CN105818995A - Detachable unmanned aerial vehicle - Google Patents
Detachable unmanned aerial vehicle Download PDFInfo
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- CN105818995A CN105818995A CN201610280404.XA CN201610280404A CN105818995A CN 105818995 A CN105818995 A CN 105818995A CN 201610280404 A CN201610280404 A CN 201610280404A CN 105818995 A CN105818995 A CN 105818995A
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- China
- Prior art keywords
- side plate
- chute
- fixed
- positioning
- location
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
Abstract
The invention discloses a detachable unmanned aerial vehicle and belongs to the technical field of unmanned aerial vehicles. The detachable unmanned aerial vehicle comprises a fuselage, second detaching assemblies, a first detaching assembly, a signal positioning assembly, a rotary wing power assembly and a quick detaching assembly, wherein the fuselage comprises a shell and a body, the interior of the body is of a hollow structure, and the body is provided with at least one mounting port; the second detaching assemblies detachably connect the shell to the body, and the shell covers the mounting ports; the first detaching assembly is fixed on the body; the signal positioning assembly is fixed on the shell; the rotary wing power assembly is fixed on rotary wing shafts and comprises at least one electronic speed control; and a first rotary wing is fixed on the rotary wing power assembly in a rotating manner by virtue of the quick detaching assembly. The detachable unmanned aerial vehicle solves the technical defects that when a to-be-mounted device in the fuselage is replaced or maintained, the operation is tedious, the efficiency is low, and a cloud terrace is easily collided in the prior art.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, particularly to a kind of dismountable unmanned plane.
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 and The Cloud Terrace, and rotor shaft is rotationally fixed on fuselage, and fuselage interior is additionally provided with flight control system simultaneously.
But, in the prior art, the manufacture of unmanned aerial vehicle body is often one-body molded during assembling, The Cloud Terrace is the most directly fixed on the bottom of fuselage by an installing plate, device to be installed such as flight control systems needed for fuselage interior etc. are often through first dismantling the installing plate of fuselage bottom, then in putting into fuselage.This allows for when the erecting device of fuselage interior is substituted or safeguarded it may first have to remove and install plate, and The Cloud Terrace is fixed on installing plate so that while removing and installing plate, The Cloud Terrace also needs to dismantle in the lump, complex operation.And during The Cloud Terrace is dismantled, easily damaged because of collision.Do not possesses the feature efficient, quick and safe performance is high.
Summary of the invention
The present invention provides a kind of dismountable unmanned plane, solves or part solves in prior art the device to be installed to fuselage interior when substituting or keep in repair, the technological deficiency that complex operation, inefficiency and The Cloud Terrace easily collide.
For solving above-mentioned technical problem, the invention provides a kind of dismountable unmanned plane, wherein, unmanned plane includes the first rotor, rotor shaft, The Cloud Terrace and flight control system, it is characterised in that described dismountable unmanned plane includes: fuselage, and 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；Signal framing assembly, described signal framing assembly is fixed in described casing, and is provided with the localizer for unmanned plane carries out signal framing in described signal framing assembly；Rotor power assembly, described rotor power assembly is fixed in described rotor shaft, and is connected with described flight control system, thinks the powered rotation of described first rotor, and described rotor power assembly at least includes that an electricity is adjusted；Quick-dismantle component, described first rotor is rotationally fixed on described rotor power assembly by described Quick-dismantle component；Wherein, by described first dismounting assembly, described The Cloud Terrace is connected on described body, make described The Cloud Terrace by detachable between described first dismounting assembly and described body, and described localizer is arranged on the housing by described signal framing assembly, it is isolated with the external air flow by described localizer with described fuselage.
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.
Optionally, described fixed plate includes: the first side plate；Second side plate, described first side plate and described second side plate are parallel；Transverse slat, described first side plate and described second side plate are perpendicular with described transverse slat, and described transverse slat is slidably connected with described first side plate and described second side plate respectively, described The Cloud Terrace is fixing with described transverse slat to be connected, and then by described transverse slat, described The Cloud Terrace is slided relative to described first side plate and described second side plate；Described positioning element is individually fixed on described first side plate and described second side plate, to position described transverse slat relative to the position of described first side plate and described second side plate.
Optionally, described first side plate and described second side plate are respectively arranged with a chute, to be arranged in described chute by described transverse slat so that described transverse slat is slided relative to described first side plate and described second side plate by described chute；One end of described positioning element corresponding through described first side plate, described second side plate, and in described chute internal projection or contraction, so that one end of described positioning element relative to described chute when described chute internal projection, one end of described positioning element stops that described transverse slat slides in described chute, one end of described positioning element relative to described chute when described chute contract, one end of described positioning element is separated with described transverse slat, so that described transverse slat slides in described chute.
Optionally, described positioning element includes: the first location plunger, and described first location plunger includes the first positioning end；Second location plunger, 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 or contraction, so that described first positioning end is when relative to chute internal projection in described first side plate, described first positioning end stops that described transverse slat slides in chute, described first positioning end is when relative to chute contract in described first side plate, and described first positioning end is separated with described transverse slat, so that described transverse slat slides in chute；Wherein, described second positioning end corresponding through described second side plate, and the chute internal projection in described second side plate or contraction, so that described second positioning end is when relative to chute internal projection in described second side plate, described second positioning end stops that described transverse slat slides in chute, described second positioning end is when relative to chute contract in described second side plate, and described second positioning end is separated with described transverse slat, so that described transverse slat slides in chute.
Optionally, described first location plunger includes: the first bolt, described first bolt is provided with described first positioning end；First positioning thread insert, described first positioning thread insert is set on described first bolt, and is provided with one first compression stroke between described first positioning thread insert and described first bolt；First location spring, described first location spring is arranged in described first compression stroke；Wherein, described first positioning end sequentially passes through described first location spring, described first compression stroke and described first side plate, with the chute internal projection in described first side plate or contraction；With, 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.
Optionally, on described first positioning end of described first bolt, it is provided with one first card convex, so that described first location spring is limited in described first compression stroke, and make described first positioning end when relative to chute contract in described first side plate, by the described first location spring of described first card convex compression；And/or, 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.
Optionally, described second dismounting assembly includes: socket, described socket is fixed on described body；3rd location plunger, described 3rd location plunger is fixed in described casing, and described 3rd location plunger includes the 3rd positioning end；Wherein, in the described socket of insertion that described 3rd positioning end is corresponding, with by described casing and described body clamping.
Optionally, described 3rd location plunger includes: locating dowel and the 3rd caging bolt, described locating dowel is fixed in described casing, and described 3rd caging bolt is fixed in described locating dowel；Described 3rd caging bolt is provided with described 3rd positioning end.
Optionally, described signal framing assembly also includes: location bar, and described location bar includes fixing end and a support end, and described location bar is fixed in described casing by described fixing end；Spiral shell dish, described spiral shell dish is fixed on the bar of described location by described support end, and the inside of described spiral shell dish is hollow-core construction so that described localizer is fixed in described spiral shell dish.
The dismountable unmanned plane that the present invention provides, is connected to detachable for casing on body by the second dismounting assembly so that parts to be installed in described body are placed into relative to body by installing port or are removed.Effectively avoid in conventional art and need by removing and installing plate, and The Cloud Terrace is fixed on installing plate so that while removing and installing plate, The Cloud Terrace also needs to dismantle in the lump and the technological deficiency easily collided of the complex operation, inefficiency and the The Cloud Terrace that cause.The present invention has feature simple to operate, that efficiency is high and The Cloud Terrace security performance 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.
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 dismountable unmanned plane that the present invention provides, is connected to detachable for casing on body by the second dismounting assembly so that parts to be installed in described body are placed into relative to body by installing port or are removed.Effectively avoid in conventional art and need by removing and installing plate, and The Cloud Terrace is fixed on installing plate so that while removing and installing plate, The Cloud Terrace also needs to dismantle in the lump and the technological deficiency easily collided of the complex operation, inefficiency and the The Cloud Terrace that cause.The present invention has feature simple to operate, that efficiency is high and The Cloud Terrace security performance is high.Dismountable unmanned plane in order to provide the present invention elaborates, 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 dismountable unmanned plane 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 dismountable 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 20-21, for the annexation between the first motor 61 and the first rotor 8, 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.Realize when carrying out installation or the dismantlement work of the first rotor 8, only need by rotating described first rotor 8, the fastening between the first rotor 8 and the first motor 61 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, referring to Figure 20-21, 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, and second surface 612 can be understood as the lower surface of the first motor 61, and described first motor 61 is fixed on described refrigerating seat 63 by described first surface 611.Meanwhile, described first rotor 8 is connected by described Quick-dismantle component 7 is detachable with the first surface 611 of described first motor 61.
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.
It is last it should be noted that although the present embodiment merely illustrates the first motor and the first rotor passes through Quick-dismantle component 7 and is attached so that its first rotor has the feature of fast quick-detach.But for many rotor wing unmanned aerial vehicles, between the second rotor described above and the second motor, it is also possible to be attached by Quick-dismantle component 7 so that the second rotor has the feature of fast quick-detach equally.The connected mode by Quick-dismantle component for the second motor and the second rotor, identical with the exercise mode between the first motor and the first rotor, here is omitted.
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. a dismountable unmanned plane, wherein, unmanned plane includes the first rotor, rotor shaft, The Cloud Terrace and flight control system, it is characterised in that described dismountable unmanned plane includes:
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；
Signal framing assembly, described signal framing assembly is fixed in described casing, and is provided with the localizer for unmanned plane carries out signal framing in described signal framing assembly；
Rotor power assembly, described rotor power assembly is fixed in described rotor shaft, and is connected with described flight control system, thinks the powered rotation of described first rotor, and described rotor power assembly at least includes that an electricity is adjusted；
Quick-dismantle component, described first rotor is rotationally fixed on described rotor power assembly by described Quick-dismantle component；
Wherein, by described first dismounting assembly, described The Cloud Terrace is connected on described body, make described The Cloud Terrace by detachable between described first dismounting assembly and described body, and described localizer is arranged on the housing by described signal framing assembly, it is isolated with the external air flow by described localizer with described fuselage.
2. dismountable unmanned plane 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.
3. dismountable unmanned plane as claimed in claim 2, it is characterised in that described fixed plate includes:
First side plate；
Second side plate, described first side plate and described second side plate are parallel；
Transverse slat, described first side plate and described second side plate are perpendicular with described transverse slat, and described transverse slat is slidably connected with described first side plate and described second side plate respectively, described The Cloud Terrace is fixing with described transverse slat to be connected, and then by described transverse slat, described The Cloud Terrace is slided relative to described first side plate and described second side plate；
Described positioning element is individually fixed on described first side plate and described second side plate, to position described transverse slat relative to the position of described first side plate and described second side plate.
4. dismountable unmanned plane as claimed in claim 3, it is characterised in that
It is respectively arranged with a chute, to be arranged in described chute by described transverse slat so that described transverse slat is slided relative to described first side plate and described second side plate by described chute on described first side plate and described second side plate；
One end of described positioning element corresponding through described first side plate, described second side plate, and in described chute internal projection or contraction, so that one end of described positioning element relative to described chute when described chute internal projection, one end of described positioning element stops that described transverse slat slides in described chute, one end of described positioning element relative to described chute when described chute contract, one end of described positioning element is separated with described transverse slat, so that described transverse slat slides in described chute.
5. dismountable unmanned plane as claimed in claim 4, it is characterised in that described positioning element includes:
First location plunger, described first location plunger includes the first positioning end；
Second location plunger, 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 or contraction, so that described first positioning end is when relative to chute internal projection in described first side plate, described first positioning end stops that described transverse slat slides in chute, described first positioning end is when relative to chute contract in described first side plate, and described first positioning end is separated with described transverse slat, so that described transverse slat slides in chute；
Wherein, described second positioning end corresponding through described second side plate, and the chute internal projection in described second side plate or contraction, so that described second positioning end is when relative to chute internal projection in described second side plate, described second positioning end stops that described transverse slat slides in chute, described second positioning end is when relative to chute contract in described second side plate, and described second positioning end is separated with described transverse slat, so that described transverse slat slides in chute.
6. dismountable unmanned plane as claimed in claim 5, it is characterised in that
Described first location plunger includes:
First bolt, described first bolt is provided with described first positioning end；
First positioning thread insert, described first positioning thread insert is set on described first bolt, and is provided with one first compression stroke between described first positioning thread insert and described first bolt；
First location spring, described first location spring is arranged in described first compression stroke；
Wherein, described first positioning end sequentially passes through described first location spring, described first compression stroke and described first side plate, with the chute internal projection in described first side plate or contraction；
With,
Described second location plunger includes:
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.
7. dismountable unmanned plane as claimed in claim 6, it is characterised in that
On described first positioning end of described first bolt, it is provided with one first card convex, so that described first location spring is limited in described first compression stroke, and make described first positioning end when relative to chute contract in described first side plate, by the described first location spring of described first card convex compression；
And/or,
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.
8. dismountable unmanned plane as claimed in claim 1, it is characterised in that described second dismounting assembly includes:
Socket, described socket is fixed on described body；
3rd location plunger, described 3rd location plunger is fixed in described casing, and described 3rd location plunger includes the 3rd positioning end；
Wherein, in the described socket of insertion that described 3rd positioning end is corresponding, with by described casing and described body clamping.
9. dismountable unmanned plane as claimed in claim 8, it is characterised in that
Described 3rd location plunger includes: locating dowel and the 3rd caging bolt, described locating dowel is fixed in described casing, and described 3rd caging bolt is fixed in described locating dowel；
Described 3rd caging bolt is provided with described 3rd positioning end.
10. dismountable unmanned plane as claimed in claim 1, it is characterised in that described signal framing assembly also includes:
Location bar, described location bar includes fixing end and a support end, and described location bar is fixed in described casing by described fixing end；
Spiral shell dish, described spiral shell dish is fixed on the bar of described location by described support end, and the inside of described spiral shell dish is hollow-core construction so that described localizer is fixed in described spiral shell dish.
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| CN201610280404.XA CN105818995B (en) | 2016-04-29 | 2016-04-29 | Detachable unmanned plane |
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| CN201610280404.XA CN105818995B (en) | 2016-04-29 | 2016-04-29 | Detachable unmanned plane |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107796371A (en) * | 2017-10-19 | 2018-03-13 | 太原双鼎科技有限公司 | A kind of unmanned plane surveying and mapping data harvester |
| CN108557093A (en) * | 2018-02-06 | 2018-09-21 | 贵州电网有限责任公司 | A kind of multi-rotor unmanned aerial vehicle cruising inspection system Rapid replacing device |
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| CN201989945U (en) * | 2011-04-15 | 2011-09-28 | 天津全华时代航天科技发展有限公司 | Modular quick-splicing type unmanned aerial vehicle |
| US8991743B1 (en) * | 2012-10-11 | 2015-03-31 | Charles Douglas Pope | Helicopter with blade-tip thrusters and annular centrifugal fuel supply tank and concentric cabin and fuselage |
| CN204916154U (en) * | 2015-07-10 | 2015-12-30 | 哈瓦国际航空技术（深圳）有限公司 | Integration aircraft organism |
| CN205010500U (en) * | 2015-08-10 | 2016-02-03 | 普宙飞行器科技（深圳）有限公司 | Unmanned vehicles's cloud platform quick detach device |
| CN105366041A (en) * | 2015-11-30 | 2016-03-02 | 湖北易瓦特科技股份有限公司 | Multi-rotor structure applied in unmanned aerial vehicle |
| CN205707409U (en) * | 2016-04-29 | 2016-11-23 | 易瓦特科技股份公司 | Dismountable unmanned plane |
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| CN107796371A (en) * | 2017-10-19 | 2018-03-13 | 太原双鼎科技有限公司 | A kind of unmanned plane surveying and mapping data harvester |
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| CN108557093B (en) * | 2018-02-06 | 2024-02-27 | 贵州电网有限责任公司 | Quick reloading device of multi-rotor unmanned aerial vehicle inspection system |
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