CN105818974A - Unmanned aerial vehicle with detachable rotary wing structure - Google Patents
Unmanned aerial vehicle with detachable rotary wing structure Download PDFInfo
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- CN105818974A CN105818974A CN201610280566.3A CN201610280566A CN105818974A CN 105818974 A CN105818974 A CN 105818974A CN 201610280566 A CN201610280566 A CN 201610280566A CN 105818974 A CN105818974 A CN 105818974A
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- 230000005611 electricity Effects 0.000 claims description 46
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 19
- 238000009434 installation Methods 0.000 claims description 11
- 238000010276 construction Methods 0.000 claims description 5
- 238000012546 transfer Methods 0.000 claims description 5
- 238000000926 separation method Methods 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000004411 aluminium Substances 0.000 claims description 3
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention discloses an unmanned aerial vehicle with a detachable rotary wing structure, and belongs to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle comprises a first rotary wing, a second rotary wing, two quick detaching assemblies, a rotary wing power assembly, a fuselage and a first detaching assembly, wherein the rotary wing power assembly is fixed on rotary wing shafts, the first rotary wing is rotatably fixed on the rotary wing power assembly by virtue of one quick detaching assembly, and the second rotary wing is rotatably fixed on the rotary wing power assembly by virtue of the other quick detaching assembly; the diameter of the first rotary wing is larger than the diameter of the second rotary wing; and the first detaching assembly is fixed on a body and is in sliding connection with a cloud terrace. The unmanned aerial vehicle with the detachable rotary wing structure solves the technical defects that a multi-rotary wing unmanned aerial vehicle is low in flight efficiency in the prior art.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, particularly to a kind of unmanned plane with dismountable rotor structure.
Background technology
UAV is called for short " unmanned plane ", is the most manned aircraft of the presetting apparatus manipulation utilizing radio robot with providing for oneself.Without driving cabin on machine, but the equipment such as automatic pilot, presetting apparatus, information collecting device are installed.On ground, naval vessels or machine tool remote control station personnel are by the equipment such as radar, it is tracked, positions, remote control, remote measurement and Digital Transmission.Can take off as conventional airplane under wireless remotecontrol or launch with booster rocket, it is possible to be taken to by machine tool and throw in flight in the air.
Unmanned plane of the prior art, including fuselage, rotor shaft, the end, one end of rotor shaft is used for fixing rotor, and other end end is fixed on fuselage, provides lift with the flight come by the rotation of rotor as unmanned plane.But, in the prior art, for many rotor wing unmanned aerial vehicles of coaxial double-oar, its two coaxial rotor often diameters, shape are identical, and it is positioned at the both sides up and down of rotor shaft, and it is positioned at rotor above rotor shaft rotating when, need the air-flow relying on its lower surface that this rotor is produced thrust upwards, then realize lift upwards overall to unmanned plane.Obviously, the air current flow area of its lower surface is the biggest, then the thrust produced this rotor upwards is the biggest, then realizes lift upwards overall to unmanned plane the biggest.And it is exactly identical due to two coaxial rotor sizes, this allows for the rotor of top and the rotor of lower section during rotating, the rotor of lower section blocks most of air current flow area of top rotor lower surface due to himself occupied spatial area, then entirety reduces unmanned plane lift upwards, causes flight efficiency low.
Summary of the invention
The present invention provides a kind of unmanned plane with dismountable rotor structure, solves or part solves the technological deficiency that in prior art, many rotor wing unmanned aerial vehicles flight efficiency is low.
The invention provides a kind of unmanned plane with dismountable rotor structure for solving above-mentioned technical problem, wherein, unmanned plane includes rotor shaft, flight control system and The Cloud Terrace, described in there is the unmanned plane of dismountable rotor structure include: the first rotor；Second rotor；Two Quick-dismantle components；Rotor power assembly, described rotor power assembly is fixed in described rotor shaft, and is connected with described flight control system, thinks described first rotor and the powered rotation of described second rotor；And described first rotor is rotationally fixed on described rotor power assembly by a Quick-dismantle component so that described first rotor is rotatable relative to described rotor shaft；Described second rotor is rotationally fixed on described rotor power assembly by another Quick-dismantle component so that described second rotor is rotatable relative to described rotor shaft；And the diameter of described first rotor is more than the diameter of described second rotor, fuselage, described fuselage includes: casing；Body, the inside of described body is hollow-core construction, and is provided with at least one installing port on described body；Second dismounting assembly, detachable for described casing is connected on described body, and covers described installing port by described casing by described second dismounting assembly；Wherein, parts to be installed in described body are placed into by described installing port relative to described body or are removed；First dismounting assembly, described first dismounting assembly is fixed on described body, and is slidably connected with described The Cloud Terrace, so that described The Cloud Terrace can slide relative to described first dismounting assembly or described body；Wherein, by described first dismounting assembly, described The Cloud Terrace is connected on described body so that described The Cloud Terrace is by detachable between described first dismounting assembly and described body.
Optionally, described rotor power assembly includes: refrigerating seat, and described refrigerating seat includes the first stationary plane and the second stationary plane, described first stationary plane and described second stationary plane transverse axis centered by described rotor shaft, is symmetrically dispersed in the both sides of described rotor shaft；First motor, described first motor is fixed on described first stationary plane, makes described first rotor be fixed on described first motor by what a Quick-dismantle component rotated；Second motor, described second motor is fixed on described second stationary plane, makes described second rotor be fixed on described second motor by what another Quick-dismantle component rotated；First electricity is adjusted, and described first electricity is adjusted and is fixed on the inside of described refrigerating seat, and is connected with the flight control system described first motor and described unmanned plane within respectively, rotates moving the first rotor described in described first driven by motor by the described first electric transfer drive；Second electricity is adjusted, and described second electricity is adjusted and is fixed on the inside of described refrigerating seat, and is connected with the flight control system described first motor and described unmanned plane within respectively, rotates moving the second rotor described in described second driven by motor by the described second electric transfer drive.
Optionally, described refrigerating seat is provided with at least one vent, communicates with free surrounding space with the inner space by described refrigerating seat.
Optionally, described first electricity is stealthily substituted and is included: the first electric capacity, first circuit board and the first heat sink；Wherein, described first circuit board is connected with described first electric capacity, described first motor and described flight control system respectively, and described first heat sink is attached on described first circuit board；With, described second electricity is stealthily substituted and is included: the second electric capacity, second circuit board and the second heat sink；Wherein, described second circuit board is connected with described second electric capacity, described second motor and described flight control system respectively, and described second heat sink is attached on described second circuit board.
Optionally, described first heat sink and/or described second heat sink are aluminium sheets.
Optionally, described first circuit board is between described first electric capacity and described first heat sink；And/or, described second circuit board is between described second electric capacity and described second heat sink.
Optionally, described Quick-dismantle component includes: the first screw；Second screw；First screw buckle, the inwall of described first screw buckle is provided with the first female thread, and the bottom of described first screw buckle offers the first screw so that described first screw buckle is fixed on described first motor or described second motor by described first screw through described first screw；First dismounting nut, the outer wall of described first dismounting nut is provided with the first external screw thread, and described first dismounting nut top offer the second screw, make described second screw sequentially pass through described first rotor, the second screw by described first dismounting nut be fixed on described first rotor, or make described second screw sequentially pass through described second rotor, the second screw by described first dismounting nut be fixed on described second rotor；Wherein, described first female thread is suitable with described first external screw thread, and by the occlusion between described first female thread and described first external screw thread or separation, corresponding realizes the installation between described first rotor and described first motor or between described second rotor and described second motor or dismounting.
Optionally, the quantity of described first screw is 2；The quantity of described second screw is 2；The quantity of described first screw is 2；The quantity of described second screw is 2；Wherein, each corresponding described first screw of described first screw so that described first screw buckle is fixed on described first motor or described second motor by each described first screw through corresponding described first screw；Each corresponding described second screw of described second screw so that described first screw buckle is fixed on described first motor or the second motor by each described second screw through corresponding described second screw.
Optionally, in the vertical direction, described first rotor is positioned at the top of described second rotor.
Optionally, described first dismounting assembly includes: fixed plate, described fixed plate is fixed on described body, and is slidably connected with described The Cloud Terrace, so that described The Cloud Terrace slides relative to described fixed plate；Positioning element, described positioning element is fixed in described fixed plate, to position described The Cloud Terrace relative to the position of described fixed plate, and then realizes described The Cloud Terrace relative to the installation of described body or dismounting.
The unmanned plane with dismountable rotor structure that the present invention provides, first rotor and corresponding being fixed on rotor power assembly by Quick-dismantle component of the second rotor, and rotor power assembly is fixed in rotor shaft, the diameter of the first rotor is more than the diameter of the second rotor, achieve the overall size overall size more than the second rotor of the first rotor, this allows for the first rotor and during the second rotor rotates at the same time, second rotor greatly reduces the spatial area existed due to himself, obstruction to the air current flow area of first its lower surface of rotor, ensure that the air-flow of first its lower surface of rotor is to thrust size upwards produced by this rotor, then it also avoid the overall upwards lift of unmanned plane to reduce and affect the technological deficiency of its flight efficiency.Have the advantages that flight efficiency is high.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, the accompanying drawing used required in embodiment will be briefly described below, apparently, accompanying drawing in describing below is only some embodiments of the present invention, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to obtain other accompanying drawing according to these accompanying drawings.
The unmanned plane overall structure schematic diagram that Fig. 1 provides for the embodiment of the present invention；
The side view of the unmanned plane that Fig. 2 provides for Fig. 1；
First dismounting assembly and the annexation overall structure schematic diagram of The Cloud Terrace in the unmanned plane that Fig. 3 provides for Fig. 1；
First dismounting assembly and the annexation overall structure side view of The Cloud Terrace in the unmanned plane that Fig. 4 provides for Fig. 1；
Fig. 5 is the first dismounting assembly overall structure schematic diagram in Fig. 4；
Fig. 6 is the first dismounting assembly overall structure front view in Fig. 5；
In the unmanned plane that Fig. 7 provides for the embodiment of the present invention, the first location plunger is in the sectional view under contraction state；
The overall structure schematic diagram that in the unmanned plane that Fig. 8 provides for the embodiment of the present invention, the first location plunger is under contraction state；
In the unmanned plane that Fig. 9 provides for the embodiment of the present invention, the first location plunger is in the sectional view under raised position；
The overall structure schematic diagram that in the unmanned plane that Figure 10 provides for the embodiment of the present invention, the first location plunger is under raised position；
The overall structure schematic diagram of fuselage in the unmanned plane that Figure 11 provides for the embodiment of the present invention；
Figure 12 is the close-up schematic view of the second dismounting assembly in Figure 11；
The overall structure schematic diagram of signal framing assembly in the unmanned plane that Figure 13 provides for the embodiment of the present invention；
The sectional view of signal framing assembly in the unmanned plane that Figure 14 provides for the embodiment of the present invention；
The annexation schematic diagram of the first motor, refrigerating seat and rotor shaft three that Figure 15 provides for the embodiment of the present invention；
The annexation sectional view of the first motor, refrigerating seat and rotor shaft three that Figure 16 provides for the embodiment of the present invention；
The overall structure schematic diagram that Figure 17 adjusts for the first electricity that the embodiment of the present invention provides；
The side view that Figure 18 adjusts for the first electricity that the embodiment of the present invention provides；
The first motor that Figure 19 provides for the embodiment of the present invention, the second motor, refrigerating seat, the annexation schematic diagram of rotor shaft；
The structural front view of the Quick-dismantle component that Figure 20 provides for the embodiment of the present invention；
The overall structure schematic diagram of the Quick-dismantle component that Figure 21 provides for the embodiment of the present invention；
The overall structure schematic diagram of the another unmanned plane that Figure 22 provides for the embodiment of the present invention；
Figure 23 is the annexation schematic diagram of the first rotor and the second rotor in Figure 22.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art are obtained, broadly fall into the scope of protection of the invention；Wherein involved in this enforcement "and/or" key word, represent and or two kinds of situations, in other words, A and/or B mentioned by the embodiment of the present invention, illustrates A and B, two kinds of situations of A or B, describes three kinds of states existing for A Yu B, such as A and/or B, represent: only include A and do not include B；Only include B and do not include A；Including A and B.
Meanwhile, in the embodiment of the present invention, when assembly is referred to as " being fixed on " another assembly, it can be directly on another assembly or can also there is assembly placed in the middle.When an assembly is considered as " connection " another assembly, and it can be directly to another assembly or may be simultaneously present assembly placed in the middle.When an assembly is considered as " being arranged at " another assembly, and it can be to be set directly on another assembly or may be simultaneously present assembly placed in the middle.Term " vertical ", " level ", "left", "right" and similar statement used in the embodiment of the present invention are merely for purposes of illustration, and are not intended to limit the present invention.
The unmanned plane with dismountable rotor structure that the present invention provides, first rotor and corresponding being fixed on rotor power assembly by Quick-dismantle component of the second rotor, and rotor power assembly is fixed in rotor shaft, the diameter of the first rotor is more than the diameter of the second rotor, achieve the overall size overall size more than the second rotor of the first rotor, this allows for the first rotor and during the second rotor rotates at the same time, second rotor greatly reduces the spatial area existed due to himself, obstruction to the air current flow area of first its lower surface of rotor, ensure that the air-flow of first its lower surface of rotor is to thrust size upwards produced by this rotor, then it also avoid the overall upwards lift of unmanned plane to reduce and affect the technological deficiency of its flight efficiency.Have the advantages that flight efficiency is high.Elaborate to offer of the present invention be had the unmanned plane of dismountable rotor structure, to support the technical problem to be solved, below, in the embodiment that the present invention provides, first the overall structure of unmanned plane is elaborated, then during narration unmanned plane, the unmanned plane with dismountable rotor structure that the present invention provides is drawn the most targetedly, to reach purpose complete, clear, that understand.
Refer to Fig. 1-2,11,14, embodiments provide a kind of unmanned plane, including fuselage 1, rotor shaft 2, The Cloud Terrace 3, the first dismounting assembly 4, signal framing assembly 5 and rotor power assembly 6.
Wherein, described rotor shaft 2 is rotationally fixed on described fuselage 1 by its one end, collapsible relative to fuselage to realize rotor shaft 2, then completes rotor shaft 2 and the expansion action of fuselage or contractive action.In embodiments of the present invention, the quantity of rotor shaft 2 can be 4, and four corner portions being distributed in fuselage 1 of 4 described rotor shaft 2 symmetries.The inside of described fuselage 1 is additionally provided with the flight control system for controlling unmanned plane during flying.On the other end of rotor shaft 2, it is fixed with described rotor power assembly 6, and is connected with the flight control system set by fuselage 1 inside, think and on the powered rotation of rotor, and described rotor power assembly 6, at least include an electricity tune described above.
Simultaneously, described first dismounting assembly 4 is fixed on described fuselage 1, and by described first dismounting assembly 4, detachable for described The Cloud Terrace 3 is connected on described fuselage 1, make described The Cloud Terrace 3 by described first dismounting assembly 4 can with described fuselage 1 quickly, dismantle flexibly, to constitute the double paddle structures being applied to unmanned plane of the present invention.Certainly, fixing connected mode between first dismounting assembly 4 and described fuselage 1 can be diversified, as being bolt connection, can be screw connection, can be welding, can also be one-body molded, do not limit in this embodiment of the present invention, as long as being capable of the first dismounting assembly 4 to be fixed on described fuselage 1.
Further, described signal framing assembly 5 is fixed on described fuselage 1, and is provided with a localizer 53 in described signal framing assembly 5.Certainly, localizer 53 is mainly used in carrying out between unmanned plane and earth station the transmission of positional information in embodiments of the present invention, to be monitored position and the flight information of unmanned plane in real time by localizer 53, type for localizer 53, the embodiment of the present invention is not limited to, and can be navigational route type receiver, geodetic type receiver or time service type receiver etc..It should be understood that, in the embodiment of the present invention, described localizer 53 is arranged on described fuselage 1 by described signal framing assembly 6, thus makes the external air flow of localizer 53 with described fuselage 1 to be isolated by signal framing assembly 6；Effectively avoid localizer 53 the most exposed when external fuselage, external air flow during unmanned plane during flying, extraneous dampness or extraneous shelter because of with localizer 53 Long Term Contact or friction and the localizer 53 that causes makes moist or damages, have the advantages that security performance is high.
Below, the building block of each several part of unmanned plane is elaborated.
For above-mentioned first dismounting assembly 4, referring to Fig. 3-11, wherein, described first dismounting assembly 4 at least includes: fixed plate 41 and positioning element 42.
Wherein, described fixed plate 41 is fixed on described fuselage 1, and is slidably connected with described The Cloud Terrace 3, so that described The Cloud Terrace 3 slides relative to described fixed plate 41, and owing to fixed plate 41 is fixed relative to fuselage 1, and then realizes The Cloud Terrace 3 and slides relative to fuselage 1.Certainly, fixing connected mode between fixed plate 41 and described fuselage 1 can be diversified, as being bolt connection, can be screw connection, can be welding, can also be one-body molded, do not limit in this embodiment of the present invention, as long as being capable of fixed plate 41 to be fixed on described fuselage 1.Described positioning element 42 is fixed in described fixed plate 41, to position described The Cloud Terrace 3 relative to the position of described fixed plate 41, and then realizes described The Cloud Terrace 3 relative to the installation of described fuselage or dismounting.
Here, positioning element 42 is equivalent to screens parts, when The Cloud Terrace 3 is installed on fuselage 1 by needs, now slide into a certain position relative to fixed plate 41 between The Cloud Terrace 3 and fixed plate 41, then the The Cloud Terrace 3 of this position is positioned, to prevent The Cloud Terrace 3 from sliding relative to fixed plate 41 by positioning element 42.And when The Cloud Terrace 3 pulled down by needs, the most only need manual toggle positioning element 42, it is allowed to The Cloud Terrace 3 skids off relative to fixed plate 41, can realize The Cloud Terrace 3 quick, dismantle flexibly.During this, the installation and removal of The Cloud Terrace are without by any extraneous utensil such as spanner etc., easy to operate, have quickly, feature easily.
In embodiments of the present invention, as preferably, please continue to refer to Fig. 5-6, described fixed plate 42 can be the U-shaped shape in cross section, and the described fixed plate 42 under this shape at least may include that the first side plate 411；Second side plate 412 and transverse slat 413.Wherein, described first side plate 411 and described second side plate 412 are parallel；And described first side plate 411 and described second side plate 412 perpendicular with described transverse slat 413, and described transverse slat 413 is slidably connected with described first side plate 411 and described second side plate 412 respectively, described The Cloud Terrace 3 is fixing with described transverse slat 413 to be connected, and then by described transverse slat 413, described The Cloud Terrace 3 is slided relative to described first side plate 411 and described second side plate 412.Meanwhile, described positioning element 41 is individually fixed on described first side plate 411 and described second side plate 412, to position described transverse slat 413 relative to the position of described first side plate 411 and described second side plate 412.Certainly, described first side plate 411, fixing connected mode between described second side plate 412 and described fuselage 1 can be diversified, as being bolt connection, can be screw connection, can be welding, can also be one-body molded, do not limit in this embodiment of the present invention, as long as being capable of described first side plate 411, described second side plate 412 is fixed on described fuselage 1.
Same principle; fixing connected mode between described The Cloud Terrace 3 and described transverse slat 413 can also be diversified; as being bolt connection, can be screw connection, can be welding; can also be one-body molded; do not limit in this embodiment of the present invention; as long as being capable of described The Cloud Terrace 3 to be relatively fixed, all within protection scope of the present invention with described transverse slat 413.
Further, for ease of being fixed with the transverse slat 413 of The Cloud Terrace 3, it is possible to and first side plate the 411, second side plate 412 is flexibly, quickly slide, in order to The Cloud Terrace 3 flexibly, is quickly installed or dismounting.A kind of embodiment as the embodiment of the present invention, it is respectively arranged with a chute on described first side plate 411 and described second side plate 412, so that described transverse slat 413 is arranged in described chute so that described transverse slat 413 is slided relative to described first side plate 411 and described second side plate 412 by described chute.
Simultaneously, one end of described positioning element 42 corresponding through described first side plate 411, described second side plate 412, and in described chute internal projection or contraction, so that one end of described positioning element 42 relative to described chute when described chute internal projection, one end of described positioning element 42 stops that described transverse slat 413 slides in described chute, one end of described positioning element 42 relative to described chute when described chute contract, one end of described positioning element 42 is separated, so that described transverse slat 413 slides in described chute with described transverse slat 413.
Needing exist for explanation, in embodiments of the present invention, described " protruding " is it can be understood as be that parts slip in some parts, and " contraction " can be understood as parts and skid off some parts.Such as, one end of described positioning element 42 described above relative to described chute when described chute internal projection, i.e. refer to that one end of described positioning element 42 is slipped in described chute, one end of positioning element 42 described above when described chute contract, i.e. refers to that one end of described positioning element 42 skids off described chute relative to described chute.The Cloud Terrace 3 is realized relative to the dismounting of fuselage 1 or installation by positioning element 42 with this.For described positioning element 42, in embodiments of the present invention, as a kind of implementation of the present embodiment, described positioning element 42 can at least include: the first location plunger and described second location plunger.And described first location plunger include the first positioning end；Described second location plunger includes the second positioning end.
Wherein, described first positioning end corresponding through described first side plate, and the chute internal projection in described first side plate 411 or contraction, so that described first positioning end is when relative to chute internal projection in described first side plate 411, described first positioning end stops that described transverse slat 413 slides in chute, described first positioning end is when relative to chute contract in described first side plate 411, described first positioning end is separated, so that described transverse slat 413 slides in chute with described transverse slat 413.Wherein, described second positioning end corresponding through described second side plate 412, and the chute internal projection in described second side plate 412 or contraction, so that described second positioning end is when relative to chute internal projection in described second side plate 412, described second positioning end stops that described transverse slat 413 slides in chute, described second positioning end is when relative to chute contract in described second side plate 412, described second positioning end is separated with described transverse slat, so that described transverse slat 413 slides in chute.
Here, can be as shown in Fig. 5 or Fig. 6, can be understood as the first side plate 411 and both sides being distributed in described transverse slat 413 of the second side plate 412 symmetry, insert described first side plate 411 while thus making the both sides correspondence of described transverse slat 413 and in chute that described second side plate 412 is offered, realize, with this, the transverse slat 413 being fixed with The Cloud Terrace 3 and slide relative to the first side plate 411 and the second side plate 412.Meanwhile, in order to preferably the transverse slat 413 in sliding process be positioned.The embodiment of the present invention is corresponding by the first location plunger and the second location plunger, the both sides at transverse slat 413 of symmetrical setting, namely the first location plunger and the first side plate 411, and the second location plunger and the second side plate 412 are corresponding.It should be noted that in embodiments of the present invention, the first side plate 411 and the structure of the second side plate 412 can identical can also be different, the first location plunger and the second location plunger can identical can also be different.And in embodiments of the present invention, for convenience of description, the first selected side plate 411 is identical with the second side plate 412 structure, the structure of the first location plunger and the second location plunger is identical.
Certainly, it will be appreciated by those skilled in the art that, first side plate 411 and the second side plate 412, first position plunger and the second location plunger can also be mutually different various structures, if the first side plate 411 can be square structure, second side plate 412 can be rectangle structure, or the first side plate 411 can be trapezium structure, the second side plate 412 can be square or the polygonized structure such as rectangle or rhombus.In other words; as long as be capable of the first side plate 411 and the second side plate 412 be relatively fixed with fuselage 1; and the first side plate 411 and the second side plate 412 structure that transverse slat 413 can relative with the first side plate 411 and the second side plate 412 slide, all within protection scope of the present invention.Same, first location plunger and the second location plunger can also be multiple different structures, as long as disclosure satisfy that the first location plunger can be corresponding through the first side plate 411, second location plunger can be corresponding through the second side plate 412, and carry out projection or flexible in the chute of each its correspondence of leisure, to carry out transverse slat 413 spacing to the greatest extent may be used.The planform being placed in the first location plunger and the second location plunger is the most identical, and the embodiment of the present invention does not do restriction further.
Please continue to refer to Fig. 7-10, as stated above, a kind of embodiment as the embodiment of the present invention, assuming that the first selected in embodiments of the present invention location plunger and the second location plunger are completely identical in structure, as a example by the first location plunger 421 shown in Fig. 7-10, the internal structure of location plunger is described in further detail.
Such as Fig. 7-10, described first location plunger 421 includes: first bolt the 4211, first positioning thread insert 4212, first positions spring 4213.Wherein, described first bolt 4211 is provided with described first positioning end 4211a；Described first positioning thread insert 4212 is set on described first bolt 4211, and is provided with one first compression stroke 4214 between described first positioning thread insert 4212 and described first bolt 4211.Can be understood as the internal diameter external diameter more than described first bolt 4211 of the most described first positioning thread insert 4212, when thus making the first positioning thread insert 4212 be set on described first bolt 4211, therebetween there is neutral region, this neutral region is above-mentioned first compression stroke 4214.Described first location spring is arranged in described first compression stroke 4214；Wherein, described first positioning end 4211a sequentially passes through described first location spring 4213, described first compression stroke 4214 and described first side plate 411, with the chute internal projection in described first side plate 411 or contraction.
It is noted that be schematic diagram during first positioning end 4211a chute contract state in described first side plate 411 shown in Fig. 7-8.Shown in Fig. 9-10 is schematic diagram during first positioning end 4211a chute internal projection state in described first side plate 411.And in order to preferably position spring 4213 by first the most now in the first compression stroke 4214, on the described first positioning end 4211a of the first bolt 4211 described in the embodiment of the present invention, it is provided with one first card convex 4215, so that described first location spring 4213 is fully defined in described first compression stroke 4214, and make described first positioning end 4211a when relative to chute contract in described first side plate 411, compress described first location spring 4213 by described first card convex 4215.
Specifically, the embodiment of the present invention is during actual job, first location spring 4213 is in the first compression stroke 4214, whole process is in compression or its pre-compressed state, thus make in its natural state, first location spring 4213 is entered by the first side plate 411 in the chute of described first side plate 411 by the elasticity tension described first positioning end 4211a of promotion of self the first compression stroke 4214 in, and then positions the transverse slat 413 in being in chute.And when needs transverse slat 413 skids off from chute, namely when needing to dismantle The Cloud Terrace 3 from fuselage 1, now have only to manual toggle the first bolt 4211, the first positioning end 4211a is made to compress the first location spring 4213 by the first card convex 4215, then make the first positioning end 4211a skid off in the chute of the first side plate 411, and then realize skidding off relative to the first side plate 411 of transverse slat 413.And when without External Force Acting after the first bolt 4211, under the elasticity tension effect of the first location spring 4213, continuing to press on the first positioning end 4211a carries out return, namely the duty of the first location plunger 421 shown in Fig. 9 or Figure 10.Effectively achieve the installation and removal of The Cloud Terrace without by any extraneous utensil such as spanner etc., easy to operate, have quickly, feature easily.
In embodiments of the present invention, described second location plunger includes: the second bolt, described second bolt is provided with described second positioning end；Second positioning thread insert, described second positioning thread insert is set on described second bolt, and is provided with one second compression stroke between described second positioning thread insert and described second bolt；Second location spring, described second location spring is arranged in described second compression stroke；Wherein, described second positioning end sequentially passes through described second location spring, described second compression stroke and described second side plate, with the chute internal projection in described second side plate or contraction.On described second positioning end of described second bolt, it is provided with one second card convex, so that described second location spring is limited in described second compression stroke, and make described second positioning end when relative to chute contract in described second side plate, by the described second location spring of described second card convex compression.
As mentioned above, the second location plunger in the embodiment of the present invention is identical with the structure of the first location plunger 421 shown in Fig. 7-10, the most no longer the internal structure of the second location plunger is repeated, for the non-detailed portion of internal structure of the second location plunger, see the detailed portion of the first location plunger 421 in the embodiment of the present invention.
Secondly, for the fuselage 1 that the embodiment of the present invention provides, see Fig. 1-2 and 11-12, the fuselage 1 that the embodiment of the present invention provides has removable feature.Thus make again when the internally installed device of fuselage 1, convenient, fast.Specifically, described fuselage 1 at least may include that body 12, casing 11 and the second dismounting assembly 13.Wherein, the inside of described body 12 is hollow-core construction；At least one installing port 121 it is provided with on described body 12；Detachable for described casing 11 is connected on described body 12 by described second dismounting assembly 13.Meanwhile, described first dismounting assembly 4 is fixed on the bottom of described body, and described signal framing assembly 5 is fixed on described body 12；So that parts to be installed in described body 12 are placed into by described installing port relative to described body 12 or are removed.As preferably, the quantity of the described second dismounting assembly 13 in the embodiment of the present invention is at least 2, and 2 described two are dismantled assemblies and are symmetrically dispersed in the both sides of described casing 11, in order to the connection between casing 11 and body 12 is more firm.
Further, see Figure 12, described second dismounting assembly 13 includes: socket 131 and the 3rd location plunger 132.Wherein, described socket 131 is fixed on described body 12；Described 3rd location plunger 132 is fixed in described casing 11, and described 3rd location plunger 132 includes the 3rd positioning end.Thus make in the described socket of insertion 131 that described 3rd positioning end is corresponding, with by described casing 11 and described body 12 clamping.
Here it should be noted that in described second dismounting assembly 13 socket 131 be for the parts inserted being carried out the effect of screens, being similar to keeper principle.In described second dismounting assembly 13, the 3rd location plunger 132 is for insertion in socket 131, and then casing 11 and body 12 play the effect that bridge connects.Certainly, in the embodiment of the present invention, the structure of the 3rd location plunger 132 can be diversified.
Such as, can as shown in figure 12, described 3rd location plunger 132 may include that locating dowel 1321 and the 3rd caging bolt 1322, described locating dowel 1321 are fixed in described casing 11, and described 3rd caging bolt 1322 is fixed in described locating dowel 1321；Described 3rd caging bolt 1322 is provided with described 3rd positioning end.And then by casing 11 is removably connected by the 3rd positioning end insertion socket 131 with body 12.As the quantity of above-mentioned second dismounting assembly 13 is at least 2, and 2 described two are dismantled assemblies and are symmetrically dispersed in the both sides of described casing 11.In specific implementation process, can first mate the 3rd caging bolt 1322 and the socket 131 inserting side, then at the 3rd caging bolt 1322 and the socket 131 of corresponding coupling opposite side.Certainly, in this kind of embodiment, casing 11 can also be to be made up of flexible material, casing 11 is made to present flexible characteristic, so pinch the both sides of casing 11 by hands casing 11 to be made to prolong the center portion thereof position be curved, the corresponding body 12 of placing of casing 11 after bending is fixed with on the position of two sockets 131, loosen the casing 11 being pinched, so casing 11 automatically restores to original state under the elasticity tension effect of self, casing 11 in recovery process is owing to being precisely placed on two the 3rd caging bolts 1322 and the position of two socket 131 correspondences, thus make the most corresponding each being inserted in two sockets 131 by two the 3rd caging bolts 1322 of the casing after recovering 11, complete to be connected with the quick of body 12.There is feature easily and efficiently.
For another example, the structure of the first location plunger during the 3rd location plunger 132 in the embodiment of the present invention can also is that such as above-mentioned first dismounting assembly 4.That is: the described 3rd positions plunger 132 may include that locating dowel 1321, described locating dowel 1321 are fixed in described casing 11；3rd bolt, described 3rd bolt is fixed in described locating dowel, and described 3rd bolt is provided with described 3rd positioning end；3rd positioning thread insert, described 3rd positioning thread insert is set on described 3rd bolt, and is provided with one the 3rd compression stroke between described 3rd positioning thread insert and described 3rd bolt；3rd location spring, described 3rd location spring is arranged in described 3rd compression stroke；Wherein, described 3rd positioning end sequentially passes through described 3rd location spring, described 3rd compression stroke inserts in described socket.Further, on described 3rd positioning end of described 3rd bolt, it is provided with one the 3rd card convex, so that described 3rd location spring is limited in described 3rd compression stroke, and when described 3rd positioning end and described socket are separated, by the described 3rd location spring of described 3rd card convex compression.
In embodiments of the present invention, as the presently preferred embodiments, described 3rd caging bolt and/or described 3rd bolt are mutually perpendicular to described locating dowel.Fixing connection between described locating dowel and described casing is welding；And/or, described locating dowel and described casing are one-body molded.Fixing connection between described locating dowel with described 3rd caging bolt and/or described 3rd bolt is welding；And/or, described locating dowel and described 3rd caging bolt are one-body molded.
Again, for described signal framing assembly 5, referring to Figure 13-14, described signal framing assembly 5 also includes: location bar 51 and spiral shell dish 52.Wherein, described location bar 51 includes fixing end 511 and a support end 512, and described location bar 51 is fixed in described casing 11 by described fixing end 511.Described spiral shell dish 52 is fixed on described location bar 51 by described support end 512, and the inside of described spiral shell dish 52 is hollow-core construction so that described localizer 53 is fixed in described spiral shell dish 52.Described localizer 53 is arranged on described fuselage 1 by location bar 51 and spiral shell dish 52, thus makes the external air flow of localizer 53 with described fuselage 1 to be isolated by spiral shell dish 52；Effectively avoid localizer 53 the most exposed when external fuselage, external air flow during unmanned plane during flying, extraneous dampness or extraneous shelter because of with localizer 53 Long Term Contact or friction and the localizer 53 that causes makes moist or damages, have the advantages that security performance is high.
As preferably, described location bar 51 and described casing 11 are one-body molded；And/or, described location bar 5151 and described spiral shell dish 52 are one-body molded.Certainly, for spiral shell dish 52, it is the equal of a protective cover of localizer 53, and for protecting localizer 53, in embodiments of the present invention, described spiral shell dish 52 can at least include: the first blind nut 521, and described first blind nut 521 is provided with female thread；Second blind nut 522, described second blind nut 522 is provided with external screw thread, described first blind nut 521 and the threaded composition of described second blind nut 522 described spiral shell dish 52；Wherein, described first blind nut 521 and described second blind nut 522 can be with rounded shapes, it is also possible to be square shape, or diamond shaped, and the embodiment of the present invention does not limits.It is noted that the angle constituted between described location bar 51 and described casing 11 is an acute angle.That is, the plane at center vertical pivot and casing 11 place of location bar 51 is not mutually perpendicular to, and the inclined plane of location bar 51 with towards tail orientation, the most further reduce position bar 51 during unmanned plane during flying with the contact resistance of external air flow.
Again, for rotor power assembly 6, referring to Figure 15-16, described rotor power assembly 6 at least includes: the first motor 61, refrigerating seat 63 and the first electricity tune 64 (the first electricity tune 64 and the following second electricity are adjusted and all be can be understood as heat radiating type electricity tune).Being fixed on described first motor 61 of first rotor rotational of power is provided owing to rotating to be unmanned plane during flying；Described refrigerating seat 63 is fixed in described rotor shaft 2, and described first motor 61 is fixed on described refrigerating seat 63.In embodiments of the present invention, the inside of refrigerating seat 63 is hollow-core construction, and described first electricity adjusts 64 inside being fixed on described refrigerating seat 63, and be connected with the described flight control system within described first motor 61 and fuselage 1 respectively, to control described first electricity tune 64 by described flight control system, it is achieved drive described first motor 61 to drive described first rotor to rotate.
It should be strongly noted that described refrigerating seat 63 is provided with at least one vent 631, communicate with free surrounding space with the inner space by described refrigerating seat 63.Thus make when the first electricity is adjusted the inside that 64 are fixed on refrigerating seat 63, real-time and refrigerating seat 63 periphery cold air forms convection current, 64 cool down in real time so that the first electricity is adjusted, effectively avoid cause because the first electricity adjusts 64 overheated mistakes to scald the first electricity adjust 64 cannot be properly functioning technological deficiency.Simultaneously, first electricity is adjusted the 64 peripheral positions being directly fixed on fuselage 1, and owing to the first rotor is arranged on refrigerating seat 63, therefore the connection line between the first electricity tune 64 and the first rotor is the shortest, significantly reduce the first electricity to adjust between the first rotor because having that circuit is long and the power attenuation that causes, possess efficient, energy-conservation feature.
Certainly, in embodiments of the present invention, referring to Figure 19, rotor power assembly 6 can also include that the second motor 62 and the second electricity are adjusted, and described second electricity is adjusted and is connected with described second motor 62 and described flight control system respectively.Now, can be understood as described refrigerating seat 63 and include the first stationary plane and the second stationary plane, described first motor 61 is fixed on described first stationary plane, described second motor 62 is fixed on described second stationary plane, to be moved described second motor 63 driven the second rotor to rotate by described second electricity transfer drive.Same with the first electricity phase modulation, described second electricity adjusts the inside also being secured to described refrigerating seat 63.So by shown in Figure 19 2 motors are set and 2 electricity are adjusted, and then realize the unmanned plane structure of coaxial double-oar.
In embodiments of the present invention, it can be identical structure that first electricity mediation the second electricity is adjusted, and as a example by the first electricity adjusts 64, refers to Figure 17-18, and it at least may include that the first electric capacity 641, first circuit board 642 and the first heat sink 643.Wherein, described first circuit board 642 is connected with described first electric capacity 641, described first motor 61 and described flight control system respectively, and described first heat sink 643 is attached on described first circuit board 642.As preferably, described first heat sink 643 can be aluminium sheet.So on the one hand, the first electricity is adjusted 64 to cool down by convection by the vent 631 offered at refrigerating seat, adjusts 64 to dispel the heat the first electricity further simultaneously also by the first heat sink 643.To reach to ensure the technique effect that the first electricity adjusts 64 safe operations.
For the second electricity is adjusted, identical with the first electricity tune 64, it is also possible to include: the second electric capacity；Second circuit board；And second heat sink；Wherein, described second circuit board is connected with described second electric capacity, described second motor and described flight control system respectively, and described second heat sink is attached on described second circuit board.Owing in embodiments of the present invention, the internal structure that the internal structure that the second electricity is adjusted is adjusted with the first electricity is identical, and here is omitted, the non-detailed portion of internal structure that the second electricity is adjusted, refer to the first electricity and adjust.
As preferably, described first circuit board is between described first electric capacity and described first heat sink；And/or, described second circuit board is between described second electric capacity and described second heat sink.
Further, continuing with seeing Figure 20-23, for the annexation between the first motor 61 and the first rotor 8, annexation between the second motor 62 and the second rotor 9, the embodiment of the present invention additionally provides a kind of Quick-dismantle component, connects for the Quick Release between the first motor 61 and the first rotor, between the second motor 62 and the second rotor 9.Realize when carrying out installation or the dismantlement work of first rotor the 8, second rotor 9, only need by rotating described first rotor 8 or described second rotor 9, the fastening between the first rotor 8 and the first motor 61, between the second motor 62 and the second rotor 9 or separation can be realized, namely without can complete installation or the dismantlement work of the first rotor 8 by external operation instrument (such as handle), there is quick, portable and that working performance is high feature.
Specifically, in the present embodiment, the first motor 61 includes first surface 611 and second surface 612.In an embodiment, first surface 611 can be understood as the upper surface of the first motor 61, second surface 612 can be understood as the lower surface of the first motor 61, and described first motor 61 is fixed on the first stationary plane of refrigerating seat 63 by described first surface 611, described second motor 62 is fixed on the second stationary plane of refrigerating seat 63 by described second surface 612.
It is significant to note that, in prior art for many rotor wing unmanned aerial vehicles of coaxial double-oar, its two coaxial rotor often diameters, shape are identical, and it is positioned at the both sides up and down of rotor shaft, and it is positioned at the rotor above rotor shaft rotating when, need the air-flow relying on its lower surface that this rotor is produced thrust upwards, then realize lift upwards overall to unmanned plane.Obviously, the air current flow area of its lower surface is the biggest, then the thrust produced this rotor upwards is the biggest, then realizes lift upwards overall to unmanned plane the biggest.And it is exactly identical due to two coaxial rotor sizes, this allows for the rotor of top and the rotor of lower section during rotating, the rotor of lower section blocks most of air current flow area of top rotor lower surface due to himself occupied spatial area, then entirety reduces unmanned plane lift upwards, causes flight efficiency low.
And in the present embodiment, by transverse axis centered by described rotor shaft, first rotor 8 and the second rotor 9 are symmetrically dispersed in the both sides of rotor shaft 2, and the diameter of the first rotor 8 is more than the diameter of the second rotor 9, realize the overall size overall size more than the second rotor 9 of the first rotor 8, this allows for the first rotor 8 and during the second rotor 9 rotates at the same time, second rotor 9 greatly reduces the spatial area existed due to himself, obstruction to the air current flow area of first its lower surface of rotor 8, ensure that the air-flow of first its lower surface of rotor 8 is to thrust size upwards produced by this rotor, then it also avoid the overall upwards lift of unmanned plane to reduce and affect the technological deficiency of its flight efficiency.Have the advantages that flight efficiency is high.
For Quick-dismantle component 7, two Quick-dismantle components 7 can be selected, described first rotor 8 is rotationally fixed on described first motor by a Quick-dismantle component correspondence, and described second rotor 9 is rotationally fixed on described second motor by another Quick-dismantle component correspondence.Owing to the first rotor 8 is by Quick-dismantle component 7 and the annexation of the first motor, action principle, identical by Quick-dismantle component 7 and the annexation of the second motor, action principle with the second rotor 9, therefore, following the present embodiment is only by being described in detail as a example by being connected by a Quick-dismantle component and the first motor 61 by the first rotor 8, second rotor 9 is repeated no more by the annexation action principle between a Quick-dismantle component and the second motor 61, can describe refering to the connection between following first rotor 8 and the first motor 61 in the lump.
Specifically, during actual job, Quick-dismantle component 7 is by threaded to both the first rotor 8 and the first motor 61.Make during actual job when needing the first rotor of unmanned plane is installed or dismantled, the most only need to rotate described first rotor 8, such as the first rotor 8 or rotation counterclockwise first rotor 8 of turning clockwise, the installation or removal between described first rotor 8 and described first motor 61 can be realized.Compared to traditional bolt that directly uses, the first rotor 8 is fixed on the first motor 61, when the first rotor 8 is dismantled from the first motor 61 by needs, or when installing, it is both needed to by extraneous handle to turn bolt, dismounting and the installment work of the first rotor 8 can be completed.And due to for connecting the first rotor 8 and the individual component that fixing bolt is individualism of the first motor 61, when by handle turn bolt unloaded time, often due to the complexity of execute-in-place environment, easily cause the loss of fixing bolt, and once fix bolt loss, the most just cannot complete the first rotor 8 and installment work of the first motor 61, i.e. cause the serious consequence that flight equipment cannot fly.And the present embodiment, it is exactly based on employing Quick-dismantle component 7 by threaded to both the first rotor 8 and the first motor 61 so that the two is when installing or dismantle, it is not necessary to by external operation instrument (such as handle), quick and convenient, have the advantages that working performance is high.
For Quick-dismantle component 7, continuing with seeing Figure 21, described Quick-dismantle component 7 at least includes: the first screw the 71, second screw the 72, first screw buckle 73 and the first dismounting nut 74.Wherein, the inwall of described first screw buckle 73 is provided with the first female thread 76, and the bottom of described first screw buckle 73 offers the first screw 77 so that described first screw buckle 73 is fixed on the first surface 611 of described first motor 61 by described first screw 432 through described first screw 77.The outer wall of described first dismounting nut 74 is provided with first external screw thread 78 suitable with described first female thread 76, and described first dismounting nut 74 top offer the second screw 79 so that described second screw 72 sequentially pass through described first rotor 8, described second screw 79 by described first dismounting nut 74 be fixed on described first rotor 8.
Wherein, the first screw buckle 73 is fixed on the first surface 611 of the first motor 61 by the first screw 71, and the first dismounting nut 74 is fixed on the first rotor 8 by the second screw 72.And first the first female thread 76 offered of the inwall of screw buckle 73, and the first external screw thread 78 that the outer wall of the first dismounting nut 74 is offered mates completely, namely occlusion locking between the first female thread 76 and the first external screw thread 78, can be realized.Thus make, when the first rotor 8 is arranged in rotor shaft 3 by needs, owing to the first motor 61 is fixed on the end of rotor shaft 3, also will be arranged on the first motor 61 by the first rotor 8.Now, only need manual rotation the first rotor 8, first external screw thread 78 is engaged mutually with the first female thread 76, continue to rotate, then the first dismounting nut 74 and locking of the first screw buckle 73 is realized, owing to the first dismounting nut 74 is fixed on the first rotor 8, the first screw buckle 73 is fixed on the first motor 61, namely the locking achieving the first rotor 8 and the first motor 61 (rotor shaft 3) is installed.And when disassembly is desired, the most only need to reversely rotate the first rotor 8, it is achieved the first external screw thread 78 and separation of the first female thread 76.There is feature swift to operate, convenient.
It should be noted that, unmanned plane is during practical flight, the direction of rotation of the first rotor 8 is direction of rotation counterclockwise, now, owing in flight course, the first rotor 8 itself is in rotating state, and itself also it is to use to rotate the connected mode realizing fastening in an embodiment between the first rotor 8 and the first motor 61.Such as, when the first rotor 8 is to be fastened therebetween by the realization that turns clockwise relative to the first motor 61, due in flight course the first rotor 8 normally rotate to be counterclockwise, now rotate along with the most normal of the first rotor 8, namely the first rotor 8 is equivalent to the first motor 61 and has the driving of rotation counterclockwise.And owing to the first rotor 8 could realize fastening therebetween by turning clockwise relative to the first motor 61, otherwise so when occurring that the first rotor 8 is to rotate counterclockwise relative to the first motor 61, fastening relationships between the first rotor 8 and the first motor 61 i.e. can be caused to occur loosening, even result in the first rotor 8 and fly away from the first motor 61 and the phenomenon generation that causes unmanned plane to crash.
Therefore, in order to avoid unmanned plane causes the fastening relationships between the first rotor 8 and the first motor 61 to occur loosening in flight course due to normal the rotation counterclockwise of the first rotor 8, the embodiment of the present invention will rotate, between the first rotor 8 and the first motor 61, the direction that the direction tightened is also configured to rotate counterclockwise.That is, the occlusion locking direction of first female thread 76 set by inwall of first external screw thread 78 set by outer wall of the first dismounting nut 74 and the first screw buckle 73 is also counterclockwise.Thus make when the first rotor 8 is to realize fastening therebetween by rotation counterclockwise relative to the first motor 61, due in flight course the first rotor 8 normally rotate to be counterclockwise, now rotate along with the most normal of the first rotor 8, namely the first rotor 8 is equivalent to the first motor 61 and also has the trend of rotation counterclockwise.
And due to the first rotor 8 relative to the first motor 61 exactly by rotating the fastening that could realize therebetween counterclockwise, so on the one hand, it is effectively prevented when the first rotor 8 is to be locked by the realization occlusion that turns clockwise relative to the first motor 61, cause due to normally rotating to be counterclockwise of the first rotor 8 fastening relationships between first rotor 8 and the first motor 61 to occur loosening, even result in the first rotor 8 and fly away from the first motor 61 and the technological deficiency that causes unmanned plane to crash.On the other hand, owing to the first rotor 8 itself is also by rotating counterclockwise the fastening that could realize therebetween relative to the first motor 4, when rotating along with the most normal of the first rotor 8, and make the first rotor 8 be equivalent to the first motor 61 and also have the trend of rotation counterclockwise, the most also the first rotor 8 and the first motor 61 fastening relationships therebetween is increased, ensure that the normal safe flight of flight equipment, have the advantages that security performance is high.
Further, continuing with seeing Figure 20-21, as described above, when sequentially passed through by the second screw 72 described first rotor 8, described second screw 79 by described first dismounting nut 74 be fixed on described first rotor 8 time, owing to unmanned plane is in flight course, external resistance many factors suffered by first rotor 8, such as air-flow, wind direction etc..It is bigger relative to the vibrations of the first motor 61 and/or rotor shaft 3 that this allows for the first rotor 8 in flight course, but, vibrations can make the annexation extremely unstable between second screw the 72, first rotor 8 and the first dismounting nut 74 three for a long time, even cause the second screw 72 to loosen, then cause security incident.Therefore, the present embodiment is by setting up the first vibration damping sheet 75, and offer the first through hole on described first vibration damping sheet 75, so that described second screw 72 sequentially passes through described first through hole, described first rotor 8 and the second screw 79 and is fixed on described first rotor 8 by described first dismounting nut 437.As preferably, first vibration damping sheet 75 can be in disc-shaped, to increase the first vibration damping sheet 75 and contact area of the first rotor 8 upper surface, by the second screw 72 by the first vibration damping sheet 75 and the first rotor 8 upper surface relative to fastening, to reduce the vibrations relative to the first motor 61 of first rotor 8, improve the safety and stability performance in flight course.
As preferably, the quantity of described first screw 71 is 2；The quantity of described second screw 72 is 2；The quantity of described first screw 77 is 2；The quantity of described second screw 79 is 2.Wherein, each corresponding described first screw 77 of described first screw 71 so that described first screw buckle 73 is fixed on described first motor 61 by each described first screw 71 through corresponding described first screw 77；Each corresponding described second screw 79 of described second screw 72 so that described first screw buckle 73 is fixed on described first motor 61 by each described second screw 72 through corresponding described second screw 79.
Although preferred embodiments of the present invention have been described, but those skilled in the art once know basic creative concept, then these embodiments can be made other change and amendment.So, claims are intended to be construed to include preferred embodiment and fall into all changes and the amendment of the scope of the invention.
Obviously, those skilled in the art can carry out various change and modification without departing from the spirit and scope of the present invention to the present invention.So, if these amendments of the present invention and modification belong within the scope of the claims in the present invention and equivalent technologies thereof, then the present invention is also intended to comprise these change and modification.
Claims (10)
1. having a unmanned plane for dismountable rotor structure, wherein, unmanned plane includes rotor shaft, flight control system and The Cloud Terrace, it is characterised in that described in there is the unmanned plane of dismountable rotor structure include:
First rotor；
Second rotor；
Two Quick-dismantle components；
Rotor power assembly, described rotor power assembly is fixed in described rotor shaft, and is connected with described flight control system, thinks described first rotor and the powered rotation of described second rotor；And described first rotor is rotationally fixed on described rotor power assembly by a Quick-dismantle component so that described first rotor is rotatable relative to described rotor shaft；Described second rotor is rotationally fixed on described rotor power assembly by another Quick-dismantle component so that described second rotor is rotatable relative to described rotor shaft；And the diameter of described first rotor is more than the diameter of described second rotor,
Fuselage, described fuselage includes:
Casing；
Body, the inside of described body is hollow-core construction, and is provided with at least one installing port on described body；
Second dismounting assembly, detachable for described casing is connected on described body, and covers described installing port by described casing by described second dismounting assembly；Wherein, parts to be installed in described body are placed into by described installing port relative to described body or are removed；
First dismounting assembly, described first dismounting assembly is fixed on described body, and is slidably connected with described The Cloud Terrace, so that described The Cloud Terrace can slide relative to described first dismounting assembly or described body；
Wherein, by described first dismounting assembly, described The Cloud Terrace is connected on described body so that described The Cloud Terrace is by detachable between described first dismounting assembly and described body.
There is the unmanned plane of dismountable rotor structure the most as claimed in claim 1, it is characterised in that described rotor power assembly includes:
Refrigerating seat, described refrigerating seat includes the first stationary plane and the second stationary plane, described first stationary plane and described second stationary plane transverse axis centered by described rotor shaft, is symmetrically dispersed in the both sides of described rotor shaft；
First motor, described first motor is fixed on described first stationary plane, makes described first rotor be fixed on described first motor by what a Quick-dismantle component rotated；
Second motor, described second motor is fixed on described second stationary plane, makes described second rotor be fixed on described second motor by what another Quick-dismantle component rotated；
First electricity is adjusted, and described first electricity is adjusted and is fixed on the inside of described refrigerating seat, and is connected with the flight control system described first motor and described unmanned plane within respectively, rotates moving the first rotor described in described first driven by motor by the described first electric transfer drive；
Second electricity is adjusted, and described second electricity is adjusted and is fixed on the inside of described refrigerating seat, and is connected with the flight control system described second motor and described unmanned plane within respectively, rotates moving the second rotor described in described second driven by motor by the described second electric transfer drive.
There is the unmanned plane of dismountable rotor structure the most as claimed in claim 2, it is characterised in that
Described refrigerating seat is provided with at least one vent, communicates with free surrounding space with the inner space by described refrigerating seat.
There is the unmanned plane of dismountable rotor structure the most as claimed in claim 3, it is characterised in that
Described first electricity is stealthily substituted and is included: the first electric capacity, first circuit board and the first heat sink；Wherein, described first circuit board is connected with described first electric capacity, described first motor and described flight control system respectively, and described first heat sink is attached on described first circuit board；
With,
Described second electricity is stealthily substituted and is included: the second electric capacity, second circuit board and the second heat sink；Wherein, described second circuit board is connected with described second electric capacity, described second motor and described flight control system respectively, and described second heat sink is attached on described second circuit board.
There is the unmanned plane of dismountable rotor structure the most as claimed in claim 4, it is characterised in that
Described first heat sink and/or described second heat sink are aluminium sheets.
6. the unmanned plane with dismountable rotor structure as described in claim 4 or 5, it is characterised in that
Described first circuit board is between described first electric capacity and described first heat sink；
And/or,
Described second circuit board is between described second electric capacity and described second heat sink.
There is the unmanned plane of dismountable rotor structure the most as claimed in claim 2, it is characterised in that described Quick-dismantle component includes:
First screw；
Second screw；
First screw buckle, the inwall of described first screw buckle is provided with the first female thread, and the bottom of described first screw buckle offers the first screw so that described first screw buckle is fixed on described first motor or described second motor by described first screw through described first screw；
First dismounting nut, the outer wall of described first dismounting nut is provided with the first external screw thread, and described first dismounting nut top offer the second screw, make described second screw sequentially pass through described first rotor, the second screw by described first dismounting nut be fixed on described first rotor, or make described second screw sequentially pass through described second rotor, the second screw by described first dismounting nut be fixed on described second rotor；
Wherein, described first female thread is suitable with described first external screw thread, and by the occlusion between described first female thread and described first external screw thread or separation, corresponding realizes the installation between described first rotor and described first motor or between described second rotor and described second motor or dismounting.
There is the unmanned plane of dismountable rotor structure the most as claimed in claim 7, it is characterised in that
The quantity of described first screw is 2；
The quantity of described second screw is 2；
The quantity of described first screw is 2；
The quantity of described second screw is 2；
Wherein, each corresponding described first screw of described first screw so that described first screw buckle is fixed on described first motor or described second motor by each described first screw through corresponding described first screw；Each corresponding described second screw of described second screw so that described first screw buckle is fixed on described first motor or the second motor by each described second screw through corresponding described second screw.
There is the unmanned plane of dismountable rotor structure the most as claimed in claim 1, it is characterised in that
In the vertical direction, described first rotor is positioned at the top of described second rotor.
There is the unmanned plane of dismountable rotor structure the most as claimed in claim 1, it is characterised in that described first dismounting assembly includes:
Fixed plate, described fixed plate is fixed on described body, and is slidably connected with described The Cloud Terrace, so that described The Cloud Terrace slides relative to described fixed plate；
Positioning element, described positioning element is fixed in described fixed plate, to position described The Cloud Terrace relative to the position of described fixed plate, and then realizes described The Cloud Terrace relative to the installation of described body or dismounting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610280566.3A CN105818974B (en) | 2016-04-29 | 2016-04-29 | Unmanned plane with detachable rotor structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610280566.3A CN105818974B (en) | 2016-04-29 | 2016-04-29 | Unmanned plane with detachable rotor structure |
Publications (2)
| Publication Number | Publication Date |
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| CN105818974A true CN105818974A (en) | 2016-08-03 |
| CN105818974B CN105818974B (en) | 2018-10-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610280566.3A Expired - Fee Related CN105818974B (en) | 2016-04-29 | 2016-04-29 | Unmanned plane with detachable rotor structure |
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| Country | Link |
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| CN (1) | CN105818974B (en) |
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| CN106437997A (en) * | 2016-10-26 | 2017-02-22 | 天津曙光天成科技有限公司 | Cooling device for engine of multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle |
| CN107380418A (en) * | 2017-08-10 | 2017-11-24 | 河南谷翼自动化科技有限公司 | A kind of axle plant protection unmanned plane of modular assembly four |
| CN109557102A (en) * | 2019-01-15 | 2019-04-02 | 成都圭目机器人有限公司 | A kind of ship type underground sewer detection robot |
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| CN109557102A (en) * | 2019-01-15 | 2019-04-02 | 成都圭目机器人有限公司 | A kind of ship type underground sewer detection robot |
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| Publication number | Publication date |
|---|---|
| CN105818974B (en) | 2018-10-19 |
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Address after: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Applicant after: Ewatt Technology Co.,Ltd. Address before: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Applicant before: Ewatt Technology Co.,Ltd. |
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