CN107856851A - A kind of compact collapsible unmanned plane - Google Patents
A kind of compact collapsible unmanned plane Download PDFInfo
- Publication number
- CN107856851A CN107856851A CN201711239041.6A CN201711239041A CN107856851A CN 107856851 A CN107856851 A CN 107856851A CN 201711239041 A CN201711239041 A CN 201711239041A CN 107856851 A CN107856851 A CN 107856851A
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- Prior art keywords
- link arm
- end link
- unmanned plane
- leg
- rear end
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- 239000002002 slurry Substances 0.000 claims abstract description 12
- 210000000245 forearm Anatomy 0.000 claims description 19
- 238000009434 installation Methods 0.000 claims description 16
- 230000005540 biological transmission Effects 0.000 claims description 7
- 238000001816 cooling Methods 0.000 claims description 6
- 230000000712 assembly Effects 0.000 claims description 2
- 238000000429 assembly Methods 0.000 claims description 2
- 230000000903 blocking effect Effects 0.000 claims 1
- 230000008859 change Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000005611 electricity Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000004806 packaging method and process Methods 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000004807 localization Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000008685 targeting Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
- H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M2220/00—Batteries for particular applications
- H01M2220/20—Batteries in motive systems, e.g. vehicle, ship, plane
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
Abstract
A kind of compact collapsible unmanned plane, including body, two front end link arms, two rear end link arms, drive member, the slurry wing, battery tray, battery and head assembly, the present invention passes through battery components and the integrated setting of head assembly and fuselage, and the slurry wing and the drive member integrated design with front end link arm and rear end link arm respectively, form the structure of compact, all parts cooperate, and reduce the space-consuming of unmanned plane on the whole；In addition when unmanned plane is in idle state, i.e. non-state of flight when, the front end link arm and rear end link arm being capable of cross foldings, substantially fuselage can be bonded, and front end link arm and rear end link arm carry leg, extra support meanss need not be increased, the small volume for taking foldable integral, be easy to store and carry.
Description
Technical field
The present invention relates to unmanned plane field, and in particular to a kind of compact collapsible unmanned plane.
Background technology
Common flight device is typically divided into fixed-wing, helicopter and more rotors（Four rotors main flow the most）.2010 it
Before, no matter fixed-wing and helicopter are taking photo by plane or model plane Sports Field, substantially occupy absolute leading position.However,
In several years afterwards, because of excellent handling, more rotors rapidly become the nova taken photo by plane with model plane Sports Field.Because of the product
The difficulty and cost taken photo by plane are significantly reduced, obtains the vast consumer group, turns into product most fast-selling so far.
Multi-rotor unmanned aerial vehicle, it is a kind of special pilotless helicopter with three and above rotor shaft.It passes through
Motor rotation on each axle, drives rotor, so as to produce a liter thrust.Rotor always away from fixation, rather than general helicopter
It is variable like that.By changing the relative rotation speed between different rotors, thus it is possible to vary the size of single shaft propulsive force, so as to control flight
The running orbit of device.
Multi-rotor unmanned aerial vehicle is many by favor reason, and such as in terms of handling, the manipulation of more rotors is simplest.It is not
Need runway can be hovered in the air after taking off with VTOL.Its manipulating principle is simple, four remote sensing operations of control device
Around corresponding aircraft, up and down and yaw direction motion.And fixed-wing flying field requires open, and helicopter
Interchannel coupling can be produced in flight course, autopilot controller design is difficult, and controller regulation is also highly difficult.
In terms of reliability, more rotors are also that performance is most outstanding.If only considering the reliability of machinery, more rotors are not lived
Dynamic component, its reliability is substantially dependent on the reliability of brushless electric machine, therefore reliability is higher.Comparatively speaking, it is fixed
The wing and helicopter have the mechanical connecting element of activity, can produce abrasion in flight course, cause reliability decrease.And more rotors
It can hover, flight range is controlled, and it is safer to be relatively fixed the wing.
In terms of duties, the duties of more rotors are highests.Because its is simple in construction, if motor, electron speed regulator, electricity
Pond, oar and frame damage, it is easy to replace.And fixed-wing and helicopter part comparison are more, installation is also required to skill, relatively
Trouble.
However, the expansion of rotor occupies very big space, when not in use, can not preferably be stored, neither just
Just transport, be also inconvenient to pack.In the prior art, some more rotors also fold unmanned plane, but the design of integral body is not
It is enough compact, make the fuselage after folding still larger, packaging, transport are all inconvenient.
The content of the invention
It is an object of the invention to provide a kind of compact collapsible unmanned plane, and it is not tight to solve multi-rotor unmanned aerial vehicle structure
Gather, the problem of space-consuming is big.
In order to solve the above problems, the present invention provides a kind of compact collapsible unmanned plane, including body, two front-end chains
Arm, two rear end link arms, drive member, multiple the slurry wing, battery component and head assemblies are connect,
The body includes being used for the body fuselage for protecting internal structure, and the sky for accommodating battery component is provided with the upside of the body
Chamber, the battery component are removably mounted in cavity, and body battery interface, the battery component bottom are provided with the cavity
Portion is provided with battery interface, battery is electrically connected with body；
The body front end is provided with installation position, and the head assembly is arranged on installation position；
Described two front end link arms and two rear end link arms are respectively symmetrically located at the both sides of body,
The front end link arm and rear end link arm are near-end close to one end of body, and one end away from body is distal end,
The near-end of the front end link arm and rear end link arm is hinged with body so that front end link arm and rear end link arm can
Folded towards body direction；
Drive member is respectively equipped with the upside of the distal end of the front end link arm and rear end link arm, the slurry wing is located at drive member
Top, and be electrically connected with drive member；
The distal bottom of the front end link arm and rear end link arm is respectively equipped with forearm leg and postbrachium leg, the front-end chain
Connect arm and link arm distal end in rear end is respectively equipped with mounting groove so that the forearm leg and postbrachium leg can be accommodated in mounting groove
It is interior.
In order to reduce body volume, detachable battery assembly is arranged in the cavity of body upper by the present invention, described
Battery component includes battery tray and battery, and the battery tray is provided with power switch and power supply indicator, is charging or using
Cheng Zhong, power supply indicator can clearly show that electricity and whether be in "on" position.Battery, institute are set inside the battery tray
State battery to surround by the battery frame of outside, the frame size is just coincide with engine cavity, can be fully mated and solid
Fixed, after the battery tray is entrenched in cavity, battery tray upper surface can coordinate with body, from the appearance form regarding for integration
Feel effect, while also at utmost reduce the volume of complete machine.Body battery interface, the battery tray bottom are provided with the cavity
Portion is provided with battery interface corresponding to battery, when battery tray is installed in cavity, the battery interface and body battery interface shape
Into electric connection, turn into the major impetus source of each driving part of the unmanned plane.
The head assembly is mainly used in shooting to scene of the unmanned plane in flight course, is connected by mobile data
Connect, user can be immediately seen the scene of shooting on MOVING STRUCTURE, and be switched over according to the needs various visual angles of oneself, increase
The experience of user.The present invention is not on the premise of unmanned plane overall volume is increased, will by setting installation position in front fuselage
Head assembly is arranged in installation position, on the one hand, ensure that unmanned plane has the visual field of maximum in flight course, on the other hand
Overall volume will not be taken, makes structure compacter.
The present invention is provided with four link arms, two front end link arms, two rear end link arms, and the right and left is symmetrical arranged,
Play a part of balance.The near-end of the front end link arm and rear end link arm is hinged with body so that front end link arm is with after
End link arm can fold towards body direction；When needs fly in use, link arm can manually or automatically be deployed, when end flies
OK, when or needing storage, again can automatic or manual fold, and be cross folding, without departing from fuselage after link arm folding, it is easier to
Packaging carries transport.
It is respectively equipped with drive member on the upside of the distal end of the front end link arm and rear end link arm, the drive member can be with
For motor or other drive devices, the drive member connects power supply by control circuit, and the slurry wing is in drive member
Portion, and be electrically connected with drive member；After switching on power, the rotation of the slurry wing can be driven by drive member.The front end
Link arm and rear end link arm inner hollow, the control line can be by inside by reducing the damage of winding and the exposure of circuit
It is bad.
The distal bottom of the front end link arm and rear end link arm is respectively equipped with forearm leg and postbrachium leg, the branch
When pin is mainly used in taking off, leg is manually or automatically strutted, unmanned plane is stably placed at departure location, and
, being capable of stable landing when unmanned plane lands.Front end link arm and rear end the link arm distal end is respectively equipped with mounting groove so that institute
Stating forearm leg and postbrachium leg can be accommodated in mounting groove, and unmanned plane landing can either be made steady, will not additionally be increased again
Volume.
Further, the body includes head and fuselage, and the front end link arm is located at the left and right sides of head, described
Fuselage is divided into anterior, middle part and rear portion, described anterior for close to head one end, the rear end link arm is located at a left side for fuselage afterbody
Right both sides, plane residing for described two front end link arms are higher than two rear end link arms, and the front end link arm can be folded back upon
It is folded, the rear end link arm can collapsed forward, form cross folding structure.
In order that front end link arm and rear end link arm can interfolded, the present invention will put down residing for two front end link arms
Face is higher than two rear end link arms, and two planes have certain difference in height so that the two complete intersection can be folded to make-up machine
Body, and because the distal end of front end link arm and rear end link arm is provided with drive mechanism and the slurry wing, so front end link arm and rear end
Link arm horizontal range is approximately equal to link arm and the length of fuselage junction to link arm and drive mechanism junction.Work as unmanned plane
When needing expansion, the rear end link arm is first deployed；When unmanned plane, which needs to store, to be folded, the front end link arm first folds.
Preferably, the fuselage and battery component are all elongated, and the cavity both sides are provided with neck, the battery component
Provided with buckle, the battery component is fastened by buckle and cavity inner card cage.
For the cavity on the upside of fuselage, the buckle of the battery tray is elastic construction, is put into battery tray by pressing
In cavity, after release, buckle and neck fasten, and prevent unmanned plane is done in flight course from rotating, tilting etc. when acting, battery
Seat, which drops, triggers danger.
Preferably, the forearm leg and the distal end articulated of front end link arm, postbrachium leg and the distal end of rear end link arm
Be hinged, the length of the forearm leg is more than the length of postbrachium leg, the support end of forearm leg and postbrachium leg is in same
One horizontal plane.
The forearm leg and postbrachium leg are connected with front end link arm and rear end link arm by way of be hinged respectively,
The leg is enabled to realize free folding.Because the height residing for the link arm of front end is higher than rear end link arm, therefore, in order to
Ensure that four support ends are in same level, the present invention sets the length of forearm leg to be more than postbrachium leg length, and forearm
The difference in height of leg and postbrachium leg is equal to the two difference in level.
Further, be provided with the antenna for transmission of control signals in one of front end leg, it is described another
The antenna for being used for image transmission is provided with the leg of front end.
The antenna is arranged on inside leg, because the leg can fold, therefore folding can be achieved in the antenna
Folded, therefore, on the one hand the antenna that the present invention is set can play a part of supporting ground when unmanned plane rises and falls, on the other hand can
Use as antenna, be connected for the remote control antenna with ground, with 2.4g network connections, transmit various instructions.Due to present
Most unmanned plane all realizes the function of shooting, and in the present invention, an antenna is used for photograph unmanned plane in addition
Picture transmission increases Consumer's Experience on mobile terminal, realizing that synchronizing picture shows.
Preferably, the fuselage interior is additionally provided with circuit control panel, and the circuit control panel is located at the cavity bottom.
In order to realize the various intelligent functions of unmanned plane, the fuselage interior is provided with circuit control panel, due on fuselage
Side has been provided with cavity, therefore circuit control panel can only be arranged on the fuselage interior of battery tray bottom.
Further, the bottom surface of the fuselage afterbody is provided with cooling fan and thermovent；The bottom surface of the waist and
Side is respectively equipped with multiple air inlets, and the air inlet forms cooling duct with thermovent.
Because battery can distribute substantial amounts of heat in use, and circuit control panel can also be sent out in the energized state
Heat, a cooling duct is set, on the one hand, the bottom surface of the fuselage afterbody sets cooling fan, and circuit control panel is directly entered
Row radiating, on the other hand, in flight course, air enters unmanned plane from air inlet, is come out from thermovent, forms air pair
Stream, accelerate internal heat dissipating, it is too high to prevent that unmanned plane from generating heat in flight course, causes the damage of parts.
Preferably, the unmanned plane is additionally provided with positioner, and the positioner is located at fuselage afterbody.
Unmanned plane relies primarily on gps satellite positioning in outdoor, and indoor scene is positioned mainly by radar wave indoors,
The space orientation of unmanned plane can be achieved after the positional information of comprehensive at least 4 satellites in GPS.Utilize centered on GPS, auxiliary
Localization method with various sensors is nowadays main flow targeting scheme used by unmanned plane.Unmanned plane needs first before hovering
The clear and definite elevation information and horizontal information of itself is wanted, and in the positioning method based on GPS module, GPS module is mainly responsible for
The horizontal position coordinate of unmanned plane is provided, and its Height position co-ordinate is by barometer, using on different height in general
The change of atmospheric pressure provides to calculate.The setting of positioner can realize a key of unmanned plane make a return voyage, it is out of control make a return voyage automatically,
Fixed point flight, fixed height of fixed point, hovering, it is automatic the function related to GPS location such as follow, and can be unmanned plane realization
The related function of course correction, pose adjustment, fixed high sensor, makes unmanned plane during flying more steady.Because positioner exists
Also certain heat can be distributed in the course of work, therefore, positioner is arranged on fuselage afterbody, beneficial to radiating.
Preferably, the head is formed inverted "L" shaped with fuselage connection end, head lower end is formed the peace of installation head assembly
Fill position.
The head can be used for setting infrared transmitter and infrared remote receiver to realize positioning function, and the head is located at fuselage
Anterior upside, length and the fuselage of the head form inverted "L" shaped structure, an installation position are formed, for installing head group
Part, make whole unmanned plane structure compacter, and protection can be played a part of to head assembly.
Further, the head assembly is provided with the first tie point, the second tie point and the 3rd tie point connection body, institute
The first tie point connection head bottom is stated, second tie point and the 3rd tie point connect fore-body respectively, form stable
Triangle.
In mechanical connection, the connected mode of triangle is relatively stable connection, described in the inverted "L" shaped structure
First tie point connection head bottom, second tie point and the 3rd tie point connect fore-body, form stabilization respectively
Triangle, also first tie point can be connected fore-body, second tie point and the 3rd tie point connect machine respectively
Head bottom, stable triangle is also may make up, therefore stable connection can be achieved in two ways.In order to reduce flight resistance,
The head front end can be gradually reduced, and therefore, if head bottom sets two tie points, can make the distance of two tie points too
Closely, it is therefore preferable that connecting head bottom for the first tie point, second tie point and the 3rd tie point connect fuselage respectively
Front portion, head assembly can either be made to be fully accommodated in installation position, and can is enough stably connected with.
Further, first tie point, the second tie point and the 3rd tie point and body connected mode connect for elasticity
Connect.
Rocked because unmanned plane has in flight course, or unmanned plane do rotate, tilt flight etc. action when can not
It is enough stable, in order to ensure that unmanned plane camera in flight course can photograph stable picture, the head assembly and machine
The connected mode of body is elastic connection, plays a part of buffering, prevents Long-term Vibration from causing head to loosen, and can be ensured as far as possible
The picture of camera shooting is more stable.
Beneficial effects of the present invention：A kind of compact collapsible unmanned plane provided by the invention, passes through battery component and cloud
The integrated setting of platform component and fuselage, and slurry the wing and drive member respectively with front end link arm and the one of rear end link arm
Change design, form the structure of compact, all parts cooperate, and reduce the space-consuming of unmanned plane on the whole；In addition
When unmanned plane is in idle state, i.e., non-state of flight when, the front end link arm and rear end link arm can cross folding,
Substantially fuselage can be bonded, and front end link arm and rear end link arm carry leg, it is not necessary to increase extra support meanss, make
The small volume that foldable integral takes, is easy to store and carries.
Brief description of the drawings
Fig. 1 is the open cube display of compact type folding unmanned plane of the present invention.
Fig. 2 is compact type folding unmanned plane battery tray figure of the present invention.
Fig. 3 is the stereogram that compact type folding unmanned plane of the present invention takes down battery tray.
Fig. 4 is the stereogram that compact type folding unmanned plane of the present invention removes head assembly.
Fig. 5 is the stereogram after compact type folding unmanned plane of the present invention folds.
Fig. 6 is the stereogram of the legs fold of compact type folding unmanned plane of the present invention.
Fig. 7 is compact type folding unmanned plane backsight open cube display of the present invention.
Fig. 8 is compact type folding unmanned plane complete machine stereogram of the present invention.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
Part of the embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
As shown in figure 1, a kind of compact collapsible unmanned plane, including the rear end chain of front end link arm 2, two of body 1, two
Arm 3, drive member 4, the slurry wing 5, head assembly 8 are connect, as shown in Fig. 2 the unmanned plane also includes battery tray 6, battery 7,
As shown in Fig. 2 ~ 3, the cavity 10 for accommodating battery tray 6 is provided with the upside of the body, the battery 7 is in battery tray 6, institute
State battery tray 6 to be removably mounted in cavity 10, the battery 7 is provided with battery interface 71, is provided with and electricity in the cavity 10
Body battery interface 11 corresponding to pond interface 71, makes battery 7 be electrically connected with body 1；
As shown in figure 4, the front end of body 1 is provided with installation position 20, the head assembly 8 is arranged on installation position 20；
As shown in figure 1, described two front end link arms 2 and two rear end link arms 3 are respectively symmetrically located at the both sides of body 1, institute
It is near-end that front end link arm 2 and rear end link arm 3, which are stated, close to one end of body 1, and one end away from body 1 is distal end, before described
Hold the near-end of link arm 2 and rear end link arm 3 be hinged with body 1 so that front end link arm 2 and rear end link arm 3 can be towards machines
Body direction folds；After folding as shown in Figure 5.
As shown in figure 1, it is respectively equipped with drive member 4, institute on the upside of the distal end of the front end link arm 2 and rear end link arm 3
State the slurry wing 5 and be located at the top of drive member 4, and be electrically connected with drive member 4；
As shown in figure 1, the distal bottom of the front end link arm 2 and rear end link arm 3 is respectively equipped with forearm leg 21 and postbrachium
Leg 31, as shown in figure 4, the front end link arm 2 and the distal end of rear end link arm 3 are respectively equipped with mounting groove 30 so that before described
Arm leg 21 and postbrachium leg 31 can be accommodated in mounting groove 30.
As shown in figure 1, the forearm leg 21 and postbrachium leg 31 are remote with front end link arm 2 and rear end link arm respectively
End 3 is be hinged, and the length of the forearm leg 21 is more than the length of postbrachium leg 31, makes the branch of forearm leg 21 and postbrachium leg 31
Support end is in same horizontal plane.
As shown in figure 4, the antenna 40 for transmission of control signals is provided with one of front end leg, it is described another
The antenna 50 for being used for image transmission is provided with individual front end leg.
Further, as shown in fig. 6, the body 1 includes head 12 and fuselage 13, the front end link arm 2 is located at machine
First 12 left and right sides, the fuselage 13 divide for anterior, middle part and rear portion, it is described it is anterior be close to the one end of head 12, after described
Link arm 3 is held to be located at the left and right sides at the rear portion of fuselage 13, higher than two rear ends of plane residing for described two front end link arms 2 link
Arm 3, the front end link arm 2 can fold back, the rear end link arm 3 can collapsed forward, as indicated by arrows in fig. 6, shape
Into intersection foldable structure.
Further, as shown in Fig. 2 ~ 3, the fuselage 13 and battery tray 6 are all elongated, and the both sides of cavity 10 are provided with
Neck 101, the battery tray 6 are provided with buckle 61, and the battery tray 6 is fastened by buckle 61 and the inner card cage 101 of cavity 10.
Further, it is additionally provided with circuit control panel inside the fuselage 13（Not shown in figure）, the circuit control panel sets
In the bottom of battery tray 6.
Further, as shown in fig. 7, the bottom surface at the rear portion of the fuselage 13 is provided with cooling fan 132 and thermovent 133；Institute
State the bottom surface of waist and side and be respectively equipped with multiple air inlets 134, the air inlet 134 is formed with thermovent 133 and cooled down
Passage.
Further, the unmanned plane is additionally provided with positioner（Not shown in figure）, the positioner 9 is located at fuselage 13
Rear portion.
Further, it is shown in dotted line as shown in figure 8, the head 12 and the connection end of fuselage 13 composition are inverted "L" shaped, make
Head lower end forms the installation position of installation head assembly 8.
Further, as shown in fig. 7, the head assembly 8 is provided with the first tie point 81, the second tie point 82 and the 3rd connects
Contact 83 connects body 1, and first tie point 81 connects the bottom of head 12, the tie point 83 of the second tie point 82 and the 3rd
It is anterior that fuselage 13 is connected respectively, forms stable triangle.
Further, first tie point 81, the second tie point 82 and the 3rd tie point 82 are connected with body 1 by Jiao Jiao
Connect.
Embodiment of above is merely illustrative of the technical solution of the present invention and unrestricted, although the preferable embodiment party with reference to more than
The present invention is described in detail formula, it will be understood by those within the art that, can be to technical scheme
Modify or equivalent substitution should not all depart from the spirit and scope of technical solution of the present invention.Those skilled in the art can also be at this
The design that other changes etc. are used in the present invention is done in spirit, without departing from the technique effect of the present invention.These
The change done according to present invention spirit, it should all be included within scope of the present invention.
Claims (10)
1. a kind of compact collapsible unmanned plane, including body, two front end link arms, two rear end link arms, drive member,
Multiple the slurry wing, battery component and head assemblies,
The body includes being used for the body fuselage for protecting internal structure, and the sky for accommodating battery component is provided with the upside of the body
Chamber, the battery component are removably mounted in cavity, and body battery interface, the battery component bottom are provided with the cavity
Portion is provided with battery interface, battery is electrically connected with body；
The body front end is provided with installation position, and the head assembly is arranged on installation position；
Described two front end link arms and two rear end link arms are respectively symmetrically located at the both sides of body,
The front end link arm and rear end link arm are near-end close to one end of body, and one end away from body is distal end,
Characterized in that, the near-end of the front end link arm and rear end link arm is hinged with body so that front end link arm is with after
Link arm is held to be folded respectively towards body direction；
Drive member is respectively equipped with the upside of the distal end of the front end link arm and rear end link arm, the slurry wing is located at drive member
Top, and be electrically connected with drive member；
The distal bottom of the front end link arm and rear end link arm is respectively equipped with forearm leg and postbrachium leg, the front-end chain
Connect arm and link arm distal end in rear end is respectively equipped with mounting groove so that the forearm leg and postbrachium leg can be accommodated in mounting groove
It is interior.
2. compact collapsible unmanned plane according to claim 1, it is characterised in that the body includes head and fuselage,
The front end link arm is located at the left and right sides of head, and the fuselage is divided into anterior, middle part and rear portion, described anterior for close to machine
First end, the rear end link arm are located at the left and right sides of fuselage afterbody, and plane residing for described two front end link arms is higher than two
Individual rear end link arm, the front end link arm can fold back, the rear end link arm can collapsed forward, formed intersect folding
Stack structure.
3. compact collapsible unmanned plane according to claim 2, it is characterised in that the fuselage and battery component are all in length
Bar shaped, the cavity both sides are provided with neck, and the battery component is provided with buckle, and the battery component is by buckle with blocking in cavity
Groove fastens.
4. compact collapsible unmanned plane according to claim 2, it is characterised in that the forearm leg and front end link arm
Distal end articulated, the distal end articulated of postbrachium leg and rear end link arm, the length of the forearm leg is more than the length of postbrachium leg
Degree, makes the support end of forearm leg and postbrachium leg be in same horizontal plane.
5. compact collapsible unmanned plane according to claim 4, it is characterised in that set in one of front end leg
There is the antenna for transmission of control signals, the antenna for being used for image transmission is provided with another described front end leg.
6. compact collapsible unmanned plane according to claim 5, it is characterised in that the bottom surface of the fuselage afterbody is provided with cold
But fan and thermovent；The bottom surface and side of the waist are respectively equipped with multiple air inlets, the air inlet and thermovent
Form cooling duct.
7. compact collapsible unmanned plane according to claim 5, it is characterised in that the unmanned plane is additionally provided with positioning dress
Put, the positioner is located at fuselage afterbody.
8. compact collapsible unmanned plane according to claim 2, it is characterised in that the head is formed with fuselage connection end
It is inverted "L" shaped, head lower end is formed the installation position of installation head assembly.
9. compact collapsible unmanned plane according to claim 8, it is characterised in that the head assembly is provided with the first connection
Point, the second tie point and the 3rd tie point connection body, first tie point connection head bottom, second tie point and
3rd tie point connects fore-body respectively, forms stable triangle.
10. compact collapsible unmanned plane according to claim 9, it is characterised in that first tie point, the second connection
Point and the 3rd tie point and body connected mode are elastic connection.
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| CN201711239041.6A CN107856851A (en) | 2017-11-30 | 2017-11-30 | A kind of compact collapsible unmanned plane |
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| CN201711239041.6A CN107856851A (en) | 2017-11-30 | 2017-11-30 | A kind of compact collapsible unmanned plane |
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