusting at brushless motor 4 and electricity adopts the form of banana head to be connected, and can conveniently plug, the operations such as debugging.
Described load support and release platform comprise pair of support arms and clamping device, described hold-down arm and main body cellular unit hinged, engaged each other by a pair transmission gear between described two hold-down arms, described transmission gear is connected with drive element; Described clamping device is arranged on inside hold-down arm.
Described flight control units is fixed on flight and controls on stay bearing plate 8, and described flight is controlled stay bearing plate and is arranged on main body cellular unit by nylon stud 6.
Honeycomb shell-like structure not only can alleviate the weight of fuselage, and silica gel line can be placed in fuselage interior.
The position of contact point of itself and load goods box 16 under the state of load of support platform and rotating shaft center's in the vertical direction of steering wheel 15 are in a straight line (or near straight line), and the resisting moment produced by goods is like this close to zero thus realize the function of self-locking.
As shown in Figure 4, the joint face place of described rotor cellular unit and main body cellular unit is provided with crowning, and six sides of described main body cellular unit all offer the draw-in groove to central concave, and described crowning 25 is connected together with described draw-in groove 26.
By aircraft is carried out modular design and splicing, the replacing achieving aircraft is convenient, dismantles simple effect.
As shown in Figure 6, described rotor cellular unit and main body cellular unit junction are fixed by large pitch bolt 19, described large pitch bolt is fastened in the incomplete tapped bore that rotor cellular unit is offered through main body cellular unit, and described incomplete tapped bore refers to that tapped bore two sides are plane groove.
Can will be inserted in incompleted thread hole between the bolt of large pitch during installation, only need to rotate a less angle relative to incompleted thread hole and just the bolt of large pitch can be tightened.Also only needing to rotate about four during dismounting/large pitch bolt can be extracted from incomplete tapped bore once enclosing.Also the efficiency of its dismounting is accelerated in this way.
As shown in Figure 3, the joint face between described adjacent rotor cellular unit, wherein, a side is provided with chute, and another side is provided with the lug boss 27 mated with chute.
Carry out installation fix according to the convex surface (concave surface) of the concave surface (convex surface) of the rotor cellular unit rotor cellular unit adjacent with its both sides is corresponding during installation, namely lug boss 27 is mounted in chute 28.
As shown in Figure 5, described rotor cellular unit surface is provided with snap fit, is fastened on snap fit, is connected and fixed adjacent rotor cellular unit by buckle 9.
Be inserted in the snap fit of two adjacent rotor cellular units by corresponding for hole longer for buckle width between centers, then 90-degree rotation just can block the position of its rotor cellular unit, thus serves fixing effect.
In order to prevent shearing stress to causing buckle to be fractureed greatly, so the fuselage of each rotor cellular unit is connected by two snap fits 10 of two snap fits with adjacent rotor cellular unit fuselage 11, because the fuselage of each rotor cellular unit has a rotor cellular unit to be connected along anticlockwise direction, each rotor cellular unit arranges 4 snap fits.
Described clamping device both sides are provided with plate spring 20, and the two ends of described plate spring 20 are connected with the expansion link be fixed on hold-down arm by L-type pipe link 29.
Described L-type pipe link moves with expansion link, and the distance between the L-type pipe link of plate spring 20 two ends changes, thus changes the curvature of plate spring, to be applicable to the goods of various dissimilar size.
Described clamping device both sides are provided with plate spring, and the two ends of described plate spring are connected with the expansion link be fixed on hold-down arm by L-type pipe link.
Each hold-down arm at least comprises a set of expansion link, often overlaps expansion link and comprise two, be set in parallel in the both sides of hold-down arm respectively; The outside of described expansion link is connected with strut bar.
Front leg support strut and rear leg support strut is respectively arranged with in hold-down arm both sides, front leg support strut and rear leg support strut move with expansion link, plate spring two ends change with the distance between the pin strut bar of front and back, thus change the curvature of plate spring, adjustment sheet spring to reach the suitable gripping power of different cargo load box, thus is applicable to the goods of various dissimilar size in the length of groove.
On clamping device, both sides are all provided with plate spring, and when goods clamping, plate spring will be out of shape and contact closely with the appearance profile of cargo load box.
Described drive element is steering wheel, and steering wheel 15 is fixed on steering wheel mount pad 17, and described steering wheel mount pad is fixed on below main body cellular unit by Antisliding bolt 18.
Transmission gear between described two hold-down arms is partial gear, and wherein, a partial gear is connected with the rotating shaft of described steering wheel, and another partial gear is fixed on below described main body cellular unit by L-type gear pivot shaft.
Elastomeric layer 1 is equipped with outside described rotor cellular unit.
When aircraft unstability is born, play the effect of buffering.
Described main body cellular unit and rotor honeycomb list at least offer three well-distributed through holes.
As shown in Figure 7 and Figure 8, steering wheel 15 is connected and fixed by steering wheel mount pad and main body cellular unit.The output of steering wheel 15 is coupling a partial gear.The supporting way of another partial gear is connected and fixed by a L-type gear pivot shaft 13 and main body cellular unit.First expansion link 21 and the second expansion link 22 are connected on front leg support strut 23 and rear leg support strut 24 by screw thread fit.
L-type pipe link is provided with plate spring to stretch draw-in groove, the distance of plate spring between L-type pipe link changes with the length variations of expansion link, and plate spring is rollable in flexible draw-in groove.
Expansion link is three pair rod as shown in Figure 10, and wherein, the second pole and partial gear hold-down arm 14 are fixed together.The two ends of the first pole and three pair rod are outside thread, can with the screw-internal thread fit on the hold-down arm of front and back foot rest, and the outside dimension that fixing and three pair rod and first segment external diameter exceedes second section is less than 0.02mm.The size changing load support and release platform only needs expansion link in axial direction to extend.
Flight control units can receive the operation signal of the remote controller transmitted from receiver, by controlling the anglec of rotation of steering wheel 15, can realize the two-axle interlocking of the hold-down arm of load platform.When zero load is flown, the rotation that can control steering wheel makes hold-down arm parallel to the ground.When load is flown, the rotation that can control steering wheel comes the position of the hold-down arm by regulating load support and release platform.Thus control load platform is the state for load-supporting state or release load.
As shown in Figure 9, aircraft is the goods carrying different dimensionss.Only load goods need be put in the box of size corresponding to it.Again the upper cover of box is advanced in groove.The adjustment stroke of expansion link of aircraft and the sinuousness of plate spring can control its gripping power to goods, prevent coming off because of shake of its goods.
According to load support platform to the force direction of load box straight up, be in a straight line resisting moment that (or near straight line) produced by load like this of the position of contact point on itself and load goods box 16 both sides under loaded state of support platform and rotating shaft center's in the vertical direction of hold-down arm realizes the function of self-locking close to zero.
Claims (10)
1. a cell type six rotor transporter aircraft, is characterized in that, comprises main body cellular unit, the multiple wing and the load support be connected to below main body cellular unit and release platform;
Described main body cellular unit and the multiple wing are the honeycomb shell-like structure on regular hexagon limit;
Flight control units is provided with in the middle of described main body cellular unit;
The described multiple wing comprises six rotor cellular units, and each rotor cellular unit is provided with screw propeller and brushless motor, and described screw propeller is driven by brushless motor; Described six rotor cellular units are evenly distributed on the surrounding of main body cellular unit, and each rotor cellular unit is all connected with main body cellular unit, and between adjacent rotor cellular unit, splicing is fixedly connected with;
Described load support and release platform comprise pair of support arms and clamping device, described hold-down arm and main body cellular unit hinged, engaged each other by transmission gear between described two hold-down arms, described transmission gear is connected with drive element; Described clamping device is arranged on inside hold-down arm.
2. a kind of cell type six rotor transporter aircraft according to claim 1, it is characterized in that, the joint face place of described rotor cellular unit and main body cellular unit is provided with crowning (25), six sides of described main body cellular unit all offer the draw-in groove (26) to central concave, and described crowning and described draw-in groove (26) are connected together.
3. a kind of cell type six rotor transporter aircraft according to claim 2, it is characterized in that, described rotor cellular unit and main body cellular unit junction are fixed by large pitch bolt, described large pitch bolt is through in the incomplete tapped bore that main body cellular unit is fastened on rotor cellular unit and main body cellular unit is offered, and described incomplete tapped bore refers to that tapped bore two sides are plane groove.
4. a kind of cell type six rotor transporter aircraft according to claim 1, it is characterized in that, joint face between described adjacent rotor cellular unit, wherein, a side is provided with chute (28), and another side is provided with the lug boss (27) mated with chute (28).
5. a kind of cell type six rotor transporter aircraft according to claim 4, is characterized in that, described rotor cellular unit surface is provided with snap fit, is fastened on snap fit, is connected and fixed adjacent rotor cellular unit by buckle.
6. a kind of cell type six rotor transporter aircraft according to claim 1, is characterized in that, described clamping device both sides are provided with plate spring, and the two ends of described plate spring are connected with the expansion link be fixed on hold-down arm by L-type pipe link.
7. described a kind of cell type six rotor transporter aircraft according to claim 1, it is characterized in that, described drive element is steering wheel, and steering wheel is fixed on steering wheel mount pad, and described steering wheel mount pad is fixed on below main body cellular unit.
8. a kind of cell type six rotor transporter aircraft according to claim 8, it is characterized in that, transmission gear between described two hold-down arms is partial gear, wherein, a partial gear is connected with the rotating shaft of described steering wheel, and another partial gear is fixed on below described main body cellular unit by L-type gear pivot shaft.
9. a kind of cell type six rotor transporter aircraft according to any one of claim 1-8, is characterized in that, be equipped with elastomeric layer outside described rotor cellular unit.
10. a kind of cell type six rotor transporter aircraft according to any one of claim 1-8, is characterized in that, described main body cellular unit and rotor honeycomb list at least offer three well-distributed through holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510050112.2A CN104608923B (en) | 2015-01-31 | 2015-01-31 | A kind of honeycomb fashion six rotor transporter aircrafts |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510050112.2A CN104608923B (en) | 2015-01-31 | 2015-01-31 | A kind of honeycomb fashion six rotor transporter aircrafts |
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| CN104608923A true CN104608923A (en) | 2015-05-13 |
| CN104608923B CN104608923B (en) | 2016-05-11 |
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| CN201510050112.2A Expired - Fee Related CN104608923B (en) | 2015-01-31 | 2015-01-31 | A kind of honeycomb fashion six rotor transporter aircrafts |
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