CN105292457A - Heavy-load unmanned aerial vehicle - Google Patents
Heavy-load unmanned aerial vehicle Download PDFInfo
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- CN105292457A CN105292457A CN201510782290.4A CN201510782290A CN105292457A CN 105292457 A CN105292457 A CN 105292457A CN 201510782290 A CN201510782290 A CN 201510782290A CN 105292457 A CN105292457 A CN 105292457A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention discloses a heavy-load unmanned aerial vehicle. The heavy-load unmanned aerial vehicle comprises a fuselage assembly and more than three arm assemblies, one end of each arm assembly is connected with the fuselage assembly, the other end of each arm assembly is provided with two coaxially arranged rotor components, each rotor component comprises a propeller and a motor, and the bottom part of the fuselage assembly is provided with a loading platform for loading articles. The heavy-load unmanned aerial vehicle has the advantages of large pulling force, capability of adjusting flight gravity center, good loading damping effect, good flight efficiency, high security and carriage convenience, and the heavy-load unmanned aerial vehicle can meet the heavy load demands.
Description
Technical field
The present invention is mainly concerned with unmanned plane field, is specifically related to a kind of heavy－duty unmanned plane.
Background technology
Existing rotor wing unmanned aerial vehicle field, heavy－duty type of aircraft is little, and most of load-carrying is all no more than 3KG, for the carry of some large quality, does not have suitable flying platform.Meanwhile, the existing flying platform also following technical matters of ubiquity:
(1) existing aircraft pulling force is inadequate, can not meet the large pulling force demand of heavy－duty.
(2) existing aircraft is not suitable for the carry platform of large quality carry specially.Because the volume of each large quality carry thing, quality, attachment point are different, cause the center of gravity of each large quality carry thing self also different, if take unified position carry on unmanned plane, this will certainly cause the center of flying gravity of unmanned plane unstable, man-machine flight attitude is changed, directly affects stability and the safety of unmanned plane, even may cause time serious can not take off, danger such as falling machine of dropping in the air.
(3) the carry platform damping effect of existing aircraft is not good, can not meet the damping requirement of heavy－duty.Unmanned plane can cause certain vibration environment in flight course, and this vibrations impact for stationarity exigent unmanned plane carry thing is very large; Especially the high-power aircraft of heavy－duty inherently produces larger flight vibrations, if do not carried out effective damping filter shake to these vibrations, the normal operation (operation is unstable as caused, fuzzy, the light shake of making a video recording, device failure etc.) of large quality carry thing will certainly be had a strong impact on.
(3) existing Flight Vehicle Structure arranges scientific and reasonable not, and development size is excessive, and folding mode is unreasonable, and transport is difficult, not Portable belt.
(4) existing aircraft is by the restriction of the limited or take-off weight of portable number of batteries, and the hang time is short, the working effect that out of reach is desirable, is especially not suitable for the flight requirement of heavy－duty.
(5) existing aircraft flight safety factor is low, and safety of structure is low, and landing is dangerous, can not deal with the emergency case of heavy－duty.
Summary of the invention
Technical matters solved by the invention is: for prior art Problems existing, provides large, the adjustable center of flying gravity of a kind of pulling force, carry good damping effect, flight usefulness is good, safety is high, portable heavy－duty unmanned plane.
For solving the problems of the technologies described above, the present invention by the following technical solutions:
A kind of heavy－duty unmanned plane, comprise the horn assembly of fuselage assembly and more than three, one end of each described horn assembly is connected with fuselage assembly, the other end of each described horn assembly is equipped with two coaxially arranged rotor assemblies, each described rotor assemblies includes a screw propeller and a motor, and the bottom of described fuselage assembly is provided with the carry platform for carry article.
As a further improvement on the present invention, described carry platform comprises the center of gravity adjusting part for adjusting center of gravity and the carry assembly for carry article, described center of gravity adjusting part is connected with fuselage assembly, described carry assembly carry is on center of gravity adjusting part, and described center of gravity adjusting part is provided with multiple first carry portion to regulate the level attitude of carry assembly.
As a further improvement on the present invention, described center of gravity adjusting part comprises more than the one center of gravity adjust bar be arranged at bottom unmanned plane, and described carry assembly is connected with center of gravity adjust bar and can adjusts level attitude along the axial direction of center of gravity adjust bar.
As a further improvement on the present invention, described carry assembly comprises the shock-absorbing support plate, elastomeric damper member and the upper carry plate for carry article that superpose successively from bottom to up, described shock-absorbing support plate is connected with center of gravity adjusting part, and described upper carry plate is carried in elastomeric damper member to be filtered out the vibrations that unmanned plane produces by elastomeric damper member.
As a further improvement on the present invention, described shock-absorbing support plate is provided with several through hole, described carry assembly comprises several carry bar, and one end of several described carry bar is connected with upper carry plate, and the other end of several described carry bar passes through hole and do not contact with shock-absorbing support plate.
As a further improvement on the present invention, described carry assembly comprises the lower carry plate be located at below shock-absorbing support plate, described lower carry plate is connected to make article carry on lower carry plate with the several carry bars through through hole, and described lower carry plate is provided with multiple for regulating the second carry portion of article carry position.
As a further improvement on the present invention, described elastomeric damper member is the multiple elastic shock absorption balls be uniformly distributed on shock-absorbing support plate, one end of each described elastic shock absorption ball contacts with shock-absorbing support plate, and the other end of each described elastic shock absorption ball contacts with upper carry plate.
As a further improvement on the present invention, described fuselage assembly comprises the upper plate arranged successively from top to bottom, middle plate and lower plate, is set to control circuit mounting layer between described upper plate and middle plate, is set to big current pull up circuit mounting layer between described middle plate and lower plate.
As a further improvement on the present invention, be provided with the side shield for the formation of surrounding space between described middle plate and lower plate, described lower plate is provided with even number battery component in the outside of side shield, battery component described in even number is evenly distributed in the both sides of fuselage assembly.
As a further improvement on the present invention, the position of the corresponding battery component in both sides of described upper plate is respectively equipped with a battery hatch, and one end and the upper plate of described battery hatch are hinged, and the other end of described battery hatch is locked by locking piece and lower plate.
As a further improvement on the present invention, described fuselage assembly comprises the articulated section that more than three levels are protruded, described horn assembly comprises horn, each described articulated section is all hinged with a horn, and the accommodation space forming depression between adjacent two articulated sections of protruding is to make to take in accommodation space when the folding of horn assembly.
As a further improvement on the present invention, one end of described horn is provided with the jointed shaft be connected with articulated section, described horn take jointed shaft as axis rotation, and described horn and articulated section are equipped with corresponding horn locking hole, inserts locking screw rod with by horn locking in described horn locking hole.
As a further improvement on the present invention, described horn is provided with motor cabinet away from one end of articulated section, and described motor cabinet is sheathed to be fixed on horn, and the end face of described motor cabinet and bottom surface are equipped with a rotor assemblies.
As a further improvement on the present invention, each described articulated section place is equipped with the brace panel for increasing articulated section intensity, and described brace panel level is fixed on articulated section.
As a further improvement on the present invention, the below of described fuselage assembly is provided with plural alighting gear, each described alighting gear includes the cross bar of horizontal arrangement, the two ends of described cross bar are respectively provided with a leg, the bottom surface of described cross bar and fuselage assembly removably connects, and each described leg is provided with buffer part near the one end on ground.
As a further improvement on the present invention, the top of described fuselage assembly is provided with parachute assembly.
Compared with prior art, the invention has the advantages that:
(1) heavy－duty unmanned plane of the present invention, adopts the dynamic mode of two oar double-motor up and down, for unmanned plane provides extremely strong pulling force, ensure that the flying power demand of heavy－duty.Meanwhile, for improving stability and the safety of carry, the present invention arranges special carry platform in the bottom at fuselage assembly, makes the carry thing of large quality that special mount point and unmanned plane can be had to realize being connected, carry is stablized, and ensure that heavy－duty flight the safe and effective of operation is carried out.
(2) heavy－duty unmanned plane of the present invention, carry platform is not only provided with carry assembly, also specially be provided with center of gravity adjusting part, make certain fixed position being fixed on unmanned plane that carry assembly is no longer single, but the center of flying gravity of unmanned plane can be adjusted flexibly according to different large quality carry things, to realize the splendid flight usefulness of unmanned plane.Finally make unmanned plane can the different large quality carry thing of carry, can meet multiple different job requirements, the range of use of unmanned plane be wider.
(3) heavy－duty unmanned plane of the present invention, for offsetting the strong motion that heavy－duty aircraft brings, reduce the vibration influence to carry thing, carry assembly of the present invention has Aseismatic Design, enable the vibrations filtering out unmanned plane generation, the strong motion of heavy－duty aircraft is made to the raw vibration influence of the carry produce on carry assembly, can not well to meet the flight requirement of heavy－duty.
(4) heavy－duty unmanned plane of the present invention, fuselage assembly takes the design of three ply board, and is optimized layout to the device on fuselage assembly, makes fuselage assembly structure simply compact, alleviates the weight of unmanned plane.Meanwhile, horn assembly and fuselage assembly hinged, after making folding, unmanned plane volume is little, be convenient to transport and carry.
(5) heavy－duty unmanned plane of the present invention, take motor to be first arranged on motor cabinet is set in again the mounting means on horn, actv. ensure that the intensity of motor cabinet and horn; Make easier for installation, firm, and the perfect mounting means supporting upper and lower double-motor, effectively ensure that upper and lower two motor coaxle hearts, ensure that the maximum pull of unmanned plane and the stationarity of flight.
(6) heavy－duty unmanned plane of the present invention, by taking two battery components as propulsion source, for heavy－duty unmanned plane provides powerful electric power support, meets the demand of heavy－duty transport.Meanwhile, by adopting the particular design such as side shield, battery hatch, two alighting gear, parachute assembly, further ensure that the safety and stability of heavy－duty unmanned plane.
Accompanying drawing explanation
Fig. 1 is the spatial structure principle schematic at heavy－duty unmanned plane first visual angle of the present invention.
Fig. 2 is the spatial structure principle schematic at heavy－duty unmanned plane second visual angle of the present invention.
Fig. 3 is the spatial structure principle schematic at heavy－duty unmanned plane the 3rd visual angle of the present invention.
Fig. 4 is the decomposition texture principle schematic of heavy－duty unmanned plane of the present invention.
Fig. 5 is the spatial structure principle schematic of the carry platform of heavy－duty unmanned plane of the present invention.
Fig. 6 is the spatial structure principle schematic at another visual angle of carry platform of heavy－duty unmanned plane of the present invention.
Fig. 7 is the decomposition texture principle schematic of the fuselage assembly of heavy－duty unmanned plane of the present invention.
Fig. 8 is the plan structure principle schematic after heavy－duty unmanned plane horn assembly of the present invention folding.
Fig. 9 is the spatial structure principle schematic after heavy－duty unmanned plane horn assembly of the present invention folding.
Figure 10 is the decomposition texture principle schematic of heavy－duty unmanned plane horn assembly of the present invention.
Marginal data:
1, fuselage assembly; 11, articulated section; 111, brace panel; 12, upper plate; 121, battery hatch; 13, middle plate; 14, lower plate; 15, side shield; 2, horn assembly; 21, rotor assemblies; 211, screw propeller; 212, motor; 22, horn; 221, jointed shaft; 222, horn locking hole; 223, locking screw rod; 224, pipe end plug member; 23, motor cabinet; 3, carry platform; 31, center of gravity adjusting part; 311, center of gravity adjust bar; 32, carry assembly; 321, shock-absorbing support plate; 3211, through hole; 322, elastomeric damper member; 323, upper carry plate; 324, carry bar; 325, lower carry plate; 4, battery component; 5, alighting gear; 51, cross bar; 52, leg; 521, buffer part; 6, parachute assembly.
Detailed description of the invention
Below in conjunction with specific embodiments and the drawings, the present invention is described in further detail.
As shown in Figures 1 to 10, the invention provides a kind of heavy－duty unmanned plane, comprise the horn assembly 2 of more than fuselage assembly 1 and three, one end of each horn assembly 2 is connected with fuselage assembly 1, the other end of each horn assembly 2 is equipped with two coaxially arranged rotor assemblies 21, each rotor assemblies 21 includes a screw propeller 211 and a motor 212, and the bottom of fuselage assembly 1 is provided with the carry platform 3 for carry article.For realizing the requirement of heavy－duty, improve the lift of unmanned plane, the present invention is provided with the horn assembly 2 of more than three, on each horn assembly 2, be equipped with two groups of coaxially arranged screw propellers 211 and a motor 212 simultaneously, adopt the dynamic mode of two oar double-motor up and down, for unmanned plane provides extremely strong pulling force, ensure that the flying power demand of heavy－duty.Simultaneously, because the carry of this unmanned plane is to the carry thing liking large quality, for improving stability and the safety of carry, the present invention arranges special carry platform 3 in the bottom at fuselage assembly 1, make the carry thing of large quality that special mount point and unmanned plane can be had to realize being connected, carry is stablized, and ensure that heavy－duty flight the safe and effective of operation is carried out.
As shown in Figures 2 to 5, further, in the preferred embodiment, carry platform 3 comprises the center of gravity adjusting part 31 for adjusting center of gravity and the carry assembly 32 for carry article, center of gravity adjusting part 31 is connected with fuselage assembly 1, carry assembly 32 carry is on center of gravity adjusting part 31, and center of gravity adjusting part 31 is provided with multiple first carry portion to regulate the level attitude of carry assembly 32.
When different large quality carry thing carries is on carry assembly 32, because the volume of each large quality carry thing, quality, attachment point are different, cause the center of gravity of each large quality carry thing self also different, as being directly connected with unmanned plane by carry assembly 32, the center of flying gravity of unmanned plane will certainly be caused unstable.For this technical matters, the present invention is provided with the center of gravity adjusting part 31 be connected with fuselage assembly 1, and center of gravity adjusting part 31 is provided with multiple first carry portion.Operating personal can according to the center of gravity situation of difference large quality carry thing, the level attitude of rational flexible carry assembly 32 that carry assembly 32 carry is come up in the first different carry portions, until the center of flying gravity of unmanned plane is adjusted to optimum regime, enable steady, safe the taking off and operation of unmanned plane.
Such particular design, makes certain fixed position being fixed on unmanned plane that carry assembly 32 is no longer single, but can adjust the center of flying gravity of unmanned plane flexibly according to different large quality carry things, to realize the splendid flight usefulness of unmanned plane.Finally make unmanned plane can the different large quality carry thing of carry, can meet multiple different job requirements, the range of use of unmanned plane be wider.
Further, in the preferred embodiment, center of gravity adjusting part 31 comprises more than the one center of gravity adjust bar 311 be arranged at bottom unmanned plane, carry assembly 32 is connected with center of gravity adjust bar 311 and can adjusts level attitude along the axial direction of center of gravity adjust bar 311, and namely carry assembly 32 axially can realize the carry of multiple diverse location at whole center of gravity adjust bar 311.In the present embodiment, center of gravity adjust bar 311 is two, and be parallel to each other be horizontally placed on bottom unmanned plane, carry assembly 32 is connected with two center of gravity adjusts bar 311 respectively and axially can adjusts level attitude along center of gravity adjust bar 311.In the present embodiment, center of gravity adjust bar 311 designs for Hollow circular beam, and carry assembly 32 is connected with two center of gravity adjusts bar 311 by four pipe clamp fixed blocks.In other embodiments, center of gravity adjust bar 311 also can design for special pipe, and attaching parts is designed to other attaching partss of corresponding cooperation too.Center of gravity adjust bar 311 structure is simple, light, the use of very applicable unmanned plane; And carry assembly 32 along center of gravity adjust bar 311 slide axially regulate center of gravity regulative mode also simple to operate, time saving and energy saving.
It should be noted that, under the technology of said structure and embodiment inspires, those of ordinary skill in the art can also expect form center of gravity adjusting part 31 being set to other easily, as arranged a centre of gravity adjustment plate in the bottom of fuselage assembly 1, multiple first carry portion is multiple hooks that centre of gravity adjustment plate is arranged, and carry assembly 32 is by linking up with carry on center of gravity regulating plate.When needs adjustment center of gravity time, can by carry assembly 32 carry on different hooks to regulate the level attitude of carry assembly 32, until the center of flying gravity of unmanned plane is adjusted to optimum regime.Certainly, the center of gravity adjust bar 311 bottom fuselage assembly 1 can also being set to other forms, as being set to cross by two center of gravity adjusts bar 311, making carry assembly 32 can realize the adjustment of four direction all around; As center of gravity adjust bar 311 being set to circular or multiple circular concentric, to realize the adjustment of multiple dimensions of carry assembly 32.
Therefore under the inspiration of the said structure of the present embodiment, as long as reached the technique effect of the center of flying gravity of adjustment unmanned plane by the horizontal carry position of adjustment carry assembly 32, all should belong to protection scope of the present invention.
As shown in Figure 5 and Figure 6, further, in the preferred embodiment, carry assembly 32 comprises the shock-absorbing support plate 321, elastomeric damper member 322 and the upper carry plate 323 for carry article that superpose successively from bottom to up, shock-absorbing support plate 321 is connected with center of gravity adjusting part 31, and upper carry plate 323 is carried in elastomeric damper member 322 to be filtered out the vibrations that unmanned plane produces by elastomeric damper member 322.When unmanned plane creates strong motion in flight course, vibrations can first be conducted to the shock-absorbing support plate 321 be attached thereto, conduct to the elastomeric damper member 322 be located on shock-absorbing support plate 321 again, elastomeric damper member 322 is owing to having elastic shock attenuation ability, therefore, it is possible to well filter out the vibrations of unmanned plane generation, make vibrations can not conduct to the upper carry plate 323 be carried in elastomeric damper member 322 again, the vibrations that unmanned plane is produced can not to the raw vibration influence of large quality carry produce, realize flexibly connecting between large quality carry thing and unmanned plane, well meet the flight job requirements of large quality carry thing.
Further, in the preferred embodiment, shock-absorbing support plate 321 is provided with several through hole 3211, and carry assembly 32 comprises several carry bar 324, one end of several carry bar 324 is connected with upper carry plate 323, and the other end of several carry bar 324 passes through hole 3211 and do not contact with shock-absorbing support plate 321.Several carry bar 324 can carry out fixedly contacting of multiple point with large quality carry thing, and fixed effect is better, flies safer.And because shock-absorbing support plate 321 can not come in contact with carry bar 324, also can not by vibrations conduction to carry bar 324 when shock-absorbing support plate 321 is shaken, further ensure the vibration environment that unmanned plane causes thus to impact large quality carry thing, effectively ensure that the stationarity of large quality carry thing.
Further, in the preferred embodiment, carry assembly 32 comprises the lower carry plate 325 be located at below shock-absorbing support plate 321, lower carry plate 325 is connected to make article carry on lower carry plate 325 with the several carry bars 324 through through hole 3211, and lower carry plate 325 is provided with multiple for regulating the second carry portion of article carry position.Such particular design has three advantages: one is by arranging lower carry plate 325, make large quality carry thing can with realize face between lower carry plate 325 and contact, fixed effect is better.Two is because lower carry plate 325 is provided with multiple the second carry portion for carry article, when needs adjustment center of flying gravity, also can adjust different carry positions to realize the fine setting of center of flying gravity by multiple second carry portion.The centre of gravity adjustment mode of lower carry plate 325 and the centre of gravity adjustment mode of center of gravity adjusting part 31 match, and this dual regulation design can realize the center of flying gravity adjustment of different heavy－duty more accurately, easily.
Further, in the preferred embodiment, elastomeric damper member 322 is for being uniformly distributed in the multiple elastic shock absorption balls on shock-absorbing support plate 321, and one end of each elastic shock absorption ball contacts with shock-absorbing support plate 321, and the other end of each elastic shock absorption ball contacts with upper carry plate 323.Shock-absorbing support plate 321 and upper carry plate 323 are equipped with multiple fixed orifice portion for fixing elastic shock absorption ball.By the particular design of upper carry plate 323, shock-absorbing support plate 321, this flat superposition of lower carry plate 325, one is that actv. ensure that multiple elastic shock absorption ball can maintain in one plane, and the Distributed Design of flat board can increase the distribution area of multiple elastic shock absorption ball, make stressed more even, reach best damping filter shake effect.Two is particular design of this flat superposition, can ensure the integral rigidity of whole carry assembly 32 further, can ensure stable, the safe carry of large quality carry thing.
It should be noted that; under the technology of said structure and embodiment inspires; those of ordinary skill in the art can also expect elastomeric damper member 322 to take other mode to arrange easily; as adopted sponge kind elasticity thing, the caoutchouc elasticity thing of monoblock; or adopt spring or other elastic components of multiple distribution; all can reach the technique effect of damping filter shake, all should belong to protection scope of the present invention.
As shown in Figure 7, further, in the preferred embodiment, fuselage assembly 1 comprises upper plate 12, middle plate 13 and the lower plate 14 of arranging successively from top to bottom, be set to control circuit mounting layer between upper plate 12 and middle plate 13, between middle plate 13 and lower plate 14, be set to big current pull up circuit mounting layer.Two-layer design actv. prevents the interference of signal, adds the reliability of unmanned plane during flying.Between middle plate 13 and lower plate 14, be provided with the side shield 15 for the formation of surrounding space, the big current pull up circuit components and parts installed in the involutory confining space of side shield 15 energy are done to protect further, and also centering plate 13 serves good supporting role simultaneously.Lower plate 14 is provided with even number battery component 4 in the outside of side shield 15, and even number battery component 4 is evenly distributed in the both sides of fuselage assembly 1.
Because the present invention is heavy－duty unmanned plane, need the article quality of carry heavier.For obtaining usefulness of well flying, the present invention devises plural battery component 4 especially as propulsion source, for unmanned plane provides powerful electric power support.Simultaneously, because battery component 4 volume is comparatively large, heavier-weight, for making unmanned plane keep gravity balance, it is also the space of compression fuselage assembly 1 further simultaneously, unmanned plane is tried one's best miniaturization, and plural even number battery component 4 is evenly distributed in the both sides of fuselage assembly 1 by the present invention.In the present embodiment, be provided with two battery components 4 and be arranged symmetrically, the position of upper plate 12 and the corresponding battery component 4 of middle plate 13 is equipped with corresponding depressed part to form the installing space of two battery components 4, by such design, make between two battery components 4 and upper plate 12, middle plate 13, lower plate 14 in very compact layout.Meanwhile, the both sides being arranged on fuselage assembly 1 that two battery components 4 are symmetrical respectively, well balance the center of gravity of unmanned plane.
Further, in the preferred embodiment, the position of the corresponding battery component 4 in both sides of upper plate 12 is respectively equipped with a battery hatch 121, and one end and the upper plate 12 of battery hatch 121 are hinged, and the other end of battery hatch 121 is locked by locking piece and lower plate 14.Battery hatch 121 can form protection to battery component 4; outer bound pair battery component 4 is avoided to cause damage; stop the possibility of battery component 4 unexpected landing aloft; improve the safety of unmanned plane; simultaneously; operator can open battery hatch 121 at any time and be taken out by battery component 4, to carry out charging or changing, operates very convenient.
As shown in Fig. 8 to Figure 10, further, in the preferred embodiment, fuselage assembly 1 comprises the articulated section 11 that more than three levels are protruded, horn assembly 2 comprises horn 22, each articulated section 11 is all hinged with a horn 22, and the accommodation space forming depression between adjacent two articulated sections 11 of protruding is to make to take in accommodation space when 2 folding of horn assembly.When not needing to use, can enter in accommodation space by horn assembly 2 folding, make horn assembly 2 can press close to fuselage assembly 1 folding, after folding, unmanned plane volume is little, is convenient to transport and carries.In the present embodiment, four articulated sections 11 and four horn assemblies, 2, four horn assemblies 2 are folded in fuselage assembly 1 respectively both sides in the mode of drawing close folding are between two provided with altogether.But it should be noted that, under the technology of said structure and embodiment inspires, those of ordinary skill in the art can also expect fuselage assembly 1 design to be square easily, after the folding of four horn assemblies 2 each individually be accommodated in an accommodation space, namely four horn assemblies 2 are received near the four edges of fuselage assembly 1 respectively.Certainly, those of ordinary skill in the art can also expect fuselage assembly 1 to be designed to polygon easily, the multiple articulated section 11 of corresponding design and multiple horn assembly 2 also can again, as fuselage assembly 1 is designed to pentagon, articulated section 11 and horn assembly 2 also equal correspondence are designed with five, five even circumferences of horn assembly 2 are distributed on fuselage assembly 1, and after folding, five horn assemblies 2 are respectively near five limits storages of fuselage assembly 1.Above variation all should belong to protection scope of the present invention.
Further, in the preferred embodiment, one end of horn 22 is provided with the jointed shaft 221 be connected with articulated section 11, horn 22 with jointed shaft 221 for axis rotation, horn 22 and articulated section 11 are equipped with corresponding horn locking hole 222, insert locking screw rod 223 in horn locking hole 222 with by horn 22 locking.In the present embodiment, locking screw rod 223 is that hand twists screw rod, after horn 22 launches, tightens locking screw rod 223 from articulated section 11, and locking screw rod 223 inserts in horn locking hole 222 and makes horn 22 keep launching shape; When horn 22 needs folding, first locking screw rod 223 is unscrewed, then by horn 22 with jointed shaft 221 for rotating in axle center, finally make horn 22 folding in the accommodation space of fuselage.The expansion locking mechanism of this design, the simple but excellent of structure, not only alleviate the weight of unmanned plane, and operation is also very easy.Meanwhile, for increasing articulated section 11 intensity, each articulated section 11 place is equipped with brace panel 111, and brace panel 111 level is fixed on articulated section 11, does to strengthen further fixing to articulated section 11.To further increase between fuselage assembly 1 with horn assembly 2 firm is connected in such design, horn assembly 2 can not be shaken at flight course, make heavy－duty unmanned plane during flying more stable.In the present embodiment, brace panel 111 is fixed on the salient of middle plate 13.
As shown in Figure 10, further, in the preferred embodiment, horn 22 is provided with motor cabinet 23 away from one end of articulated section 11, and motor cabinet 23 is sheathed to be fixed on horn 22, and the end face of motor cabinet 23 and bottom surface are equipped with a rotor assemblies 21.In the present embodiment, horn 22 is square tube type, and motor cabinet 23 is in " mouth " font coordinated with it, and the end face of motor cabinet 23 and bottom surface are equipped with corresponding motor mounting hole, and horn 22 and motor cabinet 23 are equipped with corresponding several fixed orifices.During installation, on the end face first two motors 212 being directly fixed on motor cabinet 23 respectively and bottom surface, screw propeller 211 is connected with motor 212 by oar folder, and then is enclosed within horn 22 by motor cabinet 23, and the fixed orifice utilizing bolt to pass both is fixed.By the design of science special like this, one is make motor cabinet 23 adopt integrated design, and not only actv. ensure that the intensity of motor cabinet 23, and not be used on horn 22 simultaneously and offer too many motor fixed orifice portion, also actv. ensure that the intensity of horn 22; Two is this sheathed installation methods, makes easier for installation, and motor 212 is connected more firm with horn 22, profile is simply attractive in appearance, and the perfect mounting means supporting upper and lower double-motor.Three is by offering corresponding motor mounting hole on the end face and bottom surface of motor cabinet 23, effectively ensure that upper and lower two motors 212 keep concentric, ensure that the maximum pull of unmanned plane and the stationarity of flight.In other embodiments, horn 22 also can be round tube or special pipe design, and when designing for round tube, motor cabinet 23 is designed to circular short tube shape too, then is provided with two parallel top boards and base plate at the outside face of circular short tube.In the present embodiment; be connected with fuselage assembly 1 again in the pipe of the electric connection line insertion horn 22 of upper and lower two motors 212; also be provided with pipe end plug member 224 in the end of horn 22, pipe end plug member 224 is arranged on the two ends of horn 22, and object is to protect the safety of electric connection line and attractive in appearance.
As shown in Figure 1 and Figure 4, further, in the preferred embodiment, the below of fuselage assembly 1 is provided with plural alighting gear 5, each alighting gear 5 includes the cross bar 51 of horizontal arrangement, the two ends of cross bar 51 are respectively provided with a leg 52, and cross bar 51 removably connects with the bottom surface of fuselage assembly 1, and each leg 52 is provided with buffer part 521 near the one end on ground.
Because the present invention is heavy－duty unmanned plane, need the article quality of carry heavier, when unmanned plane contacts to earth in landing, unmanned plane need bear larger ground reaction force, and this antagonistic force may cause damage even to make unmanned plane topple over to unmanned plane.For this reason, the present invention is specially provided with plural alighting gear 5 in the below of fuselage assembly 1, each alighting gear 5 includes the cross bar 51 of horizontal arrangement, cross bar 51 removably connects with the bottom surface of fuselage assembly 1, the two ends of cross bar 51 are respectively provided with a leg 52, and each leg 52 is provided with buffer part 521 near the one end on ground.This alighting gear 5 taking cross bar 51 to add leg 52 to design, rigidity is very strong, at utmost can ensure the intensity of local, effectively ensures that unmanned plane takes off the stationarity of landing and safety.Meanwhile, in the present embodiment, two battery components 4 design in the middle of two alighting gears 5, make the weight of whole heavy－duty unmanned plane all concentrate on immediate vicinity, this further ensures that the flight stability of unmanned plane.
Further, in the preferred embodiment, the top of fuselage assembly 1 is provided with parachute assembly 6.Parachute assembly 6 can release a parachute under emergency case appears in unmanned plane, enables unmanned plane safe landing, drops to minimum by the risk that air crash damages.
Below be only the preferred embodiment of the present invention, protection scope of the present invention be not only confined to above-described embodiment, all technical schemes belonged under thinking of the present invention all belong to protection scope of the present invention.It should be pointed out that for those skilled in the art, some improvements and modifications without departing from the principles of the present invention, should be considered as protection scope of the present invention.
Claims (16)
1. a heavy－duty unmanned plane, comprise the horn assembly (2) of fuselage assembly (1) and more than three, one end of each described horn assembly (2) is connected with fuselage assembly (1), it is characterized in that, the other end of each described horn assembly (2) is equipped with two coaxially arranged rotor assemblies (21), each described rotor assemblies (21) includes a screw propeller (211) and a motor (212), and the bottom of described fuselage assembly (1) is provided with the carry platform (3) for carry article.
2. heavy－duty unmanned plane according to claim 1, it is characterized in that, described carry platform (3) comprises the center of gravity adjusting part (31) for adjusting center of gravity and the carry assembly (32) for carry article, described center of gravity adjusting part (31) is connected with fuselage assembly (1), described carry assembly (32) carry is on center of gravity adjusting part (31), and described center of gravity adjusting part (31) is provided with multiple first carry portion to regulate the level attitude of carry assembly (32).
3. heavy－duty unmanned plane according to claim 2, it is characterized in that, described center of gravity adjusting part (31) comprises more than the one center of gravity adjust bar (311) be arranged at bottom unmanned plane, and described carry assembly (32) is connected with center of gravity adjust bar (311) and can adjusts level attitude along the axial direction of center of gravity adjust bar (311).
4. heavy－duty unmanned plane according to claim 2, it is characterized in that, described carry assembly (32) comprise superpose successively from bottom to up shock-absorbing support plate (321), elastomeric damper member (322) and the upper carry plate (323) for carry article, described shock-absorbing support plate (321) is connected with center of gravity adjusting part (31), and described upper carry plate (323) is carried in elastomeric damper member (322) to be filtered out the vibrations that unmanned plane produces by elastomeric damper member (322).
5. heavy－duty unmanned plane according to claim 4, it is characterized in that, described shock-absorbing support plate (321) is provided with several through hole (3211), described carry assembly (32) comprises several carry bar (324), one end of several described carry bar (324) is connected with upper carry plate (323), and the other end of several described carry bar (324) passes through hole (3211) and do not contact with shock-absorbing support plate (321).
6. heavy－duty unmanned plane according to claim 5, it is characterized in that, described carry assembly (32) comprises the lower carry plate (325) being located at shock-absorbing support plate (321) below, described lower carry plate (325) is connected to make article carry on lower carry plate (325) with the several carry bars (324) through through hole (3211), and described lower carry plate (325) is provided with multiple for regulating the second carry portion of article carry position.
7. according to the heavy－duty unmanned plane in claim 4 ~ 6 described in any one, it is characterized in that, described elastomeric damper member (322) is for being uniformly distributed in the multiple elastic shock absorption balls on shock-absorbing support plate (321), one end of each described elastic shock absorption ball contacts with shock-absorbing support plate (321), and the other end of each described elastic shock absorption ball contacts with upper carry plate (323).
8. according to the heavy－duty unmanned plane in claim 1 ~ 6 described in any one, it is characterized in that, described fuselage assembly (1) comprises the upper plate (12) arranged successively from top to bottom, middle plate (13) and lower plate (14), be set to control circuit mounting layer between described upper plate (12) and middle plate (13), between described middle plate (13) and lower plate (14), be set to big current pull up circuit mounting layer.
9. heavy－duty unmanned plane according to claim 8, it is characterized in that, be provided with between described middle plate (13) and lower plate (14) for the formation of the side shield surrounding space (15), described lower plate (14) is provided with even number battery component (4) in the outside of side shield (15), and battery component described in even number (4) is evenly distributed in the both sides of fuselage assembly (1).
10. heavy－duty unmanned plane according to claim 9, it is characterized in that, the position of the corresponding battery component (4) in both sides of described upper plate (12) is respectively equipped with a battery hatch (121), one end and the upper plate (12) of described battery hatch (121) are hinged, and the other end of described battery hatch (121) is locked by locking piece and lower plate (14).
11. according to the heavy－duty unmanned plane in claim 1 ~ 6 described in any one, it is characterized in that, described fuselage assembly (1) comprises the articulated section (11) that more than three levels are protruded, described horn assembly (2) comprises horn (22), each described articulated section (11) is all hinged with a horn (22), and the accommodation space forming depression between adjacent two articulated sections (11) of protruding is to make to take in accommodation space when horn assembly (2) folding.
12. heavy－duty unmanned planes according to claim 11, it is characterized in that, one end of described horn (22) is provided with the jointed shaft (221) be connected with articulated section (11), described horn (22) with jointed shaft (221) for axis rotation, described horn (22) and articulated section (11) are equipped with corresponding horn locking hole (222), insert locking screw rod (223) in described horn locking hole (222) with by horn (22) locking.
13. heavy－duty unmanned planes according to claim 11, it is characterized in that, described horn (22) is provided with motor cabinet (23) away from the one end of articulated section (11), described motor cabinet (23) is sheathed to be fixed on horn (22), and the end face of described motor cabinet (23) and bottom surface are equipped with a rotor assemblies (21).
14. heavy－duty unmanned planes according to claim 11, is characterized in that, each described articulated section (11) place is equipped with the brace panel (111) for increasing articulated section (11) intensity, and described brace panel (111) level is fixed on articulated section (11).
15. according to the heavy－duty unmanned plane in claim 1 ~ 6 described in any one, it is characterized in that, the below of described fuselage assembly (1) is provided with plural alighting gear (5), each described alighting gear (5) includes the cross bar (51) of horizontal arrangement, the two ends of described cross bar (51) are respectively provided with a leg (52), described cross bar (51) removably connects with the bottom surface of fuselage assembly (1), and each described leg (52) is provided with buffer part (521) near the one end on ground.
16., according to the heavy－duty unmanned plane in claim 1 ~ 6 described in any one, is characterized in that, the top of described fuselage assembly (1) is provided with parachute assembly (6).
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|---|---|---|---|---|
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Families Citing this family (1)
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202609080U (en) * | 2012-03-22 | 2012-12-19 | 杨育会 | Unmanned rotorcraft with paradrop device |
| US20140145026A1 (en) * | 2012-11-28 | 2014-05-29 | Hans Skjersaa | Unmanned Aerial Device |
| CN203996886U (en) * | 2014-06-30 | 2014-12-10 | 上海汇联皆景信息科技有限公司 | A kind of four axle eight oars aircraft of taking photo by plane |
| CN104386249A (en) * | 2014-11-17 | 2015-03-04 | 马鞍山市靓马航空科技有限公司 | Multi-rotor unmanned aerial vehicle for fast surveying and surveying method of multi-rotor unmanned aerial vehicle |
| CN104760694A (en) * | 2014-10-27 | 2015-07-08 | 深圳九星智能航空科技有限公司 | Dual rotor aircraft provided with foldable and dangling lower blades |
| CN204507252U (en) * | 2015-02-10 | 2015-07-29 | 上海美利达电子科技有限公司 | A kind of collapsible four axle multi-rotor aerocrafts |
| CN204568055U (en) * | 2015-02-05 | 2015-08-19 | 深圳雷柏科技股份有限公司 | A kind of Modularized unmanned aircraft |
| US20150321755A1 (en) * | 2014-04-28 | 2015-11-12 | Arch Aerial, Llc | Collapsible multi-rotor uav |
| CN205131646U (en) * | 2015-11-16 | 2016-04-06 | 湖南云顶智能科技有限公司 | Big load unmanned aerial vehicle |
-
2015
- 2015-11-16 CN CN201510782290.4A patent/CN105292457B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202609080U (en) * | 2012-03-22 | 2012-12-19 | 杨育会 | Unmanned rotorcraft with paradrop device |
| US20140145026A1 (en) * | 2012-11-28 | 2014-05-29 | Hans Skjersaa | Unmanned Aerial Device |
| US20150321755A1 (en) * | 2014-04-28 | 2015-11-12 | Arch Aerial, Llc | Collapsible multi-rotor uav |
| CN203996886U (en) * | 2014-06-30 | 2014-12-10 | 上海汇联皆景信息科技有限公司 | A kind of four axle eight oars aircraft of taking photo by plane |
| CN104760694A (en) * | 2014-10-27 | 2015-07-08 | 深圳九星智能航空科技有限公司 | Dual rotor aircraft provided with foldable and dangling lower blades |
| CN104386249A (en) * | 2014-11-17 | 2015-03-04 | 马鞍山市靓马航空科技有限公司 | Multi-rotor unmanned aerial vehicle for fast surveying and surveying method of multi-rotor unmanned aerial vehicle |
| CN204568055U (en) * | 2015-02-05 | 2015-08-19 | 深圳雷柏科技股份有限公司 | A kind of Modularized unmanned aircraft |
| CN204507252U (en) * | 2015-02-10 | 2015-07-29 | 上海美利达电子科技有限公司 | A kind of collapsible four axle multi-rotor aerocrafts |
| CN205131646U (en) * | 2015-11-16 | 2016-04-06 | 湖南云顶智能科技有限公司 | Big load unmanned aerial vehicle |
Cited By (33)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775152A (en) * | 2016-03-08 | 2016-07-20 | 谭圆圆 | Unmanned aerial vehicle with battery type counterweight device and counterweight method thereof |
| CN105842662B (en) * | 2016-03-21 | 2018-11-02 | 沈阳理工大学 | Radar and monocular vision sensor fusion for unmanned plane avoidance and suspension mechanism |
| CN105842662A (en) * | 2016-03-21 | 2016-08-10 | 沈阳理工大学 | Radar and monocular vision sensor fusion and hanging mechanism for unmanned plane obstacle avoidance |
| CN105905274A (en) * | 2016-04-18 | 2016-08-31 | 中国科学院遥感与数字地球研究所 | Fuselage structure of octorotor unmanned aerial vehicle |
| WO2018103576A1 (en) * | 2016-12-05 | 2018-06-14 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| US11498677B2 (en) | 2016-12-05 | 2022-11-15 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| EP3795474A1 (en) * | 2016-12-05 | 2021-03-24 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| US10407171B2 (en) | 2016-12-05 | 2019-09-10 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| EP3369658A4 (en) * | 2016-12-05 | 2018-12-05 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| US10266264B2 (en) | 2016-12-05 | 2019-04-23 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| US10906643B2 (en) | 2016-12-05 | 2021-02-02 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| CN108238243A (en) * | 2016-12-27 | 2018-07-03 | 中国科学院遥感与数字地球研究所 | 5kg load-carryings length six rotor wing unmanned aerial vehicles of continuation of the journey |
| CN106898187A (en) * | 2017-04-17 | 2017-06-27 | 金陵科技学院 | A kind of rotor wing unmanned aerial vehicle landing training platform that takes off |
| CN106898187B (en) * | 2017-04-17 | 2019-05-24 | 金陵科技学院 | A kind of rotor wing unmanned aerial vehicle training platform that lands that takes off |
| CN107235156A (en) * | 2017-06-26 | 2017-10-10 | 中国电建集团成都勘测设计研究院有限公司 | Can folding and unfolding and continuously adjust unmanned plane panoramic video collection camera mounting structure |
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