CN105366042B - Unmanned flight's equipment - Google Patents
Unmanned flight's equipment Download PDFInfo
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- CN105366042B CN105366042B CN201510861047.1A CN201510861047A CN105366042B CN 105366042 B CN105366042 B CN 105366042B CN 201510861047 A CN201510861047 A CN 201510861047A CN 105366042 B CN105366042 B CN 105366042B
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Abstract
The invention discloses a kind of unmanned flight's equipment, belong to unmanned air vehicle technique field, including fuselage, the first rotor, the second rotor, rotor shaft, the first rotary connector, the second rotary connector, foldable assembly and slide assemblies.Wherein, first rotary connector includes：First motor and the first dismounting screw thread group, the first rotor pass through the described first dismounting screw thread group and the first motor detachable connection so that installation or removal between the first rotor and the first motor can be realized by rotating first rotor；Second rotary connector includes：Second motor and the second dismounting screw thread group, the second rotor pass through the described second dismounting screw thread group and the second motor detachable connection so that installation or removal between the second rotor and the second motor can be realized by rotating second rotor.The present invention has the characteristics that quick, portable and operating efficiency is high.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, more particularly to a kind of unmanned flight's equipment.
Background technology
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Without cockpit 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 equipment such as radars, it is passed into line trace, positioning, remote control, telemetering and number
It is defeated.It can take off as conventional airplane or be launched with booster rocket under wireless remotecontrol, can also be taken to by machine tool in the air
Launch flight.
Unmanned plane of the prior art is usually fixed with a driving motor in the end of rotor shaft, takes off for unmanned plane
Rotor generally use bolt be directly fixed on driving motor, and then by driving motor drive rotor rotated.
However, this connection mode being directly bolted so that rotor is either being mounted on driving motor
On or rotor dismantled from driving motor, be both needed to turn bolt by extraneous handle, and then complete the peace of rotor
Assembly and disassembly work, for multi-rotor unmanned aerial vehicle, rotor quantity is often multiple, when need to more rotors without
When several man-machine rotors are installed or dismantled so that installing and dismounting work is very cumbersome, influences the work of staff
Industry efficiency.Meanwhile in the prior art the fuselage of unmanned plane and rotor often by the way of being fixedly connected so that rotor compared with
The fuselage of unmanned plane is in the state of relative securement, however no matter the mode that this fuselage is fixedly connected with rotor causes unmanned plane
Be in flight operation again without flight operation when, rotor, always in open configuration, under the state, works as nothing compared with fuselage
It is man-machine that the rotor under open configuration not only occupies parking space when not having flight operation, at the same also easily by it is extraneous other
Cargo clashing and breaking are broken, and are greatly shortened the service life of unmanned plane (rotor), and then are brought dimension due to rotor repair is frequent
Repair the defects of of high cost.
The content of the invention
The present invention provides a kind of unmanned flight's equipment, solves or part solves the prior art for multi-rotor unmanned aerial vehicle
Several rotors when being installed or being dismantled, installing and dismounting work is very cumbersome, influences the skill of staff's operating efficiency
Art defect.Meanwhile be rotatablely connected rotor shaft and fuselage by foldable assembly, it overcomes in the prior art when unmanned plane does not fly
During row operation, the paddle under open configuration not only occupies parking space, also easily by other extraneous cargo clashing and breaking, the skill broken
Art defect.
The present invention provides a kind of unmanned flight's equipment, including fuselage, at least four first rotors and described first
The second identical rotor of rotor quantity, the rotor shaft identical with first rotor or the second rotor quantity；The nothing
People's flight equipment further includes：First rotary connector identical with the first rotor quantity, first rotor pass through
One first rotary connector is rotatably connected with a rotor shaft, and first rotary connector includes：First electricity
Machine, first motor includes first surface and second surface, and first motor is fixed on institute by the first surface
It states in rotor shaft；First dismounting screw thread group, first rotor are revolved by the described first dismounting screw thread group with the first surface
Turn connection so that by rotating the installation between the first rotor realization first rotor and first motor or tearing open
It unloads；Second rotary connector identical with the second rotor quantity, second rotor pass through second rotation
Turn connector to be rotatably connected with a rotor shaft, second rotary connector includes：Second motor, second motor
Including the 3rd surface and the 4th surface, and second motor is fixed on by the 3rd surface in the rotor shaft；Second
Screw thread group is dismantled, second rotor is rotatably connected by the described second dismounting screw thread group with the 3rd surface so that is passed through
Rotate the installation or removal between the second rotor realization second rotor and second motor；With first rotor
Quantity or the identical foldable assembly of the second rotor quantity, a rotor shaft pass through a foldable assembly and rotate
Ground is fixed on the fuselage so that the rotor shaft can be opened or shunk compared with the fuselage；Slide assemblies, for pacifying
Battery is put, and the slide assemblies are connected with the sliding machine body, to be slided compared with the fuselage.
Optionally, the first dismounting screw thread group includes：First screw；Second screw；First screw buckle, first spiral shell
The inner wall of line button is provided with the first internal thread, and the bottom of first screw buckle offers the first screw hole so that described first
First screw buckle is fixed on the first surface by screw through first screw hole；First dismounting nut, described the
The outer wall of one dismounting nut is provided with the first external screw thread, and offers the second screw hole at the top of the first dismounting nut so that
Second screw sequentially passes through first rotor, the described first dismounting nut is fixed on described first by second screw hole
On rotor；Wherein, first internal thread is adapted with first external screw thread, and passes through first internal thread and described
Occlusion between one external screw thread either the corresponding installation realized between first rotor and first motor of separation or
Dismounting.
Optionally, the first dismounting screw thread group further includes：First vibration damping sheet offers first on first vibration damping sheet
Through hole, and second screw sequentially passes through the first through hole, first rotor and the second screw hole and is dismantled described first
Nut is fixed on first rotor.
Optionally, the second dismounting screw thread group includes：3rd screw；4th screw；Second screw buckle, second spiral shell
The inner wall of line button is provided with the second internal thread, and the bottom of second screw buckle offers the 3rd screw hole so that the described 3rd
Second screw buckle is fixed on the 3rd surface by screw through the 3rd screw hole；Second dismounting nut, described the
The outer wall of two dismounting nuts is provided with the second external screw thread, and offers the 4th screw hole at the top of the second dismounting nut so that
4th screw sequentially passes through second rotor, the described second dismounting nut is fixed on described second by the 3rd screw hole
On rotor；Wherein, second internal thread is adapted with second external screw thread, and passes through second internal thread and described
Occlusion between two external screw threads either the corresponding installation realized between second rotor and second motor of separation or
Dismounting.
Optionally, the first dismounting screw thread group further includes：Second vibration damping sheet offers second on second vibration damping sheet
Through hole, and the 4th screw sequentially passes through second through hole, second rotor and the 4th screw hole and is dismantled described second
Nut is fixed on second rotor.
Optionally, the foldable assembly includes：Side plate part, the side plate part are fixed on the end of the rotor shaft；Rotation
Part, the revolving part are fixed on the fuselage, and are rotatablely connected with the side plate part, make the side plate part and the revolving part
Between it is rotatable；Locating part, the locating part are fixed on the side plate part, with to the revolving part compared with the side plate part
Rotation angle positioned.
Optionally：The end of the rotor shaft includes first side and second side, and the first side and described the
Two side faces are symmetrically distributed in the end both sides of the rotor shaft；The side plate part includes：First side plate, first side plate are consolidated
Due in the first side；Second side plate, second side plate are fixed in the second side；Wherein, first side
A sliding slot is offered on plate and first side plate, the locating part is made to be slided in the sliding slot.
Optionally, the locating part includes：Fixed link, the fixed link are fixed on first side plate and the second side
Between plate, and it is perpendicular with first side plate and second side plate respectively, and a slide opening is offered in the fixed link；Limit
Position bar, the gag lever post is placed in the sliding slot, and is slidably connected with the sliding slot；Stayed mast, one end of the stayed mast are worn
It crosses the slide opening to be fixedly connected with the gag lever post so that by the way that the stayed mast is pulled to drive the gag lever post in the sliding slot
Inside slided.
Optionally, the revolving part includes：First puts ear, and the first swing hole is offered on the first pendulum ear；Second pendulum
Ear, it is described second pendulum ear on offer and described first swing hole it is corresponding second swing hole；Fixed cylinder, the fixed cylinder
One end is fixed on the fuselage, and the other end is fixedly connected respectively with the described first pendulum ear and the second pendulum ear；Rotation axis, institute
It states rotation axis and sequentially passes through first side plate, the first swing hole, the second swing hole and second side plate, it will
The side plate part and revolving part rotation connection.
Optionally, the slide assemblies include：Fixed seat, the fixed seat are fixed on the fuselage；Sliding rack, it is described
The inside of sliding rack is in hollow-core construction, and for disposing battery, and the sliding rack is slidably fixed in the fixed seat；Card
Button, described be buckled are fixed on the end of the fixed seat, and a protrusion is provided on the buckle, to pass through the convex barrier
The battery is skidded off from the sliding rack.
Advantageous effect：
A kind of unmanned flight's equipment provided by the invention, each first rotor pass through corresponding one first dismounting screw thread
Group is rotatably connected with the first surface of the first motor so that when carrying out the installation of the first rotor or dismantlement work, it is only necessary to logical
It crosses and rotates first rotor, you can realize the fastening or separation between the first rotor and the first motor, each second rotation
The wing is rotatably connected by corresponding one second dismounting screw thread group with the 3rd surface of the second motor so that is carrying out the second rotor
Installation or during dismantlement work, it is only necessary to by rotating second rotor, you can realize between the second rotor and the second motor
Fastening either separation namely without external operation instrument (such as handle) can be completed rotor installation or dismounting work
Make, have the characteristics that quick, portable and operating efficiency is high.Meanwhile the present invention is rotated rotor shaft and fuselage by foldable assembly
Connection so that rotor shaft can realize opening or retraction compared with flight equipment, overcome and work as flight equipment in the prior art
Not during flight operation, the first rotor and/or the second rotor under open configuration not only occupy parking space, while also pole
Easily by other extraneous cargo clashing and breaking, break, greatly shorten the service life of flight equipment, so because paddle repair frequently due to band
The defects of maintenance cost is high is carried out.
Description of the drawings
It in order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the present invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 is the overall structure diagram for unmanned flight's equipment that the embodiment of the present invention one provides；
Fig. 2 is by the side view of Fig. 1 unmanned flight's equipment provided；
Fig. 3 is that the connection relation of the first rotor in Fig. 1, the first dismounting screw thread group and rotor shaft splits structural side view；
Fig. 4 is the connection relation overall structure side view of the first rotor in Fig. 3, the first dismounting screw thread group and rotor shaft；
Fig. 5 is the overall structure diagram one of foldable assembly in Fig. 1；
Fig. 6 is the top view of foldable assembly in Fig. 5；
Fig. 7 is the overall structure diagram two of foldable assembly in Fig. 1；
Fig. 8 is the top view of foldable assembly in Fig. 7；
Fig. 9 is the overall structure diagram of slide assemblies in Fig. 1；
Figure 10 is the side view of slide assemblies in Fig. 9；
Figure 11 is the first rotor, the second rotor and rotor shaft in unmanned flight's equipment provided by Embodiment 2 of the present invention
Connection relation split schematic diagram.
Specific embodiment
Below in conjunction with the attached drawing in the embodiment of the present invention, the technical solution in the embodiment of the present invention is carried out clear, complete
Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art's all other embodiments obtained belong to what the present invention protected
Scope；Involved "and/or" keyword wherein in this implementation, represent and or two kinds of situations, in other words, the present invention is implemented
A and/or B mentioned by example, illustrate two kinds of A and B, A or B situations, describe three kinds of states present in A and B, such as A and/or
B is represented：Only including A does not include B；Only including B does not include A；Including A and B.
Meanwhile in the embodiment of the present invention, when component is referred to as " being fixed on " another component, it can be directly at another
On component or there may also be components placed in the middle.When a component is considered as " connection " another component, it can be direct
It is connected to another component or may be simultaneously present component placed in the middle.When a component is considered as " being arranged at " another group
Part, it can be set directly on another component or may be simultaneously present component placed in the middle.Made in the embodiment of the present invention
Term " vertically ", " horizontal ", "left", "right" and similar statement are merely for purposes of illustration, and are not intended to
The limitation present invention.
A kind of unmanned flight's equipment provided by the invention, each first rotor pass through corresponding one first dismounting screw thread
Group is rotatably connected with the first surface of the first motor so that when carrying out the installation of the first rotor or dismantlement work, it is only necessary to logical
It crosses and rotates first rotor, you can realize the fastening or separation between the first rotor and the first motor, each second rotation
The wing is rotatably connected by corresponding one second dismounting screw thread group with the 3rd surface of the second motor so that is carrying out the second rotor
Installation or during dismantlement work, it is only necessary to by rotating second rotor, you can realize between the second rotor and the second motor
Fastening either separation namely without external operation instrument (such as handle) can be completed rotor installation or dismounting work
Make, have the characteristics that quick, portable and operating efficiency is high.Meanwhile the present invention is rotated rotor shaft and fuselage by foldable assembly
Connection so that rotor shaft can realize opening or retraction compared with flight equipment, overcome and work as flight equipment in the prior art
Not during flight operation, the first rotor and/or the second rotor under open configuration not only occupy parking space, while also pole
Easily by other extraneous cargo clashing and breaking, break, greatly shorten the service life of flight equipment, so because paddle repair frequently due to band
The defects of maintenance cost is high is carried out.
Embodiment one
Specifically, -2 are please referred to Fig.1, a kind of unmanned flight's equipment that the embodiment of the present invention one provides includes at least：Machine
Body 1, at least four first rotors 2, the rotor shaft 3 identical with 21 quantity of the first rotor and 21 quantity of the first rotor
Identical the first rotary connector 4, the foldable assembly 5 identical with 21 quantity of the first rotor, the slip for disposing battery
Component 6 and stent 8.
Wherein, first rotor 21 can by first rotary connector 4 and a rotor shaft 3
It is detachably connected with.Please as shown in Figure 3-4, first rotary connector 4 includes at least：First motor 41 and the first dismounting screw thread
Group 43.First motor 41 is for driving first rotor 21 to be rotated, fuselage 1 to be driven to fly.First motor 41
Including first surface 411 and second surface 412.It in embodiments of the present invention, can be as shown in figure 3, first surface 411 be appreciated that
To be the upper surface of the first motor 41, second surface 412 can be understood as the lower surface of the first motor 41, and described first is electric
Machine 41 is fixed on by the first surface 411 in the rotor shaft 3.Meanwhile first rotor 21 is torn open by described first
Unload 411 detachable connection of first surface of screw thread group 43 and first motor 41.
For the connection mode of the first rotor 21 and the first motor 41, the embodiment of the present invention one is torn open by adding first
Screw thread group 43 is unloaded, is threadedly coupled both the first rotor 21 and the first motor 41 by the first dismounting screw thread group 43.So that in reality
In the operation process of border when multiple rotors to unmanned flight's equipment is needed to be installed or dismantled, only need described in rotation
First rotor 21 such as rotates clockwise the first rotor 21 or counterclockwise the first rotor 21 of rotation, you can realizes first rotation
Installation or removal between the wing 21 and first motor 41.Directly the first rotor 21 is fixed using bolt compared to traditional
In on the first motor 41, when needing that the first rotor 21 is dismantled or installed from the first motor 41, it is both needed to by extraneous
Hand turns bolt, can complete the disassembly and installation work of the first rotor 21.And due to being used to connect the first rotor 21 and the
The fixing bolt of one motor 41 is the individual component of individualism, when turning bolt by handle and being unloaded, often due to
The complexity of execute-in-place environment easily causes the loss of fixing bolt, once and fixing bolt lose, then can not just complete the
The installment work of one rotor 21 and the first motor 41, that is, the serious consequence for causing flight equipment that can not fly.And the present invention is implemented
Example is exactly based on and is threadedly coupled both the first rotor 21 and the first motor 41 using the first dismounting screw thread group 43 so that the two
In installation or dismounting, without external operation instrument (such as handle), fast and conveniently, the spy for having operating efficiency high
Point.
For the first dismounting screw thread group 43, continuing with referring to Fig. 4, the first dismounting screw thread group 43 includes at least：First
Screw 431, the second screw 432, the first screw buckle 433 and the first dismounting nut 436.Wherein, first screw buckle 433 is interior
Wall is provided with the first internal thread 434, and the bottom of first screw buckle 433 offers the first screw hole 435 so that described first
First screw buckle 433 is fixed on the first surface of first motor 41 through first screw hole 435 by screw 432
On 411.The outer wall of the first dismounting nut 436 is provided with the first external screw thread being adapted with first internal thread 434
437, and the top of the first dismounting nut 436 offers the second screw hole 438 so that second screw 432 sequentially passes through
Described first dismounting nut 436 is fixed on first rotor 21 by first rotor 21, second screw hole 438.
Wherein, the first screw buckle 433 is fixed on by the first screw 431 on the first surface 411 of first motor 41, and first
Dismounting nut 436 is fixed on by the second screw 432 on the first rotor 21.And first screw buckle 433 inner wall opened up
The first external screw thread 437 that the outer wall of one internal thread 434 and the first dismounting nut 436 is opened up exactly match namely first in spiral shell
Occlusion locking can be realized between 434 and first external screw thread 437 of line.It so allows for, when needing to be mounted on the first rotor 21
When in rotor shaft 3, since the first motor 41 is fixed on the end of rotor shaft 3, the first rotor 21 is also mounted on the first motor
On 41.At this time, it is only necessary to the first rotor of manual rotation 21 so that the first external screw thread 437 is mutually engaged with the first internal thread 434, is continued
The locking of the first dismounting 436 and first screw buckle 433 of nut is then realized in rotation, since the first dismounting nut 436 is fixed on the
On one rotor 21, the first screw buckle 433 is fixed on the first motor 41 namely realizes the first rotor 21 and the first motor 41
The locking installation of (rotor shaft 3).And when disassembly is desired, it only needs to reversely rotate the first rotor 21 at this time, realizes the first external screw thread
437 and first internal thread 434 separation.It is swift to operate, convenient to have the characteristics that.
It should be noted that unmanned flight's equipment, during practical flight, the direction of rotation of the first rotor 21 is the inverse time
Pin direction of rotation, at this point, due in flight course the first rotor 21 be and the first rotor 21 in rotating state in itself
And first itself be also the connection mode that fastening is realized using rotation in embodiments of the present invention between motor 41.For example, when the
One rotor 21 is when being fastened therebetween by rotating clockwise realization, due to first in flight course compared with the first motor 41
The normal of rotor 21 is rotated to be counterclockwise, at this time with 21 phase of normal rotation counterclockwise namely the first rotor of the first rotor 21
When there is the driving that rotates counterclockwise in the first motor 41.And since the first rotor 21 compared with the first motor 41 is by clockwise
Rotation could realize what is fastened therebetween, then on the contrary it is to revolve counterclockwise when there is the first rotor 21 compared with the first motor 41
When turning, i.e., the fastening relationships between the first rotor 21 and the first motor 41 can be caused to loosen, even result in the first rotor 21
The phenomenon that flying away from the first motor 41 and unmanned flight's equipment caused to crash.
Therefore, in order to avoid more rotor flying equipment in flight course due to the normal rotation counterclockwise of the first rotor 21
And the fastening relationships between the first rotor 21 and the first motor 41 is caused to loosen, the embodiment of the present invention is by 21 He of the first rotor
The direction that the direction tightened is also configured to rotate counterclockwise is rotated between first motor 41.That is, the first dismounting nut 436 is outer
The occlusion locking side of the first external screw thread 437 set by wall and the first internal thread 434 set by the inner wall of the first screw buckle 433
To be also counterclockwise.It is by rotating realization two counterclockwise so to allow for working as the first rotor 21 compared with the first motor 41
When being fastened between person, since the normal of the first rotor 21 is rotated to be counterclockwise, at this time with the first rotor 21 in flight course
Normal rotation namely the first rotor 21 are equivalent to the first motor 41 and also have the trend rotated counterclockwise counterclockwise.
And since the first rotor 21 could exactly be realized therebetween compared with the first motor 41 by rotating counterclockwise
Fastening, so on the one hand, effectively prevent when the first rotor 21 compared with the first motor 41 is by rotating clockwise reality
During now occlusion locking, caused due to normal rotate to be counterclockwise of the first rotor 21 between the first rotor 21 and the first motor 41
Fastening relationships loosen, even result in the first rotor 21 fly away from the first motor 41 and cause unmanned flight's equipment crash skill
Art defect.On the other hand, two could be realized due to the first rotor 21 compared with the first motor 4 itself and by rotation counterclockwise
Fastening between person when with the normal rotation counterclockwise of the first rotor 21, and causes the first rotor 21 to be equivalent to the first motor
41 also have the trend rotated counterclockwise, just also increase the first rotor 21 and the first motor 41 at this time and fasten pass therebetween
System, ensure that the normal safe flight of flight equipment, has the characteristics that security performance is high.
Further, it is as described above continuing with referring to Fig. 3-4, when sequentially passing through described first by the second screw 432
When described first dismounting nut 436 is fixed on first rotor 21 by rotor 21, second screw hole 438, due to nobody
Flight equipment is in flight course, and the external resistance factor suffered by the first rotor 21 is more, such as air-flow, wind direction.This just makes
It is bigger compared with the vibrations of the first motor 41 and/or rotor shaft 3 to obtain the first rotor 21 in flight course, however, for a long time
Vibrations can so that the connection relation between the second screw 432, the first rotor 21 and the first dismounting 436 three of nut is extremely unstable,
Even the second screw 432 is caused to loosen, then trigger security incident.Therefore, the embodiment of the present invention is by adding the first vibration damping sheet
439, and first through hole is opened up on first vibration damping sheet 439, lead to so that second screw 432 sequentially passes through described first
Described first dismounting nut 437 is fixed on first rotor 21 by hole, first rotor, 21 and second screw hole 438.Make
To be preferred, the first vibration damping sheet 439 can be in disc-shaped, to increase the contact surface of 21 upper surface of the first vibration damping sheet 439 and the first rotor
Product, by the second screw 432 by the first vibration damping sheet 439 and 21 upper surface of the first rotor compared with fastening, to reduce by the first rotor
21 compared with the first motor 41 vibrations, improve flight course in safety and stability performance.
Incorporated by reference to Fig. 1-2 together refering to Fig. 3-6, for the foldable assembly 5 that the embodiment of the present invention one provides, an institute
It states rotor shaft 3 to be rotationally fixed on the fuselage 1 by a foldable assembly 5 so that the rotor shaft 3 can be opposite
It opens or shrinks in the fuselage 1.It so allows for during actual job, when flight equipment needs flight operation, then
Rotor shaft 3 is rotated by foldable assembly compared with fuselage 1, realizes that rotor shaft 3 is in open configuration compared with fuselage 1.When
When flight operation is not required in flight equipment, then rotor shaft 3 is rotated again by foldable assembly compared with fuselage 1 so that rotation
Wing axis 3 is in indentation state compared with the fuselage 1, overcomes in the prior art when flight equipment not flight operation, place
The first rotor 21 and/or rotor shaft 3 under open configuration not only occupy parking space, while also easily by other extraneous cargos
Clashing and breaking are broken, and greatly shorten the service life of flight equipment (the first rotor 21), and then because of the repair frequency of the first rotor 21
It is numerous and bring the defects of maintenance cost is high.
It specifically, please be as shown in figure 5, the foldable assembly 5 includes at least：Side plate part 51, revolving part 52 and locating part
53。
Wherein, the end of that one end of the rotor shaft 3 away from the first rotor 21 is fixed in one end of the side plate part 51.
The bottom of the revolving part 52 is fixed on the fuselage 1, and top is rotatablely connected with the side plate part 51, makes the side plate part
51 and the revolving part 52 centered on tie point therebetween point realize rotation.The locating part 53 is slidably fixed on institute
State on side plate part 51, and by the locating part 53 compared with the revolving part 52 move come to the revolving part 52 compared with institute
The rotation angle for stating side plate part 51 is positioned.For example, referring to shown in Fig. 5, side plate part 51 is vertical with revolving part 52 at this time divides
Cloth, i.e. side plate part 51 are 90 ° compared with the angle of revolving part 52, and pass through the positioning that locating part 53 realizes 90 ° of angles between the two.
For another example, refer to shown in Fig. 7, at this time side plate part 51 and 52 horizontal distribution of revolving part, i.e., side plate part 51 is compared with revolving part 52
Angle is 0 °, and passes through the positioning that locating part 53 realizes 0 ° of angle between the two.
For the operation principle between 53 three of side plate part 51, revolving part 52 and locating part, please as further described below：
For side plate part 51, including the first side plate 511 and the second side plate 512, and the first side plate 511 and the second side plate
A sliding slot 513 for the slip of locating part 53 is also offered on 512.Wherein, the first side plate 511 is fixed on 3 end of rotor shaft
A side on, it can be understood as be the first side of 3 end of rotor shaft, the second side plate 512 is fixed on 3 end of rotor shaft
On another side, it can be understood as be the second side of 3 end of rotor shaft.And the first side and the second side pair
The end both sides for being distributed in the rotor shaft 3 claimed.The first side plate 511 and the second side plate 512 are so allowed for be mutually parallel
Mode be fixed on the end of rotor shaft 3.
For locating part 53, including：Fixed link 531, gag lever post 532 and stayed mast 533.Wherein, the fixed link
531 both ends are corresponding to be fixed on the first side plate 511 and the second side plate 512 so that fixed link 531 is located at described first
Between side plate 511 and second side plate 512, and it is perpendicular with first side plate 511 and second side plate 512 respectively,
And the slide opening passed through there are one being opened up on the middle part of the fixed link 531 for stayed mast 533.The gag lever post 532 is horizontal
To being placed in the sliding slot 513 so that the axis direction that gag lever post 532 can prolong rotor shaft 3 in the sliding slot 513 is slided
It is dynamic.One end of the stayed mast 533 passes through the slide opening opened up in the fixed link 531, and fixes and connect with the gag lever post 532
It connects so that slided by the way that the stayed mast 533 is pulled to drive described in the gag lever post 532 in sliding slot 513.
For revolving part 52, including：First pendulum ear 521, second puts ear 522, fixed cylinder 523 and rotation axis 524.Its
In, offer the first swing hole on the first pendulum ear 521；It is offered on the second pendulum ear 522 and swings hole with described first
Corresponding second swings hole.And one end of the fixed cylinder 523 is fixed on the fuselage 1, the other end is respectively with described
One pendulum ear 521 is fixedly connected with the described second pendulum ear 522.The rotation axis 524 sequentially passes through first side plate 521, described
First swings hole, the second swing hole and second side plate 522, and the side plate part 51 and the revolving part 52 are rotated
Connection.
Wherein, attached drawing 5 and shown in attached drawing 6 be schematic diagram that revolving part 52 is in 90 ° of angles compared with side plate part 51, this
Under state, gag lever post 532 slides into rightmost (Fig. 5 and Fig. 6 of sliding slot 513 in sliding slot 513 under the action of stayed mast 533
Shown rightmost), fixed cylinder 523 is in vertical state at this time.It further can be as shown in figure 5, the first close limit of pendulum ear 521
The one side of position bar 532 is corresponding to be provided with the first curvilinear portion, and first curvilinear portion is in arc-shaped, back to gag lever post 532
One side it is corresponding be provided with the first screens, first screens is L-shaped.Identical, the second pendulum ear 522 is close to gag lever post 532
One side it is corresponding be provided with the second curvilinear portion, second curvilinear portion is in arc-shaped, back to the one side pair of gag lever post 532
That answers is provided with the second screens, and second screens is L-shaped.
Specifically, when revolving part 52 is in 90 ° of angles compared with side plate part 51 (shown in attached drawing 5), gag lever post at this time
532 slide into 532 and first song of the rightmost of sliding slot 513 namely gag lever post in sliding slot 513 under the action of stayed mast 533
Line position and the second curvilinear portion are in contact.When revolving part 52 is in 0 ° of angle compared with side plate part 51 (shown in attached drawing 7), this
When gag lever post 532 slided in sliding slot 513 under the action of stayed mast 533 to the left side of sliding slot 513, until the first curvilinear portion
The lower section of gag lever post 532 is completely in the second curvilinear portion.At this moment gag lever post 532 just drops down onto the first screens and the second screens
Carry out /V.Because caused by gag lever post 532 digs the first curvilinear portion and the second curvilinear portion upwards at this time stop namely
It limits the first pendulum ear 521 and the second pendulum ear 522 moves up, the level for then realizing side plate part 51 and revolving part 52 is determined
Position.
It should be strongly noted that in order to strengthen the automatic spacing function of foldable assembly 5, realize manual without operating personnel
Pull stayed mast 533 that the /V action between side plate part 51 and revolving part 52 can be realized.Preferably, in the fixed link
A spring 534 is additionally provided between the slide opening and the gag lever post 532 that are opened up among 531, and the spring 534 is set in institute
On the outer wall for stating stayed mast 533.
As stated above, after adding spring 534, (the attached drawing when revolving part 52 is in 90 ° of angles compared with side plate part 51
Shown in 5), gag lever post 532 slides into the most right of sliding slot 513 under the compression thrust of spring 534 in sliding slot 513 at this time
Side namely gag lever post 532 are in contact with the first curvilinear portion and the second curvilinear portion.When needing revolving part 52 compared with side plate
When part 51 is in 0 ° of angle (shown in attached drawing 7), fixed cylinder 523 need to be only overturn at this time, due to the first curvilinear portion and the second curve
Position in arc-shaped, therefore the first curvilinear portion and the second curvilinear portion with clockwise gram in 532 contact process of gag lever post
It takes and is slowly rotated in the compression of spring 534.When the first curvilinear portion and the second curvilinear portion just climb over gag lever post 533, this
When gag lever post 533 spring 534 compression thrust, promote gag lever post 533 be repositioned to the first screens and the second screens rapidly
Place then limits the first pendulum pendulum ear 522 of ear 521 and second and moves up, realizes the horizontal location of side plate part 51 and revolving part 52.
Further, the slide assemblies 6 provided together refering to Fig. 9-10, the embodiment of the present invention one incorporated by reference to Fig. 1, are used for
Battery 7 is disposed, and the slide assemblies 6 are slidably connected with the fuselage 1, to be slided compared with the fuselage 1, and pass through
Slide assemblies 6 realize the dismounting or installation of battery compared with the slip of fuselage 1.
Specifically, the slide assemblies 6 include：Fixed seat 61, sliding rack 62, buckle 63.
Wherein, the fixed seat 61 is fixed on the bottom of the fuselage 1.The inside of the sliding rack 62 is in hollow knot
Structure, and the spatial volume of the hollow-core construction is adapted with the volume of battery 7, for disposing battery 7.And the sliding rack 62 is slided
It is fixed on dynamicly in the fixed seat 61.The buckle 63 is fixed on the end of the fixed seat 61, and is set on the buckle 63
One is equipped with for stopping the protrusion 64 of the slip of battery 7, to stop the battery 7 from the sliding rack 62 by described raised 64
It skids off.
Preferably, the sliding rack can include：First side frame 621, the second side frame 622, the 3rd side frame 623 and slide plate
624.Wherein, what first side frame 621, the second side frame 622 and the 3rd side frame 623 were respectively perpendicular is fixed on the fixed seat 61
On, and first side frame 621 and second side frame 622 opposition distribution, the 3rd side frame 623 and described raised 64 oppose
Distribution, to form institute by first side frame 621, second side frame 622, the 3rd side frame 623 and described raised 64
State the boring structure of sliding rack.First side frame 621 and second side frame 622 and the fixed seat 61 are mutually fixed
One side is respectively provided with there are one slide 67 so that the slide plate 624 passes through the slide 67 and first side frame 621 and described
Second side frame, 622 slide connects, and then realizes slide plate 624 by the slide 67 compared with first side frame 621 and described
Second side frame 622 is slided.The battery arrangement is on the slide plate.
It is noted that the lower section of the buckle 63, also set up that there are one elastic buttons 65.By pressing the elasticity
Button 65 realizes raised 64 opening or clamping.65 structure of elastic button can be similar to the prior art in buckle 3 herein
In the structures such as hair clip, file.When needing battery 7 being fixed in slide assemblies 6, elastic button only need to be pressed downwards
65, protrusion 64 is opened, slide plate 624 is then outwards skidded off compared with sliding rack, after battery 7 is fixed on slide plate 624, compared with
Sliding rack slid inward slide plate 624, loosens elastic button 65, and protrusion is close to battery 7 to be clamped.Battery 7 is realized in nothing
Firm installation in people's flight equipment flight course, has the characteristics that easy to operate, convenient disassembly.
In addition, unmanned flight's equipment that the embodiment of the present invention one provides further includes a stent 8, which can be T-shaped by 2
Frame forms, i.e., including the first T-shaped 81 and second T-shaped frame 82 of frame.Wherein, the vertical end of the first T-shaped frame 81 and the second T-shaped frame 82
Vertical end is fixed on the bottom of fuselage 1, and passes through the transverse end of the first T-shaped frame 81 and the transverse end composition one of the second T-shaped frame 82
It is supported when stablizing chessboard to land to flight equipment, has the characteristics that stationary performance is high.
Just as shown in Figs. 1-2, unmanned flight's equipment that the embodiment of the present invention one provides can be that six rotor unmanned flights set
It is standby, both including 6 the first rotors 21.Certainly, it will be understood by those skilled in the art that six rotor unmanned flight equipment are only this hairs
A kind of embodiment of bright embodiment, not limits to, in other words, for unmanned flights such as quadrotor, eight rotors, 12 rotors
Equipment may also apply to the embodiment of the present invention one.
Embodiment two
Using 12 rotor unmanned flight equipment as the embodiment of the present invention two because six rotors shown in Fig. 1-2 nobody
Flight equipment, what is used is that single-blade is uniaxial namely each rotor shaft 3 is equipped with first motor 41 and one first rotation
The wing 21.When six rotor unmanned flight's equipment shown in Fig. 1-2, each of which rotor shaft 3 two motors of outfit and two rotors,
Namely using double paddles, coaxial (two rotors share a rotor shaft 3, and the second rotor 22 and the second motor 42 form the second rotation
Connector), that is, form 12 rotor unmanned flight's equipment.It can be as shown in figure 11.
At this point, rotor shaft 3 is used to connect one end of fuselage 1 as connecting pin 32, rotated by foldable assembly 5 and fuselage 1
Connection.Rotor shaft 3 is used to connect one end of rotor as coaxial end 21, which can include 311 (upper end of first end face
Face), second end face 312 (lower face) and accommodating space 313.In double paddle coaxial constructions, by the first rotor 21 and the second rotor 22
A rotor group 2 is formed, and the first rotor 21 is rotationally fixed to the first end face 311 at coaxial end 31 by the first motor 41
On, the second rotor 22 passes through on the second motor 42 rotationally second end face 312 at coaxial end 31.For connecting the first motor respectively
41 and second motor 42 electricity adjust be fixed in accommodating space 313 so that first motor 41 and second motor 42 divide
It is not adjusted by the electricity and is connected with the flight control system in fuselage 1, and then the realization flight control system passes through described the
One motor, 41 corresponding driving first rotor 21 is rotated and by described in the 42 corresponding driving of the second motor
Second rotor 22 is rotated.
Obviously, it will be understood by those skilled in the art that in double paddle coaxial constructions, the first rotor 21 passes through the first dismounting spiral shell
Line group 43 is rotatably connected with the first surface 411 of the first motor 41, and the second rotor 22 is also by the second dismounting screw thread group and second
3rd surface 421 of motor 42 is rotatably connected, and (the second dismounting screw thread group forms second in the present embodiment two with the second motor 42
Rotary connector), the second end face 312 of the 4th surface 422 of the second motor shaft end 31 together is fixedly connected.First rotor 21 is logical
It crosses the first dismounting screw thread group 43 to be rotatably connected with the first surface 411 of the first motor 41, be discussed in detail above-mentioned, herein not
It repeats again.It is only rotatably connected below to the second rotor 22 by the second dismounting screw thread group with the 3rd surface 421 of the second motor 42
It elaborates.
The embodiment of the present invention two, continuing with referring to Figure 11, the second dismounting spiral shell corresponding with the first dismounting screw thread group 43
Line group includes at least：3rd screw 441, the 4th screw 442, the second screw buckle 443 and the second dismounting nut 446.Wherein, it is described
The inner wall of second screw buckle 443 is provided with the second internal thread, and the bottom of second screw buckle 443 offers the 3rd screw hole,
So that second screw buckle 443 is fixed on second motor 42 by the 3rd screw 441 through the 3rd screw hole
On 3rd surface 421.The outer wall of the second dismounting nut 446 is provided with the second outer spiral shell being adapted with second internal thread
Line, and the top of the second dismounting nut 446 offers the 4th screw hole so that the 4th screw 442 sequentially passes through described
Described second dismounting nut 446 is fixed on second rotor 22 by the second rotor 22, the 4th screw hole.
Identical with the first dismounting screw thread 43 internal structures of group, the second screw buckle 443 is fixed on second by the 3rd screw 441
On 3rd surface 421 of motor 42, the second dismounting nut 446 is fixed on by the 4th screw 442 on the second rotor 22.And second
The second internal thread that the inner wall of screw buckle 443 is opened up and the second external screw thread that the outer wall of the second dismounting nut 446 is opened up are complete
Occlusion locking can be realized between full matching namely the second internal thread and the second external screw thread.It so allows for, when needing second
When rotor 22 is mounted in rotor shaft 3, since the second motor 42 is fixed on the end of rotor shaft 3, also the second rotor 22 is pacified
On the second motor 42.At this time, it is only necessary to the second rotor of manual rotation 22 so that the second external screw thread and the second internal thread are mutually stung
It closes, continues to rotate, then realize the locking of the second dismounting 446 and second screw buckle 443 of nut, due to the second dismounting nut 446
It is fixed on the second rotor 22, the second screw buckle 443 is fixed on the second motor 42 namely realizes the second rotor 22 and second
The locking installation of motor 42 (rotor shaft 3).And when disassembly is desired, it only needs to reversely rotate the second rotor 22 at this time, realizes second
The separation of external screw thread and the second internal thread.It is swift to operate, convenient to have the characteristics that.
It is specifically intended that in the embodiment of the present invention two, the direction of rotation of the first rotor 21 is counterclockwise, then the
The direction of rotation of two rotors 22 is clockwise, because in single-blade rotary course namely the rotation of the first rotor 21, can produce
Raw corresponding torsion, it is necessary to equal its complete machine by torsion caused by the corresponding thrust confrontation of tail-rotor generation on flight equipment
Weighing apparatus.However, in the embodiment of the present invention two, double paddles (the first rotor 21 and the second rotor 22) take two opposite propellers,
It is rotated towards counterclockwise by the first rotor 21, the second rotor 22 is rotated towards clockwise so that two rotors produce
Two opposite torsion of raw direction, directly cancel out each other.So on the one hand so that the stability of flight equipment is more preferable, direction holds
It is easy to control；On the other hand it is simple in structure, reduce the generation of safety failure；In another aspect, the power bigger of flight equipment flight,
Bearing capacity is more, it is adaptable wide the characteristics of.
Also need explanation, unmanned flight's equipment that the embodiment of the present invention two is provided during practical flight,
The direction of rotation of second rotor 22 is rotates clockwise direction, at this point, due to the second rotor 22 itself and place in flight course
In rotating state, and in itself and using rotation in the embodiment of the present invention two between the second rotor 22 and the second motor 42
Turn to realize the connection mode fastened.For example, it is by rotating realization two counterclockwise to work as the second rotor 22 compared with the second motor 42
When being fastened between person, since the normal of the second rotor 22 is rotated to be clockwise, at this time with the second rotor 22 in flight course
Normal rotation namely the second rotor 22 are equivalent to the second motor 42 and have the driving rotated clockwise clockwise.And due to the second rotation
The wing 22 could be realized and fastened therebetween by rotating counterclockwise compared with the second motor 42, then otherwise when occurring second
Rotor 22 is when rotating clockwise compared with the second motor 42, i.e., can cause the fastening between the second rotor 22 and the second motor 42
Relation loosens, and even results in the phenomenon that the second rotor 22 flies away from the second motor 42 and unmanned flight's equipment is caused to crash and sends out
It is raw.
Therefore, in order to avoid more rotor flying equipment in flight course since the normal of the second rotor 22 rotating clockwise
And the fastening relationships between the second rotor 22 and the second motor 42 is caused to loosen, the embodiment of the present invention two is by the second rotor 22
And second rotate the direction that the direction tightened is also configured to rotate clockwise between motor 42.That is, the second dismounting nut 446
The occlusion locking direction of the second external screw thread set by outer wall and the second internal thread set by the inner wall of the second screw buckle 443
It is clockwise.It is to realize the two by rotating clockwise so to allow for working as the second rotor 22 compared with the second motor 42
Between when fastening, since the normal of the second rotor 22 is rotated to be clockwise, at this time with the up time of the second rotor 22 in flight course
Pin normally rotates namely the second rotor 22 is equivalent to the second motor 42 and also has the trend rotated clockwise.
And since the second rotor 22 could exactly be realized therebetween compared with the second motor 42 by rotating clockwise
Fastening, so on the one hand, effectively prevent when the second rotor 22 compared with the second motor 42 is by rotating reality counterclockwise
During now occlusion locking, caused due to normal rotate to be clockwise of the second rotor 22 between the second rotor 22 and the second motor 42
Fastening relationships loosen, even result in the second rotor 22 fly away from the second motor 42 and cause unmanned flight's equipment crash skill
Art defect.On the other hand, since the second rotor 22 is compared with the second motor 42 itself and by rotating clockwise and could realize
Therebetween fastening when with the normal rotation clockwise of the second rotor 22, and causes the second rotor 22 to be equivalent to the second electricity
Machine 42 also has the trend rotated clockwise, just also increases the second rotor 22 and the second motor 42 at this time and fastens pass therebetween
System, ensure that the normal safe flight of flight equipment, has the characteristics that security performance is high.
Further, it is as described above continuing with referring to Figure 11, when sequentially passing through described second by the 4th screw 442
When described second dismounting nut 446 is fixed on second rotor 22 by rotor 22, the 4th screw hole, due to unmanned flight
Equipment is in flight course, and the external resistance factor suffered by the second rotor 22 is more, such as air-flow, wind direction.This allows for flying
The second rotor 22 is bigger compared with the vibrations of the second motor 42 and/or rotor shaft 3 during row, however, prolonged vibrations
It can so that the connection relation between the 4th screw 442, the second rotor 22 and the second dismounting 446 three of nut is extremely unstable, even
The 4th screw 442 is caused to loosen, then triggers security incident.Therefore, the embodiment of the present invention two is by adding the second vibration damping sheet
449, and the second through hole is opened up on second vibration damping sheet 449, lead to so that the 4th screw 442 sequentially passes through described second
Described second dismounting nut 446 is fixed on second rotor 22 by hole, second rotor, 22 and the 4th screw hole.As excellent
Choosing, the second vibration damping sheet 449 can be in disc-shaped, to increase the contact area of 22 lower surface of the second vibration damping sheet 449 and the second rotor, lead to
The 4th screw 442 is crossed by the second vibration damping sheet 449 and 22 lower surface of the second rotor compared with fastening, it is opposite to reduce by the second rotor 22
In the vibrations of the second motor 42, the safety and stability performance in flight course is improved.
The embodiment of the present invention two and the embodiment of the present invention one are in addition to the second rotor 22 and the second dismounting screw thread group, remaining component
Such as：First rotor 21, first dismounting screw thread group 43, foldable assembly 5, slide assemblies 6, stent 8 etc. are identical, herein no longer
It is repeated for embodiment two, not detailed part sees embodiment one in embodiment two.
Unmanned flight's equipment provided by the invention, its advantage are as described below：
1., each first rotor 21 in the present invention pass through corresponding one first dismounting screw thread group 43 and the first motor
41 411 detachable connection of first surface so that when carrying out the installation of the first rotor 21 or dismantlement work, it is only necessary to pass through
Rotate first rotor 21, you can realize fastening between the first rotor 21 and the first motor 41 or separation namely need not
Installation or the dismantlement work of rotor can be completed by external operation instrument (such as handle), there is quick, portable and operation to imitate
The characteristics of rate is high；
2., the present invention is designed to and first by the way that the occlusion of the first external screw thread 437 and the first internal thread 434 is locked direction
The direction that rotor 21 normally rotates is identical, that is, is also counterclockwise, so on the one hand, to effectively prevent 21 He of the first rotor
Fastening relationships between first motor 41 loosen, and even result in the first rotor 21 and fly away from the first motor 41 and nobody is caused to fly
The technological deficiency that row equipment is crashed；On the other hand, just also increase the first rotor 21 and the first motor 41 fastens therebetween
Relation ensure that the normal safe flight of flight equipment, have the characteristics that security performance is high；
3., the present invention pass through the second screw 432 by the first vibration damping sheet 439 and first by adding the first vibration damping sheet 439
It, to reduce vibrations of first rotor 21 compared with the first motor 41, is improved compared with fastening in flight course 21 upper surface of rotor
Safety and stability performance；
4., the present invention in rotor shaft 3 rotated by foldable assembly 5 compared with fuselage 1, realize rotor shaft 3 being capable of phase
For fuselage 1 be in open or indentation state, overcome in the prior art when flight equipment not flight operation, in
The first rotor 21 and/or rotor shaft 3 under open state not only occupy parking space, while also easily by the external world, other cargos touch
It damages, break, greatly shorten the service life of flight equipment (the first rotor 21), and then because the repair of the first rotor 21 is frequent
And bring the defects of maintenance cost is high；
5., the present invention by setting slide assemblies 6, when needing battery 7 being fixed in slide assemblies 6, only need downward
Elastic button 65 is pressed, protrusion 64 is opened, slide plate 624 is then outwards skidded off compared with sliding rack, battery 7 is fixed on slide plate
After on 624, compared with sliding rack slid inward slide plate 624, elastic button 65 is loosened, protrusion is close to battery 7 to be clamped, real
Firm installation of the battery 7 in unmanned flight's equipment flight course is showed, there is easy to operate, convenient disassembly.
Although preferred embodiments of the present invention have been described, but those skilled in the art once know basic creation
Property concept, then can make these embodiments other change and modification.So appended claims be intended to be construed to include it is excellent
It selects embodiment and falls into all change and modification of the scope of the invention.
Obviously, various changes and modifications can be made to the invention without departing from essence of the invention by those skilled in the art
God and scope.In this way, if these modifications and changes of the present invention belongs to the scope of the claims in the present invention and its equivalent technologies
Within, then the present invention is also intended to comprising including these modification and variations.
Claims (3)
1. a kind of unmanned flight's equipment, including fuselage, at least four first rotors, identical with the first rotor quantity second
Rotor, the rotor shaft identical with first rotor or the second rotor quantity；It is characterized in that, the unmanned flight sets
It is standby to further include：
First rotary connector identical with the first rotor quantity, first rotor pass through first rotation
Turn connector to be rotatably connected with a rotor shaft, first rotary connector includes：
First motor, first motor includes first surface and second surface, and first motor passes through first table
Face is fixed in the rotor shaft；The first surface is the upper surface of first motor, and the second surface is described
The lower surface of one motor；
First dismounting screw thread group, first rotor are rotatably connected by the described first dismounting screw thread group with the first surface,
So that by rotating the installation or removal between the first rotor realization first rotor and first motor；
Second rotary connector identical with the second rotor quantity, second rotor pass through second rotation
Turn connector to be rotatably connected with a rotor shaft, second rotary connector includes：
Second motor, second motor includes the 3rd surface and the 4th surface, and second motor passes through the 3rd table
Face is fixed in the rotor shaft；
Second dismounting screw thread group, second rotor are rotatably connected by the described second dismounting screw thread group with the 3rd surface,
So that by rotating the installation or removal between the second rotor realization second rotor and second motor；
The foldable assembly identical with the first rotor quantity or the second rotor quantity, a rotor shaft pass through one
A foldable assembly is rotationally fixed on the fuselage so that the rotor shaft can be opened or received compared with the fuselage
Contracting；
Slide assemblies, for disposing battery, and the slide assemblies are connected with the sliding machine body, with compared with the fuselage into
Row slides；
The first dismounting screw thread group includes：
First screw；
Second screw；
First screw buckle, the inner wall of first screw buckle is provided with the first internal thread, and the bottom of first screw buckle is opened
Equipped with the first screw hole so that first screw buckle is fixed on first table by first screw through first screw hole
On face；
First dismounting nut, the outer wall of the first dismounting nut is provided with the first external screw thread, and described first dismantles nut
Top offers the second screw hole so that second screw sequentially passes through first rotor, second screw hole by described
One dismounting nut is fixed on first rotor；
Wherein, first internal thread is adapted with first external screw thread, and passes through first internal thread and described first
Occlusion between external screw thread either the corresponding installation realized between first rotor and first motor of separation or is torn open
It unloads；Wherein, first rotor is installed therebetween compared with first motor by rotating clockwise realization, and described first
Rotor is dismantled therebetween compared with first motor by rotating realization counterclockwise, and the rotation of the first rotor described in during flight
Turn direction as direction of rotation counterclockwise；
The second dismounting screw thread group includes：
3rd screw；
4th screw；
Second screw buckle, the inner wall of second screw buckle is provided with the second internal thread, and the bottom of second screw buckle is opened
Equipped with the 3rd screw hole so that second screw buckle is fixed on the 3rd table by the 3rd screw through the 3rd screw hole
On face；
Second dismounting nut, the outer wall of the second dismounting nut is provided with the second external screw thread, and described second dismantles nut
Top offers the 4th screw hole so that the 4th screw sequentially passes through second rotor, the 3rd screw hole by described
Two dismounting nuts are fixed on second rotor；
Wherein, second internal thread is adapted with second external screw thread, and passes through second internal thread and described second
Occlusion between external screw thread either the corresponding installation realized between second rotor and second motor of separation or is torn open
It unloads；
The first dismounting screw thread group further includes：
Second vibration damping sheet offers the second through hole on second vibration damping sheet, and the 4th screw sequentially passes through described second
Described second dismounting nut is fixed on second rotor by through hole, second rotor and the 4th screw hole；
The foldable assembly includes：
Side plate part, the side plate part are fixed on the end of the rotor shaft；
Revolving part, the revolving part are fixed on the fuselage, and are rotatablely connected with the side plate part, make the side plate part and institute
It states rotatable between revolving part；
Locating part, the locating part are fixed on the side plate part, with the rotation to the revolving part compared with the side plate part
Angle is positioned：
The end of the rotor shaft includes first side and second side, and the first side and the second side are symmetrical
It is distributed in the end both sides of the rotor shaft；
The side plate part includes：
First side plate, first side plate are fixed in the first side；
Second side plate, second side plate are fixed in the second side；
Wherein, a sliding slot is offered on first side plate and first side plate, makes the locating part in the sliding slot
It is slided；
The locating part includes：
Fixed link, the fixed link are fixed between first side plate and second side plate, and respectively with first side
Plate and second side plate are perpendicular, and a slide opening is offered in the fixed link；
Gag lever post, the gag lever post are laterally disposed in the sliding slot so that gag lever post prolongs the axis of rotor shaft in the sliding slot
It is slided in direction；
Stayed mast, one end of the stayed mast are fixedly connected through the slide opening with the gag lever post so that by described in pulling
Stayed mast drives the gag lever post to be slided in the sliding slot；
The revolving part includes：
First puts ear, and the first swing hole is offered on the first pendulum ear；
Second puts ear, is offered on the second pendulum ear and described first swings the corresponding second swing hole in hole；
Fixed cylinder, one end of the fixed cylinder are fixed on the fuselage, the other end respectively with the described first pendulum ear and described the
Two pendulum ears are fixedly connected；
Rotation axis, the rotation axis sequentially pass through first side plate, described first swing hole, described second swing hole and described
The side plate part and the revolving part are rotatablely connected by the second side plate；
The first pendulum ear is provided with the first curvilinear portion, first curvilinear portion close to the one side of the gag lever post is corresponding
In arc-shaped, back to the gag lever post one side it is corresponding be provided with the first screens, first screens is L-shaped, described second
Pendulum ear is provided with the second curvilinear portion close to the one side of the gag lever post is corresponding, and second curvilinear portion is in arc-shaped, the back of the body
Corresponding to the one side of the gag lever post to be provided with the second screens, second screens is L-shaped；When the revolving part is compared with institute
When stating side plate part and being in 90 ° of angles, the gag lever post slides into the cunning in the sliding slot under the action of the stayed mast
The rightmost of slot, the gag lever post are in contact with first curvilinear portion and second curvilinear portion；When revolving part is opposite
When the side plate part is in 0 ° of angle, the gag lever post is in the sliding slot to the sliding slot under the action of the stayed mast
The left side slide, first curvilinear portion and second curvilinear portion are completely in the lower section of the gag lever post, the limit
Position bar drops down onto first screens and second screens carries out /V.
2. unmanned flight's equipment as described in claim 1, which is characterized in that the first dismounting screw thread group further includes：
First vibration damping sheet offers first through hole on first vibration damping sheet, and second screw sequentially passes through described first
Described first dismounting nut is fixed on first rotor by through hole, first rotor and the second screw hole.
3. unmanned flight's equipment as described in claim 1, which is characterized in that the slide assemblies include：
Fixed seat, the fixed seat are fixed on the fuselage；
Sliding rack, the inside of the sliding rack is in hollow-core construction, and for disposing battery, and the sliding rack is slidably fixed on institute
It states in fixed seat；
Buckle, described be buckled are fixed on the end of the fixed seat, and a protrusion is provided on the buckle, with by described convex
It rises and stops that the battery is skidded off from the sliding rack.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510861047.1A CN105366042B (en) | 2015-11-30 | 2015-11-30 | Unmanned flight's equipment |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510861047.1A CN105366042B (en) | 2015-11-30 | 2015-11-30 | Unmanned flight's equipment |
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| CN105366042A CN105366042A (en) | 2016-03-02 |
| CN105366042B true CN105366042B (en) | 2018-05-25 |
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Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8973861B2 (en) * | 2012-10-29 | 2015-03-10 | Shenzhen Hubsan Technology Co., Ltd. | Tetra-propeller aircraft |
| CN103350752A (en) * | 2012-10-29 | 2013-10-16 | 深圳市哈博森科技有限公司 | Four-rotor aircraft |
| CN203681871U (en) * | 2013-12-20 | 2014-07-02 | 深圳市大疆创新科技有限公司 | Engine arm assembly and stander device of aircraft and aircraft |
| CN104590556B (en) * | 2014-10-31 | 2017-06-27 | 易瓦特科技股份公司 | A kind of folding unmanned plane |
| CN204279915U (en) * | 2014-10-31 | 2015-04-22 | 深圳一电科技有限公司 | Rotor craft |
| CN204548479U (en) * | 2015-03-24 | 2015-08-12 | 陈灵峰 | A kind of folded piece of Multi-axis aircraft |
| CN204507263U (en) * | 2015-04-08 | 2015-07-29 | 辽宁力德航空科技有限公司 | Unmanned plane mounting structure for propeller |
| CN204674818U (en) * | 2015-04-17 | 2015-09-30 | 巴州极飞农业航空科技有限公司 | A kind of screw propeller permanent seat |
| CN205345329U (en) * | 2015-11-30 | 2016-06-29 | 湖北易瓦特科技股份有限公司 | Unmanned aerial vehicle equipment |
-
2015
- 2015-11-30 CN CN201510861047.1A patent/CN105366042B/en not_active Expired - Fee Related
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|---|---|
| CN105366042A (en) | 2016-03-02 |
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