CN106428509A - Propeller arm structure of unmanned aircraft and unmanned aircraft - Google Patents
Propeller arm structure of unmanned aircraft and unmanned aircraft Download PDFInfo
- Publication number
- CN106428509A CN106428509A CN201610740295.5A CN201610740295A CN106428509A CN 106428509 A CN106428509 A CN 106428509A CN 201610740295 A CN201610740295 A CN 201610740295A CN 106428509 A CN106428509 A CN 106428509A
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- paddle arm
- unmanned plane
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- segment
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- 238000010276 construction Methods 0.000 claims description 7
- 238000009434 installation Methods 0.000 description 12
- 238000005183 dynamical system Methods 0.000 description 10
- 230000013011 mating Effects 0.000 description 7
- 230000000007 visual effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000001737 promoting effect Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000000151 deposition Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 208000020442 loss of weight Diseases 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000010009 beating Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 210000002421 cell wall Anatomy 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007937 lozenge Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention discloses a propeller arm structure of an unmanned aircraft and the unmanned aircraft. The propeller arm structure of the unmanned aircraft comprises a first section propeller arm connected with a fuselage of the unmanned aircraft, and a second section propeller arm far away from the fuselage of the unmanned aircraft, wherein the first section propeller arm and the second section propeller arm are connected in a detachable manner; a first wire electrically connected with a main control panel of the unmanned aircraft is arranged in the first section propeller arm; a second wire connected with the first wire is arranged in the second section propeller arm; and an electromagnetic shielding member is arranged at the connection position of the first wire and the second wire. According to the propeller arm structure disclosed by the technical scheme of the invention, through the adoption of the electromagnetic shielding member, electromagnetic shielding is performed at the connection position of the first wire and the second wire, so that the influence on a power system due to electromagnetic interference at the connection position of the first wire and the second wire can be avoided.
Description
Technical field
The present invention relates to unmanned vehicle technical field, the paddle arm structure particularly to a kind of unmanned plane and unmanned plane.
Background technology
For the paddle arm structure of unmanned plane, now in order that depositing and convenient transportation of unmanned plane, typically this paddle arm is tied
Structure is divided into two parts, and a part is the first paragraph paddle arm being connected with the casing of unmanned plane, and another part is away from unmanned plane
The second segment paddle arm of casing.But, because second segment paddle arm needs to install motor, the wire of motor needs to connect with the wire of master control borad
Connect, because the control of the dynamical system (namely motor) to unmanned plane requires very precisely, therefore, general wire adopts anti-shielding
Wire, but electromagnetic shielding cannot be accomplished in the junction of two wires.
Content of the invention
The main object of the present invention is to provide a kind of paddle arm structure of unmanned plane it is intended to connecting position of wires is carried out electromagnetic shielding.
For achieving the above object, the present invention provides a kind of paddle arm structure of unmanned plane, including the fuselage with described unmanned plane
The first paragraph paddle arm connecting and the second segment paddle arm of the fuselage away from described unmanned plane, described first paragraph paddle arm and described second segment
Paddle arm is detachably connected；
It is provided with the first wire with the master control borad electric connection of described unmanned plane, described second segment in described first paragraph paddle arm
It is provided with the second wire being connected with described first wire, the junction of described first wire and described second wire is provided with paddle arm
Electromagnetic shield.
Alternatively, the paddle arm structure of this unmanned plane also includes paddle arm linkage section, the company of described first wire and the second wire
Meet place to be located in this paddle arm linkage section, described paddle arm linkage section has the first end being oppositely arranged and the second end, this first end is even
It is connected to described first paragraph paddle arm, this second end is connected to described second segment paddle arm.
Alternatively, the second end of described paddle arm linkage section is provided with accommodating chamber, and described electromagnetic shield is fixedly installed in described
In accommodating chamber.
Alternatively, it is provided with junction block in described accommodating chamber, described junction block is used for connecting the first wire and the second wire,
Described junction block stretches into and is additionally provided with described electromagnetic shield near the side of first end.
Alternatively, it is provided with dividing plate between described first end and the second end, described accommodating chamber is separated to form two parts, institute
Stating dividing plate middle setting has square perforation, for installing described junction block.
Alternatively, described junction block includes main board and the connecting cylinder on main board, described main board fixed installation
In described accommodating chamber, the junction of described first wire and the second wire is placed in this connecting cylinder.
Alternatively, the junction of described first paragraph paddle arm and described second segment paddle arm be provided with buckle or button bit wherein it
One, the junction of described second segment paddle arm and described first paragraph paddle arm is provided with wherein another, the described buckle of buckle or button bit
Fasten with described button bit, described first paragraph paddle arm is detachably fixed with described second segment paddle arm and is connected.
Alternatively, the section of described first paragraph paddle arm is triangular in shape, and the section of described second segment paddle arm is also triangular in shape, institute
That states that the side wall of accommodating chamber surrounds is shaped as cross, and the construction section in described second segment paddle arm is also in that cross is arranged, described
The side wall of accommodating chamber is inserted in described construction section.
Alternatively, the outside wall surface of the cavity wall of described accommodating chamber is provided with locating slot, and described locating slot is from described paddle arm linkage section
The second end extend to first end, to should be provided with locating piece by locating slot, described locating piece grafting houses described second segment paddle arm
In this locating slot.
The present invention also provides a kind of unmanned plane, including the paddle arm structure of unmanned plane, connects including the fuselage with described unmanned plane
The first paragraph paddle arm connecing and the second segment paddle arm of the fuselage away from described unmanned plane, described first paragraph paddle arm and described second segment oar
Arm is detachably connected；
It is provided with the first wire with the master control borad electric connection of described unmanned plane, described second segment in described first paragraph paddle arm
It is provided with the second wire being connected with described first wire, the junction of described first wire and described second wire is provided with paddle arm
Electromagnetic shield.
The junction of the first wire and the second wire, by adopting electromagnetic shield, can be carried out electricity by technical solution of the present invention
Magnetic screen, prevents the first wire and the junction of the second wire to be subject to electromagnetic interference to have influence on dynamical system.
Brief description
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
Have technology description in required use accompanying drawing be briefly described it should be apparent that, drawings in the following description be only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, acceptable
Structure according to these accompanying drawings obtains other accompanying drawings.
Fig. 1 is the structural representation of unmanned plane one embodiment of the present invention；
Fig. 2 is the structural representation at another visual angle of unmanned plane in Fig. 1；
Fig. 3 is the part-structure schematic diagram of unmanned plane in Fig. 1；
Fig. 4 is the sectional view in Fig. 3 along line A-A；
Fig. 5 is the enlarged drawing at A in Fig. 4；
Fig. 6 is the structural representation of battery box structure one embodiment of unmanned plane of the present invention；
Fig. 7 is the structural representation of battery compartment in Fig. 6；
Fig. 8 is the structural representation of latch components in Fig. 6；
Fig. 9 is the sectional view at another visual angle of latch components in Fig. 8；
Figure 10 is the part-structure schematic diagram of paddle arm structure one embodiment of unmanned plane of the present invention；
Figure 11 is the structural representation of paddle arm linkage section in Figure 10；
Figure 12 is the top view of paddle arm linkage section in Figure 10；
Figure 13 is the part-structure schematic diagram of hanger one embodiment of unmanned plane of the present invention；
Figure 14 is the cross-sectional schematic at a visual angle of hanger of unmanned plane in Figure 13；
Figure 15 is the structural representation of the middle hanger and position limiting structure of hanger of unmanned plane in Figure 13；
Figure 16 is the cross-sectional schematic at middle hanger and position limiting structure the visual angle in Figure 15；
Figure 17 is the structural representation of the lower hanger of hanger of unmanned plane in Figure 13；
Figure 18 is the structural representation of the position limiting structure of hanger of unmanned plane in Figure 13.
Drawing reference numeral explanation：
The realization of the object of the invention, functional characteristics and advantage will be described further in conjunction with the embodiments referring to the drawings.
Specific embodiment
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 carried out clear, complete
Site preparation describes 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, those of ordinary skill in the art are not making
The every other embodiment being obtained under the premise of creative work, broadly falls into the scope of protection of the invention.
It is to be appreciated that the directional instruction (such as up, down, left, right, before and after ...) of institute is only used in the embodiment of the present invention
In explaining the relative position relation between each part, motion conditions etc. under a certain particular pose (as shown in drawings), if should
When particular pose changes, then directionality instruction also correspondingly changes therewith.
In addition, the description being related to " first ", " second " etc. in the present invention is only used for describing purpose, and it is not intended that referring to
Show or imply its relative importance or the implicit quantity indicating indicated technical characteristic.Thus, define " first ", "
Two " feature can be expressed or implicitly include at least one this feature.In addition, the technical scheme between each embodiment can
To be combined with each other, but must be capable of by those of ordinary skill in the art based on, when the combination of technical scheme occurs
Conflicting or will be understood that the combination of this technical scheme does not exist, also not in the protection model of application claims when cannot realize
Within enclosing.
The present invention proposes a kind of unmanned plane 100.
Referring to figs. 1 to Fig. 3, this unmanned plane 100 includes fuselage 10, at least one horn being arranged on fuselage 10 and sets
It is placed in dynamical system and the screw of horn one end, described dynamical system is generally motor, and screw is connected to the rotating shaft of motor,
Motor drive propeller rotational, thus provide, for unmanned plane, the lift taking off.Described horn is the structure of hollow, sets inside horn
There is wire, be that dynamical system is powered.In order to prevent being interfered of dynamical system, it is further provided with paddle arm structure 20, this oar
Arm configuration 20 includes first paragraph paddle arm 21 and the machine away from described unmanned plane 100 being connected with the fuselage 10 of described unmanned plane 100
The second segment paddle arm 22 of body 10.This first paragraph paddle arm 21 is general and fuselage 10 integrated molding is arranged, by fuselage 10 main part
Extend and formed.Second segment paddle arm 22 and first paragraph paddle arm 21 are detachably connected to facilitate installation and to carry unmanned plane 100.Transport and
When depositing, first paragraph paddle arm 21 and second segment paddle arm 22 are taken apart with save space.During use, by first paragraph paddle arm 21 and second
Section paddle arm 22 is fixedly connected.It is provided with described first paragraph paddle arm 21 and be electrically connected with the master control borad 11 of described unmanned plane 100
The first wire (not shown), be provided with the second wire being connected with described first wire in described second segment paddle arm 22 and (do not scheme
Show), the power supply to dynamical system is realized by the first wire and the second wire.
The junction of described first wire and described second wire is provided with electromagnetic shield 27.
So, by electromagnetic shield 27, the junction of the first wire and the second wire can be formed electromagnetic shielding, prevent
Electromagnetic interference and affect dynamical system.
Specifically, this paddle arm structure 20 also includes paddle arm linkage section 26, the junction of described first wire and the second wire
In this paddle arm linkage section 26, described paddle arm linkage section 26 has the first end 261 being oppositely arranged and the second end 262, and this
One end 261 is connected to first paragraph paddle arm 21, and this second end 262 is connected to second segment paddle arm 22.Described first paragraph paddle arm 21 section
Substantially triangularity, the inwall setting of horn is close at described second end 262, and therefore, described second end 262 is also substantially triangle
Structure.Certainly, this paddle arm linkage section 26 can be integrally formed with first paragraph paddle arm 21.
With reference to Figure 11, the second end 262 of paddle arm linkage section 26 is provided with accommodating chamber 211, the fixing peace of described electromagnetic shield 27
It is loaded in described accommodating chamber 211.
Specifically, the second end 262 of paddle arm linkage section 26 generally " ten " word structure, is provided with described accommodating chamber 211
Junction block 23, described junction block 23 is used for connecting the first wire and the second wire, and described junction block 23 stretches near first end 261
Side be additionally provided with described electromagnetic shield 27.The wire being somebody's turn to do i.e. fuselage interior connects to junction block 23, then by junction block 23
It is connected to the wire of dynamical system.
General, it is provided with dividing plate 211a between described first end 261 and the second end 262, described accommodating chamber 211 is separated
Form two parts, described dividing plate 211a middle setting has square perforation (sign), for installing described junction block 23.For this
Junction block 23, in the present embodiment, the shape adopting and set-up mode are：With reference to Figure 11, described junction block 23 includes main board 231
With the connecting cylinder 232 on main board 231, main board 231 is fixedly installed in described accommodating chamber 211, described first wire and
The junction of the second wire is placed in this connecting cylinder 232.
General, electromagnetic shield 27 is shielding button, and this shielding button 27 is substantially square, and the square of described dividing plate leads to
Hole interference fit.
The quantity of this connecting cylinder 232 is typically based on the quantity set connecting plug, such as adopts 4 connecting cylinders in the present embodiment
232.The general shape adaptation with accommodating cavity 411 of the shape of this main board 231, is also in substantially cross setting.
This junction block 23, can be with bolts, as described main board 231 is secured by bolts in dividing plate 211a.Also may be used
Using snapping connection, all within the scope of the present invention.
Mount and dismount described first paragraph paddle arm 21 and described second segment paddle arm 22 for convenience, with reference to Figure 10, described the
The junction of one section of paddle arm 21 and described second segment paddle arm 22 is provided with one of them of buckle 24 or button bit 25, described second segment oar
The junction of arm 22 and described first paragraph paddle arm 21 is provided with the wherein another of buckle 24 or button bit 25, described buckle 24 and described button
Position 25 fastening, described first paragraph paddle arm 21 is detachably fixed with described second segment paddle arm 22 and is connected.
Concretely, described buckle 24 one end hinged with first paragraph paddle arm 21, the other end is provided with the first grab 241, institute
State the first grab 241 to extend and to the bending extension of second segment paddle arm 22 direction so that the first grab 241 is in circular arc from buckle 24
Shape, described first grab 241 stretches in button bit 25, completes being connected of first paragraph paddle arm 21 and second segment paddle arm 22.So,
Make the installation and removal of first paragraph paddle arm 21 and second segment paddle arm 22 more convenient by the cooperation of buckle 24 and button bit 25.
It is understood that the setting of buckle 24 and button bit 25 is one-to-one, the quantity of its setting is also dependent on reality
Depending on the situation of border, as being provided at circumferentially spaced 3 buckles 24 or button along described first paragraph paddle arm 21 or described second segment paddle arm 22
Position 25.
In order to prevent first paragraph paddle arm 21 and second segment paddle arm 22 from rotating against, the section generally three of first paragraph paddle arm 21
Angular, the section of second segment paddle arm 22 is also also substantially triangular structure.
Further, with reference to Figure 10 and Figure 11, what the side wall of described accommodating chamber 211 surrounded is shaped as cross, and described the
Construction section in two sections of paddle arm 22 is also in that cross is arranged, and the side wall of described accommodating chamber 211 is inserted into described construction section (does not scheme
Show) in.
That is, described second end 262 substantially be in cross, including the first cross end, the second cross end, the 3rd cross end and
4th cross end, described first cross end and described 3rd cross end are oppositely arranged, described second cross end and the described 40th
Word end is oppositely arranged, and in order to coordinate the structure of described horn, the section at described second cross end and the 4th cross end is in substantially ladder
Shape structure.
Further, the outside wall surface of the cavity wall of described accommodating chamber 211 is provided with locating slot 212, and described locating slot 212 is from described
Second end 262 of paddle arm linkage section 26 extends to first end 261, described second segment paddle arm 22 to should locating slot 212 be provided with fixed
Position block (not shown), described locating piece grafting is placed in this locating slot 212.So, in location and installation first paragraph paddle arm 21 He
During second segment paddle arm 22, described locating slot 212 can play initial alignment effect, can play guiding simultaneously when mounted and make
With.
The present invention arranges paddle arm structure 20, connects first paragraph paddle arm 21 and second segment paddle arm 22 by paddle arm linkage section 26,
Make unmanned plane 100 easy dissembling and-assembling.Meanwhile, setting junction block 23 and electromagnetic shield 27 in this paddle arm linkage section 26
(shielding button), reduces the interference to dynamical system power line, decreases flight safety hidden danger, is also beneficial to shielding button 27 simultaneously
Modification and adjustment, additionally, by the fixation of buckle 24, the first grab 241 and button bit 25, the cross structure at the second end 262 is solid
Fixed, and the triple fixations between locating slot 212 and locating piece are so that first paragraph paddle arm 21 and second segment paddle arm 22 firmly connect
Connect.
With reference to Fig. 1, Figure 13 and Figure 14, the lower end of this fuselage 10 is provided with hanger 30, and this hanger 30 is used for suspended item, makes
Unmanned plane 100 being capable of suspended item.
The hanger 30 of this unmanned plane 100 includes upper hanger 31, the mounting article being fixedly connected with the fuselage 10 of unmanned plane 100
Lower hanger 35, and the middle hanger 33 connecting described upper hanger 31 and described lower hanger 35；
Upper hanger 31 is typically provided with stud, is fixed by the fuselage of bolt and unmanned plane, certainly can also pass through buckle
Or other connected modes are attached.
Described lower hanger 35 is provided with spacing hole 351, and in this, hanger 33 is provided with up and down motion in this spacing hole 351
Position limiting structure 37, when this position limiting structure 37 part is placed in this spacing hole 351, in this, hanger 33 and lower hanger 35 are in horizontal direction
Mutually spacing；
Described middle hanger 33 extends downwardly and is provided with shackle member 331, and described lower hanger 35 is provided with slip draw-in groove 353, this cunning
It is provided with mounting position 353c, this shackle member 331 is slided to depart from or to be mounted in described slip draw-in groove 353 in dynamic draw-in groove 353
Mounting position 353c.
When preparing using unmanned plane 100 transport article, first article to be transported are connected (this thing to be transported with lower hanger 35
Some devices that product can have in itself for unmanned plane 100, such as delivery device, or other airborne device is naturally it is also possible to be to treat
Parcel of transport etc.), then play the shackle member 331 of hanger 35 to be mounted on the mounting position 353c in slip draw-in groove 353, so that in
Hanger 33 and lower hanger 35 are in the spacing fixation of above-below direction.Meanwhile, position limiting structure 37 part is contained in spacing hole 351, with this
The hole wall of spacing hole 351 abut spacing so that in this hanger 33 and lower hanger 35 fix in horizontal direction upper limit.So, make
Obtain article to be transported and be fixed on unmanned plane 100.When unmanned plane 100 transport article are to destination, first position limiting structure 37 is departed from
Go out spacing hole 351, then promote lower hanger 35, so that shackle member 331 is slided in slip draw-in groove 353, thus departing from mounting position
353c, hanger 33 during lower hanger 35 is departed from, and then article are taken off.The hanger 30 being arranged such, facilitates unmanned plane 100 quick
Mounting and dismounting article, Lifting Convey efficiency, Lifting Convey efficiency.
General, incorporated by reference to Figure 15, in order to mitigate the weight of hanger 30, upper hanger 31, middle hanger 33 and lower hanger 35 are equal
It is provided with lightening hole (sign) so that upper hanger 31, middle hanger 33 and lower hanger 35 are in grid-like setting.Middle hanger 33 is downward
Projection the second grab 331 is to form shackle member 331.This second grab 331 is located at the downside of the grille strip of middle hanger 33, typically sets
It is equipped with four the second grabs 331, hanger is substantially square and arranges.Four the second grabs 331 are located at four of middle hanger 33
End angle.The typically L-shaped setting of second grab 331.
Incorporated by reference to Figure 17, the slip draw-in groove 353 of lower hanger 35 setting is included lead segment 353a and is connected with this lead segment 353a
Clamping section 353b connecing, described mounting position 353c is located at described clamping section 353b.Shackle member 331 slides in lead segment 353a
Clamping section 353b clamping.It is provided with card adapter plate 353c, this card adapter plate 353c is positioned at clamping section 353b shape in this slip draw-in groove 353
Become mounting position 353c, the second grab 331 is connected in this card adapter plate 353c.This slip draw-in groove 353 is generally bottle shape, its large aperture
Section forms lead segment 353a, and small-bore section forms clamping section 353b, and card adapter plate 353c, located at this small-bore section, is generally located on cunning
The cell wall upper end of dynamic draw-in groove 353.
In the present embodiment, in conjunction with Figure 15 to Figure 18, this position limiting structure 37 includes mounting box 371, typically this mounting box 371
Fastened by upper cover plate and lower cover and form.
This mounting box 371 is provided with impeller 373 and ejection piece 375, and impeller 373 is partially housed in this mounting box 371
In, and move back and forth in this mounting box 371, described ejection piece 375 is installed in described mounting box 371, this mounting box 371
Base plate is provided with the resigning hole 371a passing through for described ejection piece 375, and this resigning hole 371a is just arranged to spacing hole 351；Promote
Part 373 is abutted with ejection piece 375, to promote described ejection piece 375 upper and lower in described spacing hole 351 through resigning hole 371a
Motion.
When ejection piece 375 is located in spacing hole 351, ejection piece 375 engages with the hole wall of spacing hole 351 so that lower extension
Frame 35 is mutually spacing in horizontal direction with middle hanger 33.When impeller 373 promotes ejection piece 375, ejection piece 375 is retracted into
In mounting box 371, between lower hanger 35 and middle hanger 33 in horizontal direction not limited location, now, only need in the horizontal direction
Upper card adapter plate 353c promoting lower hanger 35, making in the second grab 331 disengaging slip draw-in groove 353 of lower hanger 35, you can take out
Lower hanger 35 is so that the dismounting of lower hanger 35 is more convenient.
With reference to Figure 18, this impeller 373 includes catch bar 3731 and the pushing block located at described catch bar 3731 one end
3732, this wedge shaped setting of pushing block 3732, described ejection piece 375 has in the mating holes 3751 of this pushing block 3732 cooperation,
The lozenges of pushing block 3732 supports the hole wall of mating holes 3751, this pushing block 3732 in horizontal motion, to promote ejection
Part 375 moves up and down.The height of pushing block 3732 near catch bar 3731 one end to the one end away from catch bar 3731 by
Gradually reduce, ejection piece 375 is located at one end away from catch bar 3731 of pushing block 3732, and the lower end of ejection piece 375 stretches to limit
In the hole 351 of position.Therefore, when promoting in catch bar 3731 is towards mounting box 371, the height of wedge 3732 gradually rises, wedge
The upper hole wall of mating holes 3751 is supported in shape face so that ejection piece 375 moves upwards and makes its lower end depart from spacing hole 351, thus
Make position limiting structure 37 no longer spacing middle hanger 33 and lower hanger 35 in horizontal direction.By the setting of wedge 3732, make
Obtain the relatively simple convenience of cooperation of catch bar 3731 and ejection piece 375.This ejection piece 375 be typically square tabular setting, ejection
Mating holes 3751 in part 375 is also square setting.
This catch bar 3731 is additionally provided with the first clamp 3733, and the height that this first clamp 3733 is located at pushing block 3732 is higher
One end, and ejection piece 375 clamping, in case the higher one end of thrust motion block 3732 is slipped in mating holes 3751.
General, the medial recess of this pushing block 3732 forms chute 3732a, and the hole wall of this mating holes 3751 upper end is downward
Extend and be provided with the second clamp 3752, this second clamp 3752 slides in this chute 3732a, and the end wall with this chute 3732a
Abut spacing.It is arranged such, be slipped in mating holes 3751 also for preventing the higher one end of pushing block 3732.
One end being provided with pushing block 3732 of this catch bar 3731 is additionally provided with the first elastic component 376, this first elastic component 376
The side wall of two ends and mounting box 371 and the end elasticity of pushing block 3732 abuts, with extension in promoting catch bar 3731 to complete
After frame 33 and the separation of lower hanger 35, realize the elastic reset of catch bar 3731.The upper end of this ejection piece 375 is provided with the second elastic component
377, the two ends of this second elastic component 377 are abutted with the roof of mounting box 371 and the upper end elasticity of ejection piece 375, to promote
After catch bar 3731 completes middle hanger 33 and the separation of lower hanger 35, realize the elastic reset of ejection piece 375.This first elastic component
376 and second elastic component 377 all can adopt spring, it is, of course, also possible to using other elastic constructions such as jump ring etc..
With reference to Figure 18, in order that the elastic compression of the first elastic component 376 and the second elastic component 377 and reply are more firm,
The end of this catch bar 3731 is additionally provided with the first locating dowel 376a, and this first elastic component 376 is sheathed on this first locating dowel 376a.
Accordingly, the upper end of this ejection piece 375 is additionally provided with the second locating dowel (sign), this second elastic component 377 be sheathed on this second
Locating dowel.
The upper end of ejection piece 375 is arranged with slot to make way, and this second locating dowel is installed in this slot to make way, so that this top
The structure going out part 375 is simple, and installation and operation is all more firm.
The base plate of this mounting box 371 is also convexly equipped with two slide units 378, and slide unit 378 described in two is located at the both sides of resigning hole 371a,
Wherein described in one, the both sides of slide unit 378 are convexly equipped with baffle plate 378a, form slideway, impeller 373 is in this cunning between two baffle plate 378a
Slide in road.It is made to slide more steady, cooperation is more firm.
It is provided with master control borad 11, power panel 12 and battery box structure 40 and various functions element in this fuselage 10.Described machine
It is provided with median septum 13, septum plate 13 is divided into the first accommodating cavity and the second accommodating cavity, institute by described fuselage 10 in body 10
State the master control borad 11 of unmanned plane 100, power panel 12 is arranged in the first accommodating cavity, certainly, is additionally provided with other in the first accommodating cavity
Components and parts.The battery box structure 40 of described unmanned plane 100 is arranged in the second accommodating cavity.First accommodating cavity is normally at fuselage 10
Top, the second accommodating cavity be located at fuselage 10 bottom.By the setting of median septum 13 so that the installation of fuselage 10 inner part relatively
For orderly and convenience.
Further, with reference to Fig. 4, it is provided between described master control borad 11 and described power panel 12 and is connected socket 14.So, lead to
Cross this connection socket 14, the inside winding displacement of unmanned plane 100 can be reduced, facilitate the cabling layout in fuselage 10.
With reference to Fig. 2, unmanned plane 100 is generally provided with radio antenna 50 and high definition antenna 60, radio antenna 50 and high definition
The lower end of the general fuselage 10 located at unmanned plane 100 of antenna 60 is received and transmission signal and data with facilitating.
The mounting means of this radio antenna 50 is：With reference to Fig. 2, described unmanned plane 100 includes radio antenna 50, described unmanned
The fuselage 10 of machine 100 is provided with antenna mounting post 51, and one end deviating from described fuselage 10 of described antenna mounting post 51 is provided with installation
Hole (does not indicate), and this installation in the hole is provided with rubber stop collar 52, and the grafting of described radio antenna 50 is limited in described rubber stop collar
In 52.So, radio antenna 50 can be prevented to be retracted into the fuselage of unmanned plane 100 during installing by rubber stop collar 52
So that the signal reception of radio antenna 50 is unaffected in 10.
The mounting means of this high definition antenna 60 is：With reference to Fig. 2, described unmanned plane 100 includes high definition antenna 60, described unmanned
The fuselage 10 of machine 100 is provided with the installing port 61 that the cable for this high definition antenna 60 passes through, the cable of described high definition antenna 60
Through this installing port 61, described high definition antenna 60 is provided with installing plate 62, and this installing plate 62 is fixedly installed in described unmanned plane 100
Fuselage 10.General, this installing plate 62 is fixedly connected using screw.By arranging installing plate 62 so that this high definition electric wire
It is fixedly connected with the fuselage 10 of unmanned plane 100.The installing port 61 preventing from repeatedly dismantling high definition antenna 60 and leading to becomes big problem.
For unmanned plane 100, the power supply of unmanned plane 100 be have impact on the endurance of unmanned plane 100, in setting no
During man-machine 100 battery box structure 40, the fast assembling-disassembling of battery compartment 41 typically to be considered, do not had with the battery in unmanned plane 100
Service efficiency can be improved with quick-replaceable when electric.Therefore, the present invention provides a kind of battery box structure of new unmanned plane 100
40, with reference to Fig. 4 to Fig. 9, including battery compartment 41 and latch components 42, described battery compartment 41 is installed on the machine of described unmanned plane 100
In body 10, described latch components 42 are installed on the side of described battery compartment 41, and described battery compartment is fixed by described latch components 42
In fuselage；
Described latch components 42 include locking part 421 and lock core 422, and described locking part 421 is fixedly installed in described battery
Storehouse 41, described lock core 422 is partially housed in described locking part 421, and at least partly exposes described locking part 421, described lock core
422 move back and forth in described locking part 421 and make described lock core 422 have locking state and disassembly status, described lock core 422
When being in locking state, the spacing fixation of fuselage 10 of one end of this lock core 422 and described unmanned plane 100.
Technical solution of the present invention passes through the battery box structure 40 using unmanned plane 100, when unmanned plane 100 uses, makes lock
One end motion of core 422 manifests locking part 421, and makes this lock core 422 be in locking state, one end of this lock core 422 and machine
The abutting of body 10, and by the spacing fixation of fuselage 10 of this latch components 42 and unmanned plane 100 so that this battery compartment 40 is fixed on no
In man-machine 100 fuselage 10.When needing to dismantle battery compartment 41, only this lock core 422 retraction need to be made at it to locking part 421
In disassembly status, and depart from the fuselage 10 of unmanned plane 100, then battery compartment 42 is extracted out.So, the installation of battery compartment 42
All more convenient with dismantling.
When understandable, this lock core 422 moves back and forth in locking part 421, can adopt various ways, e.g., locking
The internal setting slide rail of part 421, this slide rail has tooth bar, and the side of lock core 422 also has in the tooth bar of this tooth bar engagement, passes through
The mode of rack-driving makes lock core 422 move back and forth in locking part 421.It is, of course, also possible to by the way of spring 423,
Specifically：
Described latch components 42 also include spring 423, and described spring 423 is contained in described locking part 421, and two ends are divided
Do not abut described locking part 421 and described lock core 422.
Described lock core 422 includes main part 4221 and the handle portion 4222 being convexly equipped in described main part 4221 side, this lock
The first resigning mouth 4211a that one end that firmware 421 is provided with for main part 4221 passes through and back and forth transporting for described handle portion 4222
The first dynamic elongated hole 4212a.This main part 4221 passes through one end formation Plug Division 4221a of described first resigning mouth 4211a.
Described main part 4221 moves back and forth in described locking part 421 and makes described lock core 422 have locking state and disassembly status,
When described lock core 422 is in locking state, this Plug Division 4221a passes through described first resigning mouth 4211a, with described unmanned plane
The 100 spacing fixation of fuselage 10.
Specifically, described locking part 421 is locking cylinder, described spring is contained in described locking cylinder 421, described lock core
422 are partially housed in described locking cylinder 421, and at least partly expose described locking cylinder 421.General, described locking cylinder 421 is
The hollow cylindrical of one end open.
Specifically, described lock core 422 includes first end 422a located at described main part 4221 two ends and the second end relatively
422b, is substantially cylindric, and described first end 422a diameter is equal to or slightly less than the internal diameter of described locking cylinder 421, and described the
The intersection of one end 422a and the second end 422b forms flanged structure 422c, and described spring 423 two ends abut convex with described respectively
Edge structure and the bottom of described locking cylinder 421.
The length of the second end 422b of this lock core 422 can be arranged according to actual conditions, such as in the present embodiment, described locking
Cylinder 421 and lower end wall are provided with lower outlet, the second end 422b of described lock core 422 stretching motion in described lower outlet.
General, this second end 422b diameter is equal to or slightly less than the diameter of described lower outlet, can be applied in lock core 422
External force used under in described lower outlet in stretching motion.
Certainly, in another embodiment, it is not provided with lower outlet, and the height of the second end 422b is shortened it is also possible to complete
The locking state of lock core 422 and the conversion of disassembly status.
General, the Plug Division 4221a that this first end 422a is formed is plugged in the median septum 13 of fuselage 10.This battery compartment 41
For rectangle box body, the second accommodating cavity is to the shape of battery compartment 41 should making adaptive adjustment setting.This second accommodating cavity
Interior general setting slide rail (sign), battery compartment 41 coordinates the motion of plug type in this second accommodating cavity with this slide rail.?
When unmanned plane 100 uses, this lock core 422 is in locking state, by the spacing fixation of Plug Division 4221a and fuselage 10 so that
This battery compartment 41 is fixed in this second accommodating cavity.It is appreciated that the corresponding described Plug Division 4221a of septum plate 13 is provided with admittedly
Determine hole, can be specifically, septum plate 13 is provided with some lightening holes, described Plug Division 4221a passes through one of loss of weight
Hole, when described Plug Division 4221a is plugged in one of loss of weight in the hole, described latch components 42 are in locking state, when need
Dismantle, only need to press handle portion 4222, when described handle portion 4222 is applied with the power along locking cylinder 421 axis direction, described
Lock core 422 moves under the drive of described handle portion 4222, so that the second end 422b of lock core 422 skids off lower outlet.So that
This handle portion 4222 moves downward in the first elongated hole 4212a, drives the second end 422a compression spring of main part 4221
423 so that Plug Division 4221a is departed from fuselage 10, then battery compartment 41 is extracted out.
For the installation settings of latch components 42, this latch components 42 can be provided separately within the side of this battery compartment 41
Wall, is such as arranged on the lateral wall of one end of its length direction, in the present invention, for easy for installation and saving installing space, should
Latch components 42 are integrally disposed in battery compartment 41.
Specifically, with reference to Fig. 6 to Fig. 9, being provided with and described first resigning mouth 4211a corresponding second of described battery compartment 41
Resigning mouth 41a second elongated hole 41b corresponding with described first elongated hole 4212a.So, latch components 42 are arranged on electricity
In pond storehouse 41, handle portion 4222 sequentially passes through the first elongated hole 4212a and the second elongated hole 41b and manages for user.Grafting
Portion 4221a sequentially passes through the first resigning mouth 4211a and the second resigning mouth 41a, and the spacing fixation of fuselage 10 with unmanned plane 100.
Further, in order that being more firmly mounted and stable, with reference to Fig. 7 to 9, described locking part of latch components 42
421 are provided with locking board 424, and the side wall being provided with described second resigning mouth 41a of described battery compartment 41 is arranged with mounting groove 411, institute
State locking board 424 to be fixedly installed in described mounting groove 411, described first resigning mouth 4211a is located at the bottom of described mounting groove 411
Wall.
General, described locking board 424 above described battery compartment 41, for example, it may be, described battery compartment 41 top
Concave downward is formed with the mounting groove 411 accommodating described locking board 424, the shape of described mounting groove 411 and described locking board 424
Shape be adapted.Optionally, described locking board 424 is fixed on described battery compartment 41 top, now, described locking by screw
Some through holes are provided with plate 424, described battery compartment 41 is provided with screwed hole, and some screws are fixed on screwed hole through some through holes
Interior, described locking board 424 is fixing, and after locking board 424 is fixing, described locking cylinder 421 extend in battery compartment 41, optional
, described locking board 424 can also be fixed on battery compartment 41 top, such as buckle, bonding etc. by other means.Such as, institute
The surface stating locking board 424 is provided with buckle (not shown), and the diapire of described mounting groove 411 is provided with button bit (not shown), described
Buckle is fastened on described button bit.
Described locking board 424 is provided with one and crosses mouth, and described locking cylinder 421 can be to extend downwardly shape along the described ring crossing mouth
The hollow columnar structures of the one end open becoming.
Reference Fig. 8 and Fig. 9, in order to preferably manipulate latch components 42, further：
The side of described main part 4221 is arranged with screw (sign), and one end of described handle portion 4222 is provided with thread segment
4222a, described thread segment 4222a and described screw are spirally connected, and described handle portion 4222 is fixed on described main part 4221.
That is, when installing lock core 422, first main part 4221 is arranged in locking part 421, by handle portion 4222 after allowing
It is spirally connected and screw.The main part 4221 being arranged by split and the lock core 422 of handle portion 4222 composition, in installation and removal relatively
For convenience.
Certainly, in another embodiment of the invention, it is also possible that stating main part 4221 and described handle portion 4,222 1
Body chemical conversion type.So, facilitate the processing of lock core 422.
With reference to Fig. 8, the outer surface of described handle portion 4222 is provided with friction protrusion 4222b.Setting by friction protrusion 4222b
Put, the coefficient of friction of handle portion 4222 can be increased.Operator is allow preferably to manage handle portion 4222, it is to avoid to occur beating
Sliding situation.
Further, with reference to Fig. 8, in order that latch components 42 with spacing fixation more firm, described Plug Division
The wedge shaped setting of 4221a.
The foregoing is only the preferred embodiments of the present invention, not thereby limit the present invention the scope of the claims, every this
Under the inventive concept of invention, the equivalent structure transformation made using description of the invention and accompanying drawing content, or directly/indirectly use
In the scope of patent protection that other related technical fields are included in the present invention.
Claims (10)
1. a kind of paddle arm structure of unmanned plane is it is characterised in that include the first paragraph paddle arm being connected with the fuselage of described unmanned plane
With the second segment paddle arm of the fuselage away from described unmanned plane, described first paragraph paddle arm is detachably connected with described second segment paddle arm；
It is provided with the first wire with the master control borad electric connection of described unmanned plane, described second segment paddle arm in described first paragraph paddle arm
Inside it is provided with the second wire being connected with described first wire, the junction of described first wire and described second wire is provided with electromagnetism
Shielding part.
2. the paddle arm structure of unmanned plane as claimed in claim 1 is it is characterised in that the paddle arm structure of this unmanned plane also includes oar
Arm linkage section, the junction of described first wire and the second wire is located in this paddle arm linkage section, and described paddle arm linkage section has
The first end being oppositely arranged and the second end, this first end is connected to described first paragraph paddle arm, and this second end is connected to described second
Section paddle arm.
3. the paddle arm structure of unmanned plane as claimed in claim 2 is it is characterised in that the second end of described paddle arm linkage section is provided with
Accommodating chamber, described electromagnetic shield is fixedly installed in described accommodating chamber.
4. the paddle arm structure of unmanned plane as claimed in claim 3 is it is characterised in that be provided with junction block in described accommodating chamber,
Described junction block is used for connecting the first wire and the second wire, and described junction block stretches into and also sets up near the side of first end
State electromagnetic shield.
5. the paddle arm structure of unmanned plane as claimed in claim 4 is it is characterised in that arrange between described first end and the second end
There is dividing plate, described accommodating chamber is separated to form two parts, described dividing plate middle setting has square perforation, for installing described wiring
Seat.
6. unmanned plane as claimed in claim 4 paddle arm structure it is characterised in that described junction block include main board and located at
Connecting cylinder on main board, described main board is fixedly installed in described accommodating chamber, the connection of described first wire and the second wire
Place is placed in this connecting cylinder.
7. the paddle arm structure of unmanned plane as claimed in claim 1 is it is characterised in that described first paragraph paddle arm and described second segment
The junction of paddle arm is provided with one of them of buckle or button bit, and described second segment paddle arm is set with the junction of described first paragraph paddle arm
There is the wherein another of buckle or button bit, described buckle is fastened with described button bit, by described first paragraph paddle arm and described second
Section paddle arm is detachably fixed connection.
8. the paddle arm structure of unmanned plane as claimed in claim 3 is it is characterised in that the section of described first paragraph paddle arm is in triangle
Shape, the section of described second segment paddle arm is also triangular in shape, and what the side wall of described accommodating chamber surrounded is shaped as cross, and described second
Construction section in section paddle arm is also in that cross is arranged, and the side wall of described accommodating chamber is inserted in described construction section.
9. the paddle arm structure of unmanned plane as claimed in claim 3 is it is characterised in that the outside wall surface of the cavity wall of described accommodating chamber sets
There is locating slot, described locating slot extends from the second end of described paddle arm linkage section to first end, described second segment paddle arm is to should
Locating slot is provided with locating piece, and described locating piece grafting is placed in this locating slot.
10. a kind of unmanned plane is it is characterised in that include as the paddle arm structure of described unmanned plane arbitrary in claim 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610740295.5A CN106428509A (en) | 2016-08-26 | 2016-08-26 | Propeller arm structure of unmanned aircraft and unmanned aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610740295.5A CN106428509A (en) | 2016-08-26 | 2016-08-26 | Propeller arm structure of unmanned aircraft and unmanned aircraft |
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| Publication Number | Publication Date |
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| CN106428509A true CN106428509A (en) | 2017-02-22 |
Family
ID=58182355
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610740295.5A Pending CN106428509A (en) | 2016-08-26 | 2016-08-26 | Propeller arm structure of unmanned aircraft and unmanned aircraft |
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| Country | Link |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107972854A (en) * | 2017-10-27 | 2018-05-01 | 成都睿翼无人机科技有限公司 | A kind of power patrol unmanned machine |
| WO2020000660A1 (en) * | 2018-06-26 | 2020-01-02 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and arms thereof |
| CN111212781A (en) * | 2018-06-26 | 2020-05-29 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| WO2020229751A1 (en) * | 2019-05-16 | 2020-11-19 | Rte Reseau De Transport D'electricite | Unmanned aerial vehicle having an electromagnetically shielded housing and a laterally offset wing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101416359A (en) * | 2006-04-12 | 2009-04-22 | 迈恩德电子有限责任公司 | Vehicle cable for serial data transmission |
| CN203601563U (en) * | 2013-09-26 | 2014-05-21 | 深圳一电科技有限公司 | Aircraft and propeller arm thereof |
| CN103818544A (en) * | 2014-01-24 | 2014-05-28 | 深圳一电科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle body and manufacturing method thereof |
| US20140231594A1 (en) * | 2010-02-24 | 2014-08-21 | Robert Marcus | Rotocraft |
| CN104986330A (en) * | 2015-06-29 | 2015-10-21 | 深圳一电科技有限公司 | Propeller arm connection assembly and aircraft |
| CN205971789U (en) * | 2016-08-26 | 2017-02-22 | 深圳一电航空技术有限公司 | Unmanned aerial vehicle's oar arm structure and unmanned aerial vehicle |
-
2016
- 2016-08-26 CN CN201610740295.5A patent/CN106428509A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101416359A (en) * | 2006-04-12 | 2009-04-22 | 迈恩德电子有限责任公司 | Vehicle cable for serial data transmission |
| US20140231594A1 (en) * | 2010-02-24 | 2014-08-21 | Robert Marcus | Rotocraft |
| CN203601563U (en) * | 2013-09-26 | 2014-05-21 | 深圳一电科技有限公司 | Aircraft and propeller arm thereof |
| CN103818544A (en) * | 2014-01-24 | 2014-05-28 | 深圳一电科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle body and manufacturing method thereof |
| CN104986330A (en) * | 2015-06-29 | 2015-10-21 | 深圳一电科技有限公司 | Propeller arm connection assembly and aircraft |
| CN205971789U (en) * | 2016-08-26 | 2017-02-22 | 深圳一电航空技术有限公司 | Unmanned aerial vehicle's oar arm structure and unmanned aerial vehicle |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107972854A (en) * | 2017-10-27 | 2018-05-01 | 成都睿翼无人机科技有限公司 | A kind of power patrol unmanned machine |
| WO2020000660A1 (en) * | 2018-06-26 | 2020-01-02 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and arms thereof |
| CN111212781A (en) * | 2018-06-26 | 2020-05-29 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| WO2020229751A1 (en) * | 2019-05-16 | 2020-11-19 | Rte Reseau De Transport D'electricite | Unmanned aerial vehicle having an electromagnetically shielded housing and a laterally offset wing |
| FR3096026A1 (en) * | 2019-05-16 | 2020-11-20 | Rte Reseau De Transport D'electricite | Aerial vehicle without humans on board with electromagnetically protective box and laterally offset airfoil |
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