CN105398566B - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
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- CN105398566B CN105398566B CN201410458158.3A CN201410458158A CN105398566B CN 105398566 B CN105398566 B CN 105398566B CN 201410458158 A CN201410458158 A CN 201410458158A CN 105398566 B CN105398566 B CN 105398566B
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- oar
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- paddle arm
- blade
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Abstract
The invention discloses a kind of unmanned plane, including battery, control circuit component, multigroup oar component and fuselage, oar component is circumferentially disposed around fuselage；Oar component includes paddle arm, blade and the motor electrically connected with control circuit component, one end of each paddle arm is hinged with fuselage, the unmanned plane also include lock oar component and with the one-to-one gas bar of each paddle arm, arm body between paddle arm both ends is connected by a gas bar with fuselage, oar component has folded state and deployed condition, oar component in folded state is maintained at folded state by lock oar component, and the oar component in folded state is expanded to deployed condition and is maintained at deployed condition by gas bar.Thus, the spatial volume shared for the packaging structure of transport and when reducing storage is reduced, while oar component is to drive to deploy by gas bar, without manually installed.
Description
Technical field
The present invention relates to vehicle technology field, more particularly, to a kind of unmanned plane.
Background technology
This year, unmanned plane with the features such as its simple structure, convenient manipulation and higher security performance by more next
More attention.Unmanned plane of the prior art, its paddle arm are integrally formed mostly with fuselage, are also partly that paddle arm is divided into
One section of paddle arm and second segment paddle arm two parts, first paragraph paddle arm are integrally formed with fuselage, and second segment paddle arm can with first paragraph paddle arm
The connection of dismounting, solve the problems, such as transport, memory space to a certain extent, but still need artificial peace when in use
Dress, it is relatively complicated.
The content of the invention
It is a primary object of the present invention to provide a kind of unmanned plane, it is intended to further save transport and memory space
Meanwhile reach when in use without the purpose of manually installed paddle arm.
To achieve the above object, the present invention provides a kind of unmanned plane, including battery, control circuit component, multigroup oar component
And fuselage, the oar component are circumferentially disposed around the fuselage；The oar component includes paddle arm, blade and controls electricity with described
The motor of road component electrical connection, one end and the fuselage of each paddle arm are hinged, the unmanned plane also include locking oar component and
With each one-to-one gas bar of paddle arm, the arm body between the paddle arm both ends passes through a gas bar and connected with the fuselage
Connect, the oar component has folded state and deployed condition, and the lock oar component protects the oar component in folded state
Hold in folded state, the oar component in folded state is expanded to deployed condition and is maintained at expansion shape by the gas bar
State.
Preferably, the fuselage includes upper casing, lower casing and the support holder assembly between the upper casing and lower casing,
The support holder assembly includes the support base for corresponding and being set around a circumference with each paddle arm, and the support base is provided with
It is adapted to the paddle arm and for the clearance position of the accommodating paddle arm in folded state, one end of the paddle arm offers the first oar
Arm mounting hole, the opposite sides of the clearance position offer support base mounting hole respectively, and each paddle arm runs through by one respectively
The fastener of the support base mounting hole and the first paddle arm mounting hole is hinged on corresponding support base；Also opened on the support base
Provided with the position correspondence with the gas bar and the first gas bar via of the gas bar swing is available for, the gas bar passes through described first
Gas bar via, its one end are hinged on the arm of the paddle arm, and the other end is hinged on the fuselage.
Preferably, the fuselage also includes the upper fixed cover being fixed together and lower fixed cover, the lower fixed cover are located at
It is fixedly connected between the support holder assembly and the lower casing and with the lower casing, the unmanned plane also includes and each gas bar
One-to-one rotating shaft, it is fixed cover between the end face that is engaged with the lower fixed cover to be provided with cooperate and accommodating each
The locating slot of the rotating shaft, it is fixed to cover the second gas bar via offered with the position correspondence of each rotating shaft, institute
State gas bar and pass through the second gas bar via, its one end is rotatably sleeved in the rotating shaft and is hinged with the fuselage.
Preferably, the lock oar component is included around the fuselage and for tightening the oar component in folded state
Banding part and on the fuselage for locking and unclamp the locking device of the banding part.
Preferably, the banding part is left and right including bandage body and located at the bandage body both ends and with through hole
Button, the locking device include the electromagnet for having a telescopic shaft and being electrically connected with the control circuit component, the electromagnet
It is fixed on the lower casing, when the oar component is in folded state, telescopic shaft described in the solenoid actuated is protruding
And be inserted into the through hole of the left and right button, the left and right button is fixed together.
Preferably, the banding part is left and right including bandage body and located at the bandage body both ends and with through hole
Button, the locking device includes gear, rack, expansion link and the lock oar motor electrically connected with the control circuit component, described
Rack is slideably installed on the lower casing, the gear be fixed on it is described lock oar motor output shaft on and with the rack
Engagement connection, the expansion link is connected to one end of the rack, when the oar component is in folded state, the lock oar electricity
Machine drives the expansion link protruding and is inserted into the through hole of the left and right button, and the left and right button is connected in into one
Rise.
Preferably, the lock oar component includes lock blade, blasting cartridge, explosion lead and Blasting Control unit, the explosion
Pipe seals chamber up for safekeeping provided with accommodating explosive agent, and one end of the explosion lead is connected with the explosive agent in the blasting cartridge, the other end
It is connected with the Blasting Control unit, the Blasting Control unit electrically connects with the control circuit component, in the oar component
During in folded state, the blasting cartridge is fixed together with the lock blade.
Preferably, the motor includes the motor body for being fixed on the outer end of the paddle arm, and is fixed on the motor sheet
Rotating disk on the output shaft of body, is convexly equipped with two fixed columns on the rotating disk, between described two fixed columns the center of line with
The jante et perpendiculaire of the rotating disk, the blade include first paragraph blade and second segment blade, the first paragraph blade and
The connection end of two sections of blades offers the blade mounting hole being adapted to the fixed column, the first paragraph blade and second segment oar
Leaf is rotatably sleeved in two fixed column by blade mounting hole thereon respectively；Rugosity is in the oar component
During state, first paragraph blade and second segment blade are collapsed and enclosed jointly in the space to be formed in each paddle arm.
Preferably, the cross section of the paddle arm is in U shape.
A kind of unmanned plane provided by the present invention, by using the oar component of foldable design, therefore reduce for transporting
Defeated packaging structure and spatial volume shared during storage is reduced, while oar component is to drive to deploy by gas bar, nothing
Need manually installed.
Brief description of the drawings
Fig. 1 is structural representation of the unmanned plane in deployed condition of the present invention；
Fig. 2 is structural representation of the unmanned plane in folded state of the present invention；
Fig. 3 is the oar component of unmanned plane and the assembling structure schematic diagram of fuselage of the present invention；
Fig. 4 is the three-dimensional assembly diagram of the fuselage of the unmanned plane of the present invention；
Fig. 5 is the explosive view of the fuselage shown in Fig. 2；
Fig. 6 is the structural representation of the support base shown in Fig. 3；
Fig. 7 is the structural representation of the upper fixed cover shown in Fig. 3；
Fig. 8 is the structural representation of the lower fixed cover shown in Fig. 5；
Fig. 9 is the structural representation of the first embodiment of the lock oar component of the unmanned plane of the present invention；
Figure 10 is the structural representation of lock oar second of embodiment of component of the unmanned plane of the present invention；
Figure 11 is the structural representation of the oar component of the unmanned plane of the present invention；
Figure 12 is the structural representation of the motor shown in Figure 11；
Figure 13 is the structural representation of the blade shown in Figure 11.
The realization, functional characteristics and advantage of the object of the invention will be described further referring to the drawings in conjunction with the embodiments.
Embodiment
It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, it is not intended to limit the present invention.
The present invention provides a kind of unmanned plane, and it is folding Rotor Helicopter, referring to Fig. 1 to Fig. 3, in nothing of the present invention
In man-machine preferred embodiment, the unmanned plane includes battery (not shown), control circuit component (not shown), multigroup
Oar component 200 and fuselage 100, the chamber for set battery and control circuit component is provided with fuselage 100, battery is electric power storage
Pond, such as lithium battery, for providing electric energy to the associated components of unmanned plane, control circuit component includes multiple control modules, than
Such as be used for control unmanned plane during flying posture flight control modules, the big dipper module (such as GPS module) for the unmanned plane that navigates, with
And data processing module for handling the environmental information acquired in related airborne equipment etc..In better embodiment, fuselage
100 is cylindrical, and is illustrated exemplified by six groups of oar components 200 are provided with fuselage 100, as shown in figure 1, six groups of oar groups
Part 200 is uniformly arranged around the circumference of fuselage 100.It should be appreciated that the number of the oar component 200 shown in figure is only for example,
The number can be selected flexibly during practical application, such as in other embodiments, be provided with fuselage 100 four groups of oar components 200 or
The oar component 200 of other any suitable numbers.
Specifically, oar component 200 includes paddle arm 210, blade 230 and the motor 220 electrically connected with control circuit component, oar
Leaf 230 is arranged on the output shaft of motor 220, and one end of each paddle arm 210 and fuselage 100 are be hinged, and motor 220 is arranged on
On the other end of paddle arm 210, in addition, the unmanned plane also include lock oar component 400 and with the one-to-one gas bar of each paddle arm 210
300, the arm status between each both ends of paddle arm 210 is not connected by a gas bar 300 with fuselage 100.Therefore, can be stretched by this
The gas bar 300 of contracting, paddle arm 210 corresponding to driving turn an angle (such as 90 degree) around the hinge axes of itself and fuselage 100,
That is, oar component 200 has folded state and deployed condition, it is preferred that when oar component 200 is in folded state, 210 turns of paddle arm
Move to the position with fuselage 100 side by side；When oar component 200 is in deployed condition, it is vertical that paddle arm 210 turns to fuselage 100
Position.Wherein, lock oar component 400 and the oar component 200 in folded state is maintained at folded state, when lock oar component 400 opens
When releasing its lock function when dynamic, the oar component 200 in folded state is expanded to deployed condition and is maintained at by gas bar 300
Deployed condition.
It is noted that the cross section of paddle arm 210 is in U shape, and when unmanned plane deploys flight, this structure shape
The paddle arm 210 of formula has more preferable aerodynamic performance, plays a part of stable unmanned plane and reduces flight resistance.
As can be seen here, unmanned plane of the invention therefore reduces for transporting by using the oar component 200 of foldable design
Defeated packaging structure and spatial volume shared during storage is reduced, while oar component is to drive to deploy by gas bar, nothing
Need manually installed.
Specifically, referring to Fig. 4 to Fig. 6, fuselage 100 includes upper casing 110, lower casing 120 and positioned at upper casing 110 and lower casing
Support holder assembly between 120, support the upper and lower ends of holder assembly to be fixed respectively by screw and upper casing 110 and lower casing 120 and connect
Connect.Wherein, the support holder assembly includes the support base 130 for corresponding with each paddle arm 210 and being set around a circumference, compared with
Goodly, support base 130 is set around an even circumferential, so as to reduce the difficulty of balance unmanned plane, and improves the stabilization of unmanned plane
Property.Support base 130, which is provided with, to be adapted to paddle arm 210 and for the clearance position of the accommodating paddle arm 210 in folded state, upper casing 110
It is cylindrical, there is the chamber of set battery and control circuit component, lower casing 120 includes rounded body 121 and from body
121 periphery upwardly extends the annular side portions 122 to be formed, and the annular side portions 122 cave inward formed with each branch
The corresponding depressed part 123 in the position of the clearance position of seat 130 is supportted, therefore when the length of paddle arm 210 is more than the height of support base 130
When, the lower casing 120 positioned at the lower section of support base 130 will not also cause to interfere to the paddle arm 210 in folded state.When oar component
200 when being in folded state, and paddle arm 210 is overlapping with fuselage 100 to be partially submerged into the clearance position of support base 130 and depressed part
In 123, therefore volume when unmanned plane is in folded state can be reduced, be easy to packed and transported, transmitting and air-drop.Referring to Figure 11,
One end of paddle arm 210 offers the first paddle arm mounting hole 211, and the both sides that the clearance position of support base 130 is relative offer branch respectively
Seat mounting hole 1321 is supportted, and the first paddle arm mounting hole 211 is adapted with support base mounting hole 1321, each paddle arm 210 is distinguished
By always wearing the fastener of the paddle arm mounting hole 211 of support base mounting hole 1321 and first, (for example the fastener is bearing pin or spiral shell
Bar) it is hinged on corresponding support base 130.Referring to Fig. 6, in one embodiment, support base 130 include the body 131 in straight panel,
Side plate 132 positioned at the both sides of body 131 and the top plate 133 positioned at the upper end of body 131, its latus inframedium 132 and top plate 133
Vertical with body 131, two side plates 132 and top plate 133 limit the clearance position of accommodating paddle arm 210, and support base jointly
Mounting hole 1321 is opened on biside plate 132.
It is understood that can also be by the support between upper casing 110 and lower casing 120 in other embodiment
What holder assembly was formed integrally, so as to simplify the assembly process of unmanned plane and improve the bulk strength of unmanned plane.
Specifically, referring to Fig. 3, it is further opened with the position correspondence with gas bar 300 on support base 130 and is available for the gas bar 300
The the first gas bar via 1311 (corresponding referring to Fig. 6) swung, the first gas bar via 1311 is opened on body 131, it is preferred that
First gas bar via 1311 is the waist-shaped hole of strip.Gas bar 300 passes through the first gas bar via 1311 of support base 130, one
End is hinged on the arm of paddle arm 210, and the other end is hinged on fuselage 100.It should be noted that what the arm body of paddle arm 210 referred to
Long straight portion between the both ends of paddle arm 210 point, between gas bar 300 and paddle arm 210 articulated position can according to the length of gas bar 300 and
Position when paddle arm 210 is deployed is determined, this is not restricted.When lock oar component 400 releases the limitation to oar component 200, oar
Component 200 can be rotated by deployed condition in the piston rod of gas bar 300, and the expansion process of oar component 200 need not
Other power set provide power, and gas bar 300 can give the oar component 200 in deployed condition to provide stable support.Thus
Understand, the exhibition oar component 200 of the present embodiment is simple in construction, cost is cheap.It is noted that it can also use other any suitable
Piston rod piece substitute the gas bar 300 of the present embodiment, but the piston rod piece should possess the spy such as occupy little space, be in light weight
Point, the concrete structure on piston rod piece can be designed according to the structure type and operation principle of gas bar 300, do not go to live in the household of one's in-laws on getting married herein
State.
Further, referring to Fig. 7 and Fig. 8, fuselage 100 also includes the upper fixed cover 140 being fixed together and lower fixed cover
150, upper fixed cover 140 and lower fixed cover 150 are the loop configuration provided with a central through hole, so as to mitigate the weight of unmanned plane
Amount.It is fixedly connected between upper fixed cover 140 and lower fixed cover 150 by screw, for example, being offered in upper fixed cover 140 some
Around the mounting hole 143 of its central through hole, the position pair with the mounting hole 143 of upper fixed cover 140 is offered in lower fixed cover 150
The screwed hole 156 answered.Wherein, lower fixed cover 150 is fixedly connected between support holder assembly and lower casing 120 and with lower casing 120,
Lower fixed cover 150 includes the body 151 of tabular, and the end face that body 151 docks with upper fixed cover 140 is convexly equipped with around lower fixed cover
The annular relief 152 of 150 central through hole, and the side wall of body 151 caves inward formed with the empty avoiding with support base 130
The breach 157 of the position correspondence of position, so as to meet the requirement being contained in paddle arm 210 in the clearance position of support base 130.Support base
130 are fixedly connected with lower fixed cover 150 also through screw, such as, offered on body 151 and the side plate of support base 130 132
The through hole 155 of position correspondence, as shown in figure 8, through hole 155 is located at two side edges of breach 157, and the side plate of support base 130
132 bottom surface offers the screwed hole (not shown) with the position correspondence of through hole 155, and screw is through through hole 155 and screws in
Lower fixed cover 150 is fastened on support base 130 in the screwed hole of the side plate 132 of support base 130.In addition, unmanned plane also wraps
Include with the one-to-one rotating shaft 310 of each gas bar 300, set between the end face that upper fixed cover 140 is engaged with lower fixed cover 150
There is the locating slot for cooperating and housing each rotating shaft 310, the locating slot is by being separately positioned on upper fixed cover 140 and lower fixation
Two parts groove composition on lid 150, such as, the medial surface of upper fixed cover 140 be concavely provided be evenly arranged around its center and
The upper deep-slotted chip breaker 141 being adapted to rotating shaft 310, the upper surface of lower fixed cover 150 are concavely provided with the position with deep-slotted chip breaker on each 141
Lower arcuate slot 153 that is corresponding and being adapted to rotating shaft 310 is put, in order to improve the fixing intensity of rotating shaft 310, lower arcuate slot 153 is located at
On annular protrusion 152, the second gas bar via with the position correspondence of each rotating shaft 310 is further opened with upper fixed cover 140
142, and the groove 154 with the position correspondence of each the second gas bar via 142 is additionally provided with the upper surface of lower fixed cover 150
Or through hole, so as to meet the matching requirements of gas bar 300.Gas bar 300 passes through the second gas bar via 142 of upper fixed cover 140, one
End is rotatably sleeved in rotating shaft 310 and is hinged with fuselage 100, therefore improves the bonding strength of the articulated structure of gas bar 300.
It is noted that the articulated structure between gas bar 300 and fuselage 100 also has numerous embodiments, such as,
In the present embodiment, above-mentioned rotating shaft 310 is wholely set with lower fixed cover 150, so as to simplify the structure design of fuselage 100, mitigates nothing
Man-machine weight.
In an embodiment of the present invention, locking oar component 400 has numerous embodiments, and lock oar component 400 is included around machine
Body 100 and for tighten the oar component 200 in folded state banding part and on fuselage 100 for locking and pine
The locking device of the banding part is driven, the composition and operation principle of wherein banding part and locking device will be elaborated upon below.
Fig. 9 shows the lock oar component first embodiment of the unmanned plane of the present invention.In the present embodiment, banding part includes tying up
Band body 410 and located at the both ends of bandage body 410 and with through hole it is left buckle 411 and it is right buckle 412, bandage body 410 can be
Plastic cement flat rubber belting or fiber or nylon flat rubber belting, because bandage body 410 is flexible-belt, it is consequently adapted in folding
The oar component 200 of state tightens, and will not damage oar component 200.Locking device include with a telescopic shaft 421 and with control
The electromagnet 420 of circuit unit electrical connection, the electromagnet 420 is fixed on lower casing 120, for example can pass through screw between the two
It is fixed together, electromagnet 420 can be located on the upper surface of lower casing 120, can also be located on the lower surface of lower casing 120.When
When electromagnet 420 is located at the upper surface of lower casing 120, it need to also be offered in the annular side portions 122 of lower casing 120 for telescopic shaft 421
Pass the through hole 124 (corresponding referring to Fig. 5) of the annular side portions 122.When oar component 200 is in folded state, electromagnet 420 exists
Drive telescopic shaft 421 protruding under the control of control circuit component and be inserted into it is left buckle 411 and it is right buckle in 412 through hole, with
Left button 411 and right button 412 are fixed together, so as to by surrounding the fuselage bandage body 410 of 100 1 weeks by all oar components
200 are locked on fuselage 100；And when oar component 200 will deploy, electromagnet 420 drives under the control of control circuit component
Telescopic shaft 421 is inwardly retracted and exited from the through hole of left button 411 and right button 412, so that left button 411 and right button 412 are de- mutually
From so that bandage body 410 departs from fuselage 100.Thus, can be realized easily to oar component by the lock oar component 400
200 locking and release.
Figure 10 shows the lock oar component second embodiment of the unmanned plane of the present invention.In the present embodiment, locking device bag
Include gear 431, rack 432, expansion link 433 and the lock oar motor 430 electrically connected with control circuit component.Wherein, rack 432 can
Slidably it is installed on lower casing 120, same as above, locking device can be located on the upper surface or lower surface of lower casing 120, tooth
Bar 432 is fixed on lower casing 120 by a fastener 434 with chute, and rack 432 has the chute phase with fastener 434
The structure of cooperation, thus rack 432 be limited in it is for linear motion in the chute of fastener 434, gear 431 be fixed on lock oar electricity
Connection is engaged on the output shaft of machine 430 and with rack 432, expansion link 433 is connected to one end of rack 432.At oar component 200
When folded state, lock oar motor 430 just then drives expansion link 433 protruding and inserted under the control of control circuit component
Enter to the through hole of left button 411 and right button 412, left button 411 and right button 412 are fixed together, so as to by around fuselage
All oar components 200 are locked on fuselage 100 by the bandage body 410 of 100 1 weeks；And when oar component 200 will deploy, lock oar
Motor 430 inverts under the control of control circuit component and drives expansion link 433 inwardly to retract and buckle 411 from left and right buckle 412
Through hole in exit so that left button 411 and right button are 412 away from one another, so that bandage body 410 departs from fuselage 100.By
This, can also realize locking and release to oar component 200 easily by the lock oar component 400.
In addition, the lock oar component of the present invention also has other embodiment, such as, lock oar component includes lock blade, explosion
Pipe, explosion lead and Blasting Control unit (being not shown in figure), wherein blasting cartridge seal chamber up for safekeeping provided with accommodating explosive agent, in order to
Impulsive force caused by reducing explosion impacts to unmanned plane, and blasting cartridge is preferably that non-metallic pipe is made, and explosive agent can be solid
Body free-flowing dynamite or liquid explosives, in practical application, corresponding fried pharmacy type can be used as needed；It is quick-fried
Explosive agent connection in one end and blasting cartridge of broken lead, the other end is connected with Blasting Control unit, and Blasting Control unit
Electrically connected with control circuit component.In better embodiment, using pulsed arc ignition charge agent, therefore Blasting Control unit
For making one end that explosion lead is located in blasting cartridge produce high-voltage arc, and the control of controlled circuit unit.In oar component
200 when being in folded state, and blasting cartridge is fixed together with lock blade, and the oar group tightened in folded state is formed so as to enclose
The loop configuration of part 200, when oar component 200 will deploy, under the control of control circuit component, Blasting Control unit makes explosion
Lead produces high-voltage arc, to ignite blasting cartridge, disconnects, enters so that enclosing the loop configuration formed with lock blade by blasting cartridge
And lock oar component is set to be separated with unmanned plane.In the present embodiment, the working of plastics that blade can be strip is locked, or Fig. 9
And the banding part shown in Figure 10, such as, lock blade is above-mentioned banding part, then blasting cartridge is inserted into left button 411 and right button 412
In through hole, left button 411 and right button 412 are fixed together, so that will by surrounding the fuselage bandage body 410 of 100 1 weeks
All oar components 200 are locked on fuselage 100；And when oar component 200 will deploy, it is quick-fried under the control of control circuit component
Broken control unit makes explosion lead produce high-voltage arc, to ignite blasting cartridge, so that left button 411 and right button 412 are away from one another,
And then bandage body 410 is set to depart from fuselage 100.
Referring to Figure 11 to Figure 13, in the present embodiment, motor 220 includes the motor body for being fixed on the outer end of paddle arm 210
221, and the rotating disk 222 being fixed on the output shaft of motor body 221, rotating disk 222 can be circular, ellipse and other are any
Applicable shape, as illustrated, in order that rotating disk 222 is more steady in rotation process, preferably rotating disk 222 is shaped as justifying
Shape, two fixed columns (being the first fixed column 223 and the second fixed column 224 respectively), the first fixed column are convexly equipped with rotating disk 222
223 and second fixed column 224 be located in the same radial alignment of rotating disk 222, and the first fixed column 223 and the second fixed column
The center of line and the jante et perpendiculaire of rotating disk 222, blade 230 include first paragraph blade 231 and second segment blade between 224
232, the connection end 2311 of first paragraph blade 231 offers the blade mounting hole 2312 being adapted to the first fixed column 223, similarly,
The connection end of second segment blade 232 offers the blade mounting hole (not shown) being adapted to the second fixed column 224, first paragraph
Blade 231 is rotatably sleeved in the first fixed column 223 by blade mounting hole 2312 thereon, and by being fixed first
The end set position limiting structure of post 223 and prevent that first paragraph blade 231 from deviating from, for example, the end of the first fixed column 223 be provided with it is outer
Screw thread, spacing, second segment oar can be carried out to first paragraph blade 231 by the nut installed in the end of the first fixed column 223
The attachment structure and assembly method of leaf 232 are identical with first paragraph blade 231, and therefore not to repeat here.It is understood that
In order to meet that flight requires, first paragraph blade 231 and the Central Symmetry of second segment blade 232.It follows that at oar component 200
When folded state, by the way that by first paragraph blade 231 and the folded side by side of second segment blade 232, space can be saved；And work as oar group
When part 200 is in deployed condition, first paragraph blade 231 and second segment blade 232 can be from rolling under the driving of motor 220 side by side
Overlapping state is changed to the state of being arranged in a straight line, and realizes the autonomous expansion of blade 230.It is noted that at oar component 200
When deployed condition, motor 220 and blade 230 are located at the lower position of paddle arm 210, the motor 220 and oar of this arrangement form
Leaf 230 can save space when oar component 200 is in folded state.
It should be appreciated that it these are only the preferred embodiments of the present invention, it is impossible to therefore the scope of the claims of the limitation present invention,
Every equivalent structure made using description of the invention and accompanying drawing content or equivalent flow conversion, or be directly or indirectly used in
Other related technical areas, it is included within the scope of the present invention.
Claims (8)
1. a kind of unmanned plane, it is characterised in that including battery, control circuit component, multigroup oar component and fuselage, the oar component
Around the circumferentially disposed of the fuselage；The oar component includes paddle arm, blade and the electricity electrically connected with the control circuit component
Machine, one end and the fuselage of each paddle arm are hinged, the unmanned plane also include lock oar component and with each paddle arm one by one
Corresponding gas bar, positioned at the circumferential inner side of the fuselage when gas bar does not extend, the circumference of the fuselage be provided with it is described
The position correspondence of gas bar and the first gas bar via for being available for the gas bar to swing, the arm body between the paddle arm both ends pass through an institute
State gas bar to be connected with the fuselage, the oar component has folded state and deployed condition, and the lock oar component, which will be in, to be folded
The oar component of state is maintained at folded state, deploys the oar component of the original place in folded state when the gas bar extends
To deployed condition and it is maintained at deployed condition；
The fuselage includes upper casing, lower casing and the support holder assembly between the upper casing and lower casing, the support base group
Part includes the support base for corresponding and being set around a circumference with each paddle arm, and the support base is provided with and fitted with the paddle arm
Match somebody with somebody and for the clearance position of the accommodating paddle arm in folded state, one end of the paddle arm offers the first paddle arm mounting hole, institute
The opposite sides for stating clearance position offers support base mounting hole respectively, and each paddle arm is pacified by one through the support base respectively
The fastener of dress hole and the first paddle arm mounting hole is hinged on corresponding support base；First gas is offered on the support base
Bar via, the gas bar pass through the first gas bar via, and its one end is hinged on the arm of the paddle arm, and the other end is hinged on
On the fuselage.
2. unmanned plane as claimed in claim 1, it is characterised in that the fuselage also include the upper fixed cover that is fixed together and
Lower fixed cover, the lower fixed cover are fixedly connected between the support holder assembly and the lower casing and with the lower casing, institute
State the end that unmanned plane also includes being engaged with the lower fixed cover with each one-to-one rotating shaft of gas bar, fixed lid
The locating slot for cooperating and housing each rotating shaft is provided between face, fixed cover offers and each rotating shaft
Second gas bar via of position correspondence, the gas bar pass through the second gas bar via, and its one end is rotatably sleeved on described
It is hinged in rotating shaft with the fuselage.
3. unmanned plane as claimed in claim 1 or 2, it is characterised in that the lock oar component is included around the fuselage and use
In the banding part for tightening the oar component in folded state and on the fuselage for locking and unclamp the hoop
The locking device of tight part.
4. unmanned plane as claimed in claim 3, it is characterised in that the banding part includes bandage body and located at the bandage
Body both ends and with through hole left and right button, the locking device include with a telescopic shaft and with the control circuit component
The electromagnet of electrical connection, the electromagnet are fixed on the lower casing, when the oar component is in folded state, the electromagnetism
Iron drives the telescopic shaft protruding and is inserted into the through hole of the left and right button, and the left and right button is connected in into one
Rise.
5. unmanned plane as claimed in claim 3, it is characterised in that the banding part includes bandage body and located at the bandage
Body both ends and with through hole left and right button, the locking device include gear, rack, expansion link and with the control circuit
The lock oar motor of component electrical connection, the rack are slideably installed on the lower casing, and the gear is fixed on the lock oar
Connection is engaged on the output shaft of motor and with the rack, the expansion link is connected to one end of the rack, in the oar group
When part is in folded state, the lock oar motor drives the expansion link protruding and is inserted into the through hole of the left and right button
It is interior, the left and right button is fixed together.
6. unmanned plane as claimed in claim 1 or 2, it is characterised in that the lock oar component includes lock blade, blasting cartridge, quick-fried
Broken lead and Blasting Control unit, the blasting cartridge seal chamber, one end of the explosion lead and institute up for safekeeping provided with accommodating explosive agent
The explosive agent connection in blasting cartridge is stated, the other end is connected with the Blasting Control unit, the Blasting Control unit and the control
Circuit unit electrical connection processed, when the oar component is in folded state, the blasting cartridge is fixed together with the lock blade.
7. unmanned plane as claimed in claim 1, it is characterised in that the motor includes the electricity for being fixed on the outer end of the paddle arm
Machine body, and the rotating disk being fixed on the output shaft of the motor body, are convexly equipped with two fixed columns on the rotating disk, and described two
The center of line and the jante et perpendiculaire of the rotating disk, the blade include first paragraph blade and second segment between individual fixed column
Blade, the connection end of the first paragraph blade and second segment blade offer the blade mounting hole being adapted to the fixed column,
The first paragraph blade and second segment blade are rotatably sleeved in described two fixations by blade mounting hole thereon respectively
On post；When the oar component is in folded state, first paragraph blade and second segment blade are collapsed and enclosed jointly in each paddle arm
Close in the space formed.
8. unmanned plane as claimed in claim 1, it is characterised in that the cross section of the paddle arm is in U shape.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410458158.3A CN105398566B (en) | 2014-09-10 | 2014-09-10 | Unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410458158.3A CN105398566B (en) | 2014-09-10 | 2014-09-10 | Unmanned plane |
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| CN105398566A CN105398566A (en) | 2016-03-16 |
| CN105398566B true CN105398566B (en) | 2017-11-10 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106240807B (en) * | 2016-07-28 | 2018-08-28 | 上海航天控制技术研究所 | A kind of integrated unmanned plane of collection photodetection |
| CN106094857A (en) * | 2016-08-22 | 2016-11-09 | 京东方科技集团股份有限公司 | The flight control method of unmanned plane, wearable device and unmanned plane, device |
| CN106184794A (en) * | 2016-08-30 | 2016-12-07 | 成都汇丁科技有限公司 | A kind of unmanned plane for taking photo by plane |
| CN106394885B (en) * | 2016-09-21 | 2018-07-10 | 深圳飞马机器人科技有限公司 | The portable folding method of quadrotor unmanned plane |
| CN107738746B (en) * | 2017-08-30 | 2019-10-01 | 中北大学 | Folding automatic running on transmisson line unmanned plane |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US4712978A (en) * | 1986-12-01 | 1987-12-15 | Tiemann James P | Helicopter blade and the like stand-off and folding device |
| AU3245699A (en) * | 1998-02-03 | 1999-08-23 | Gunter Lang | Device for cleaning the working area of chip removal machines |
| CA2802389C (en) * | 2010-06-15 | 2015-11-24 | Bell Helicopter Textron Inc. | Method and apparatus for in-flight blade folding |
| CN102442423A (en) * | 2010-10-12 | 2012-05-09 | 徐延宇 | Adjustable-height foldable propeller |
| CN103332291B (en) * | 2013-06-14 | 2015-11-18 | 南京航空航天大学 | A kind of air-drop six rotor wing unmanned aerial vehicles fold and development mechanism |
| CN103979107B (en) * | 2014-05-21 | 2016-01-20 | 北京理工大学 | A kind of folding rotor type unmanned plane |
| CN204210727U (en) * | 2014-09-10 | 2015-03-18 | 深圳一电科技有限公司 | Unmanned plane |
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Effective date of registration: 20160304 Address after: Baoan District Shiyan street Shenzhen city Guangdong province 518108 Songbai road Tangtou junctions electric science and Technology Park Applicant after: Shenzhen Aee Technology Co., Ltd. Address before: 518108 Guangdong city of Shenzhen province Nanshan District Xili Sunshine Industrial Zone Electric Science and Technology Park Applicant before: Shenzhen Aee Technology Co., Ltd. Applicant before: Shenzhen Aee Technology Co., Ltd. |
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Effective date of registration: 20191211 Address after: Room 812, enterprise service center, No. 17, section 3, west section of Changjiang North Road, Lingang Economic Development Zone, Yibin City, Sichuan Province Patentee after: Sichuan Yidian Aviation Technology Co., Ltd Address before: Baoan District Shiyan street Shenzhen city Guangdong province 518108 Songbai road Tangtou junctions electric science and Technology Park Patentee before: Shenzhen Yidian Aviation Technology Co., Ltd. |