CN205931230U - Frame subassembly and use unmanned aerial vehicle of this frame subassembly - Google Patents
Frame subassembly and use unmanned aerial vehicle of this frame subassembly Download PDFInfo
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- CN205931230U CN205931230U CN201620804009.2U CN201620804009U CN205931230U CN 205931230 U CN205931230 U CN 205931230U CN 201620804009 U CN201620804009 U CN 201620804009U CN 205931230 U CN205931230 U CN 205931230U
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- horn
- main frame
- frame arm
- central part
- folded state
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Abstract
The utility model provides one kind frame subassembly (10) for unmanned aerial vehicle (1), frame subassembly (10) are including central part (12) and first horn (14), first horn one end with the central part is connected, first horn include first portion (141), with third part (143) and connection first portion second portion (142) partial with the third that the central part is connected, the frame subassembly can switch between development condition and fold condition, wherein when fold condition, first portion and third part are located different planes. The utility model provides an adopt the unmanned aerial vehicle of this frame subassembly. Interference when frame subassembly and unmanned aerial vehicle can avoid folding between the part just is favorable to reducing foldamer and amasss.
Description
Technical field
The utility model is related to a kind of housing assembly, more particularly, to a kind of housing assembly for unmanned plane and use this machine
The unmanned plane of frame assembly.
Background technology
Unmanned vehicle is mainly made up of housing assembly, flight control system, dynamical system and load at present, based on housing assembly
Body, remaining each several part is all installed fixation by housing assembly and is intercoupled.Wherein said housing assembly generally include fuselage and from
Multiple horns that fuselage flexes outward.But, the horn flexing outward increased the volume of unmanned plane, is unfavorable for portable.For carrying
Rise portability, a kind of foldable unmanned plane of foldable horn arises at the historic moment.
Currently existing horn fold mechanism, often has after aircraft folded, overall volume is still excessive, leads to inconvenience
Protection, transport in whole machine.
Utility model content
In view of this it is necessary to provide a kind of housing assembly that can further reduce folding rear body size and use
The unmanned plane of this housing assembly.
A kind of housing assembly, for unmanned plane, described housing assembly includes central part and stretches out from described central part
At least two first horns, each described first horn includes away from the Part I of described central part and described central part even
The Part III connecing and the Part II connecting Part I and Part III, described Part I is substantially flat with Part III
OK, described housing assembly can switch between deployed condition and folded state, wherein in folded state, described Part I
It is located at the Different Plane parallel with Part III.
Further, described first horn is arranged in pairs, and the first horn described in each pair is around the roll axle pair of described central part
Claim setting.
Further, the angle in described folded state for first horn described in each pair is less than in described deployed condition
Angle.
Further, in described folded state, described in each pair, the first horn is parallel to each other.
Further, in described deployed condition, described in each pair, the angle of the first horn is obtuse angle.
Further, described housing assembly also includes main frame arm, and described first horn is away from the other end of described central part
Rotationally it is connected on described main frame arm, described main frame arm end is used for assembling for providing thrust to the power of described unmanned plane
System.
Further, described main frame arm is arranged in pairs, and main frame arm described in each pair sets around the roll axial symmetry of described central part
Put.
Further, between being smaller than in described deployed condition in described folded state of main frame arm described in each pair
Away from.
Further, described Part I is connected to the inner side of the closely described central part of described main frame arm rest.
Further, in described folded state, described Part I is located inside described main frame arm.
Further, in described folded state, described Part I is almost parallel with described main frame arm.
Further, in described folded state, described central part is located at Different Plane with described main frame arm.
Further, in described folded state, described main frame arm is located at the over top of described central part or described center
The bottom part down in portion.
Further, described housing assembly also includes the second horn, and second horn one end is connected on described central part, separately
One end is separably attached on described main frame arm.
Further, in described folded state, described second horn and described Part III are arranged substantially in parallel in institute
State main frame arm side.
Further, in described deployed condition, described main frame arm is located at Different Plane with described second horn.
Further, in described folded state, described main frame arm is parallel to each other with described second horn.
Further, in described folded state, described main frame arm and described second horn are located at different two respectively
In individual plane.
Further, in described deployed condition, described main frame arm and described first horn and described second horn shape
Become stable triangle mechanism.
Further, described first horn and described second horn are connected with the middle part of described main frame arm respectively.
Further, described first horn and described second horn are connected with the both ends of described main frame arm respectively.
Further, described second horn is connected on described main frame arm by quick-release and self-locking mechanism.
Further, described quick-release and self-locking mechanism includes being arranged on described second horn and described main frame arm one of both person
On buckling parts and be arranged on the clamping part in both another one.
Further, when changing to described folded state from described deployed condition, described second horn and described main frame
Arm separates.
Further, in described folded state, described second horn is detachably fastened to described central part or main frame
On arm.
Further, described central part or described main frame arm are provided with fixed structure, in described folded state, described solid
Fixed structure is coordinated with described second horn and fixes described second horn on described central part or described main frame arm.
Further, described second horn is arranged in pairs, and the second horn described in each pair is around the roll axle pair of described central part
Claim setting.
Further, described housing assembly also includes the second horn, and described second horn one end is rotationally connected to described
On central part, the other end is provided with for providing thrust to the dynamical system of described unmanned plane.
Further, in pairs, the second horn described in each pair is located at described central part opposite sides to described second horn respectively,
And one end away from described central part of the second horn described in each pair being smaller than in described exhibition in described folded state
Spacing during open state.
Further, in described folded state, described in each pair, the second horn is parallel to each other.
Further, in described deployed condition, described in each pair, the angle of the second horn is obtuse angle.
Further, in described folded state, described second horn, described first horn are respectively positioned on described unmanned plane
The tail side of head side or described unmanned plane.
Further, described housing assembly also includes assisting horn, and described auxiliary horn one end is rotationally connected to described
On central part, the other end is rotationally connected on described main frame arm.
Further, described auxiliary horn is almost parallel with the Part I of described first horn or Part III.
Further, described auxiliary horn is separably attached to described central part or described master by quick-release and self-locking mechanism
On horn.
A kind of unmanned plane, including housing assembly and dynamical system, described dynamical system be arranged on described housing assembly and
For moving described unmanned plane it is characterised in that：Described housing assembly is upper described housing assembly.
After first horn folding of described housing assembly and unmanned plane, Part I and Part III are located at Different Plane, can
Avoid the interference with miscellaneous part and be conducive to reducing folding volume.
Brief description
Fig. 1 is a kind of stereogram of unmanned plane that the utility model embodiment provides.
Fig. 2 is the top view in deployed condition for the housing assembly of the unmanned plane of the utility model embodiment.
Fig. 3 is the side view of the housing assembly shown in Fig. 2.
Fig. 4 is the top view in folded state for the housing assembly of the unmanned plane of the utility model embodiment.
Fig. 5 is the sectional view along V-V line for the housing assembly shown in Fig. 4.
Fig. 6 is the top view of the housing assembly of the unmanned plane of the utility model second embodiment.
Fig. 7 is the top view in folding process for the housing assembly of the unmanned plane of the utility model second embodiment.
Main element symbol description
| Unmanned plane | 1 |
| Housing assembly | 10 |
| Central part | 12 |
| Buckle | 120 |
| First horn | 14 |
| Part I | 141 |
| Part II | 142 |
| Part III | 143 |
| Second horn | 16 |
| Clamping part | 160 |
| Main frame arm | 18 |
| Buckling parts | 180 |
| Dynamical system installation portion | 19 |
| Auxiliary horn | 15 |
Following specific embodiment will further illustrate the utility model in conjunction with above-mentioned accompanying drawing.
Specific embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely description is it is clear that described embodiment is only a part of embodiment of the utility model rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of making creative work
The every other embodiment being obtained, broadly falls into the scope of the utility model protection.
It should be noted that when assembly is referred to as " being fixed on " another assembly, it can be directly on another assembly
Or can also there is assembly placed in the middle.When an assembly is considered as " connection " another assembly, it can be directly connected to
To another assembly or may be simultaneously present assembly placed in the middle.When an assembly is considered as " being arranged at " another assembly, it
Can be to be set directly on another assembly or may be simultaneously present assembly placed in the middle.Term as used herein is " vertical
", " level ", "left", "right" and similar statement for illustrative purposes only.
Unless otherwise defined, all of technology used herein and scientific terminology are led with belonging to technology of the present utility model
The implication that the technical staff in domain is generally understood that is identical.In term used in the description of the present utility model it is simply herein
The purpose of description specific embodiment is it is not intended that in limiting the utility model.Term as used herein " and/or " include
The arbitrary and all of combination of one or more related Listed Items.
The utility model provides a kind of unmanned plane, and described unmanned plane can be used for any suitable environment, for example in the air（Example
The aircraft mixing with rotor as rotor craft, Fixed Wing AirVehicle or fixed-wing）, in water（Example, ship or submarine）, on ground
On face（Example, motorcycle, automobile, truck, bus, train etc.）, in space（Example, space shuttle, satellite or detector）, or
In underground（Such as subway）, or any combination of above-mentioned environment.
Below in conjunction with the accompanying drawings, some embodiments of the present utility model are elaborated.In the case of not conflicting, under
Feature in the embodiment stated and embodiment can be mutually combined.
Refer to Fig. 1, unmanned plane 1 includes housing assembly 10 and is arranged on the dynamical system on housing assembly 10（Figure is not
Show）.
Described dynamical system can be used for making described unmanned plane 1 take off, land, hover, and in the air with regard to three translations certainly
By degree and three rotary freedom motions.In certain embodiments, described dynamical system may include one or more rotors（Not
Illustrate）And drive mechanism（Such as motor）.Described rotor may include the one or more rotor blades connecting to a rotating shaft.Institute
State rotor blade or rotating shaft can be driven by a suitable drive mechanism and rotate.Described rotor can be one, two, three,
Four, five, six, seven, eight or more.Described rotor can with respect to described unmanned plane 1 level, vertical or other
What suitably angle setting.The angle of described rotor can be fixing or variable.The rotating shaft of the described rotor being oppositely arranged it
Between distance can be any appropriately distance, e.g., less than be equal to 2 meters, or be less than or equal to 5 meters.Alternatively, described distance can
With between 40 centimetres to 1 meter, from 10 centimetres to 2 meters, or from 5cm to 5 meter.Described dynamical system can be any
Suitable Motor drive, such as direct current generator（Example：Brush motor or brushless electric machine）Or alternating current generator.In certain embodiments,
Described motor can be configured to drive rotor blade.
Described housing assembly 10 may include central part 12, multiple first horn 14, multiple second horn 16 and main frame arm 18.
One end of each described first horn 14（Near-end）It is connected with described central part 12, the other end（Far-end）With described main frame arm 18
It is connected.One end of each described second horn 16（Near-end）It is connected with described central part 12, the other end（Far-end）With described
Main frame arm 18 is connected.
It is understood that in certain embodiments, described unmanned plane 100 may include arbitrarily an appropriate number of first horn
14th, the second horn 16 and main frame arm 18, for example, 1,2,3,4 or more, in other embodiment, each institute
State described first horn 14 that main frame arm 18 connected and the quantity of described second horn 16 all can suitably change, for example,
Each described main frame arm 18 can connect two, three or multiple described first horn 14/ second horn 16.In this enforcement
In example, described housing assembly 10 includes 14, two the second horns 16 of two the first horns and two main frame arms 18.Two described
Described second horn 16 of one horn 14, two all can symmetrically or asymmetrically be arranged around described central part 12.The present embodiment
In, two described 14, two described second horns 16 of first horn all roll axles symmetric around described central part 12 are arranged.
Main frame arm 18 described in two is symmetrically disposed in the roll axle both sides of described central part 12.Preferably, described first horn 14 and institute
State the second horn 16 equal with described central part 12 angulation respectively, so that the operation of described unmanned plane is more stable.
Alternatively, described first horn 14 all can rotationally be connected with described central part 12 with described second horn 16 so that with institute
State the height adjustable that the main frame arm 18 that the first horn 14 is connected is with respect to described central part 12 with the second horn 16.Described main frame
Arm 18 can be located at the bottom part down of described central part 12 or the over top of described central part 12 or with described central part 12 substantially
Concordantly.Described first horn 14 can be arranged on heading or the head near described unmanned plane 100 of described unmanned plane 100
Direction, correspondingly, described second horn 16 is positioned close to the tail direction of described unmanned plane.It is understood that at other
In embodiment, described first horn 14 can be positioned close to the tail direction of described unmanned plane 100, correspondingly, described
Two horns 16 are positioned close to the heading of described unmanned plane.
On described central part 12, control system can be set（For example, flight control system）To control flying of described unmanned plane 1
OK.In certain embodiments, described control system is based on following one or more：The position of described unmanned plane 1, described unmanned plane
1 direction, the current state of described unmanned plane 1, the sensor of time or described unmanned plane 1 or load are sensed the number obtaining
According to automatically controlling described unmanned plane 1.
Alternatively or can in combination, described control system may include a receiver being arranged on described unmanned plane 1
Or others communication module, for receive user instruction, for example, from remote terminal reception user instruction.By described receiver
The described user instruction being received is used for controlling described dynamical system, and described dynamical system is used for driving described unmanned plane to run,
For example take off, fly, spiral or land.
Described central part 12 can be used for supporting load.Described load may be connected to the arbitrarily suitable portion of described central part 12
Position, such as, the bottom of described central part 12 or downside.Connection between described load and described central part 12 can be fixing company
Connect, or, described load can described central part 12 activity relatively.
Described load could be for executing the load of specific function, such as, sensor, transmitter, instrument, instrument, behaviour
Vertical device, or other functions device.For example, described load can be a video capturing device.In some situations, described image obtains
Take device can be in the camera of described central part 10 lower section.Described camera can rotate relative to described central part 12（For example, lead to
Cross a carrier or other mounting platforms, concrete such as head）To obtain the image at multiple visual angles.
On described main frame arm 18, described dynamical system can be set.As shown in figure 1, the end of described main frame arm 18 be provided with dynamic
Force system installation portion 19, for installing described dynamical system thereon.It is understood that every one end of described main frame arm 18
One or two dynamical system can be set.
Buckle 120 is provided with described central part 12, described buckle 120 can be in folded state in described second horn 16
When fasten with described second horn 16, it is to avoid the second horn arbitrarily swings after folding.
See also shown in Fig. 2 and Fig. 3, be the figure that described housing assembly 10 is in deployed condition.Described first horn
14 far-end is rotatably fixed on described main frame arm 18 side by fixing devices such as hinges.In described deployed condition, two institutes
State the first horn 14 to extend to the heading of described unmanned plane, and described in two, first horn 16 is to the tail side of described unmanned plane
To extension.It is appreciated that in other embodiments, the first horn 14 described in two extends to the tail direction of described unmanned plane,
And the first horn 16 described in two extends to the heading of described unmanned plane.Under described deployed condition, described first horn 14
Angulation with described main frame arm 18 is acute angle, and described in two, between the first horn 14, angulation is obtuse angle.Described
The far-end of two horns 16 is fixed on described main frame arm 18 by quick-release and self-locking mechanism.So that described main frame arm 18 when folding
Stagger with described second horn 16, described second horn 16 is arranged on the back side of described main frame arm 18, that is, with described first horn
The face that 16 positions being fixed on described main frame arm 18 are located is adjacent.Turn under deployed condition described, described second horn 16
With described main frame arm 18 not in same plane.Described in two, between the second horn 16, angulation is obtuse angle, described second horn
Between 16 and described main frame arm 18, angulation is acute angle.In described deployed condition, described first horn 14, described second machine
Form firm triangular structure between arm 16 and described main frame arm 18.Preferably, described first horn 14 and described second machine
Arm 16 is roughly equal with described central part 12 angulation respectively, thus described first horn 14, described second horn 16 with
The triangle substantially isosceles triangle being formed between described main frame arm 18.
Described first horn 14 includes Part I 141, Part II 142 and the Part III 143 being sequentially connected.Wherein
One end of described Part I 141 is connected with described main frame arm 18, and the other end is connected with one end of described Part II 142；Institute
The other end stating Part II 142 is connected with one end of described Part III 143；The other end of described Part III 143 and institute
State central part 12 and rotate and connect.Preferably, described Part I 141 and described Part III 143 are almost parallel.In described expansion
State, described Part I 141 and described Part III 143 are located at Different Plane.
Described quick-release and self-locking mechanism includes the clamping part 160 being arranged on described second horn 16 and is arranged on described main frame
Described second horn 16 is locked by the buckling parts 180 on arm 18 by the cooperation of described clamping part 160 and buckling parts 180
On described main frame arm 18.It is understood that in other embodiments, described quick-release and self-locking mechanism can be any suitable can
The fit structure departing from, such as arrange clamping part on described main frame arm 18 and arrange buckling parts on described second horn 16,
Fit system is also not necessarily limited to buckle, such as interference, screws togather, as long as described second horn 16 can be made to be detachably fastened to institute
State on main frame arm 18.
Refer to shown in Fig. 1 and Fig. 3, described Part II 142 is with described Part I 141, described Part III 143 not
Point-blank, with described Part I 141, described Part III 143 all at an angle, it is greater than 90 degree and is less than
The obtuse angle of 180 degree, so that when described unmanned plane 1 folds, described Part I 141 and described Part III 143 are located at not
Isoplanar.The structure of described first horn 14 makes central part 12 with main frame arm 18 not at grade, it is to avoid center during folding
Portion 12 is interfered with main frame arm 18.
Refer to shown in Fig. 4 and Fig. 5, be the top view after described housing assembly 10 folds and sectional view.Folded state
In top view, described second horn 16 is folded in the back side of described main frame arm 18, is blocked by described main frame arm 18.Described first
Horn 14 is folded in inside described main frame arm 18（I.e. near the side of described central part 12）.Under described folded state, described
Part I 141 and described main frame arm 18 angulation are less than described Part I 141 and described main frame arm during deployed condition
18 angulations.In certain embodiments, under described folded state, described Part I 141 is with described main frame arm 18 substantially
Inner side that is parallel and being substantially fitted in described main frame arm 18, i.e. described Part I 141 and described main frame arm 18 angulation
Essentially a zero or close to zero.Described Part III 143 is substantially concordant with described second horn 16, so that respectively with described
The described central part 12 that one horn 14 and described second horn 16 connect be in Part III 143 with described first horn 14 and
The almost parallel plane of described second horn 16.In described folded state, described main frame arm 18 and described Part III 143 and institute
State the second horn 16 and be located at Different Plane, that is, be located at Different Plane with described central part 12, it is flat that described main frame arm 18 is located
Face can be located at the bottom part down of described central part 12 or the over top of described central part 12.Described two main frame arms 18 are near described
Central part 12 both sides, compare deployed condition, in a folded configuration being smaller than in deployed condition between described two main frame arms 18
Under two main frame arms 18 between spacing.Under described folded state, described in two, the first horn 14 is arranged substantially in parallel described
Between two main frame arms 18, that is, described in two, between the first horn 14, angulation is essentially a zero.Compare deployed condition, in rugosity
During state, described in two, between the first horn 14, angulation is less than formed angle between the first horn 14 described in two during deployed condition
Degree.Under described folded state, the second horn 16 described in two is arranged substantially in parallel the Part III in the first horn 14 described in two
143 outside, described in two, the angle between the second horn 16 is essentially a zero.Under described folded state, the second horn described in two
16 far-end is arranged at the head side of described unmanned plane 100, is located at described central part 12 with described first horn 14
Homonymy.It is appreciated that when described first horn 14 is located at the tail side of described central part 12, the second horn 16 described in two
Far-end is also similarly positioned in the tail side of described central part 12 in described folded state.Under described folded state, described in two
It is smaller than the spacing between the far-end of the second horn 16 described in deployed condition two between the far-end of two horns 16.One
In a little embodiments, under folded state, the spacing between the far-end of the second horn 16 described in two is roughly equivalent to described central part 12 and exists
Perpendicular to the axial width of its roll.
In certain embodiments, described Part I 141 is almost parallel with described Part III 143.Due to folded state
Under described Part I 141 almost parallel with described main frame arm 18, described Part III 143 is substantially flat with described second horn 16
OK, so that under folded state, main frame arm 18 described in two is almost parallel with the second horn described in two, and it is located at different flat respectively
Face.
When launching to deployed condition from folded state, first described first horn 14 and described main frame arm 18 are expanded to pre-
Positioning is put（Described precalculated position can be that described housing assembly 10 is located at the first horn 14 and described main frame arm described in during deployed condition
18 locations）, then again the far-end of the second horn 16 is exited at the buckle 120 of described central part 12, and near around it
End rotary expansion is to specified location（Described specified location can be that described housing assembly 10 is located at the second machine described in during deployed condition
Arm 16 location）, finally again the far-end of described second horn 16 is passed through quick-release and self-locking mechanism and locks in described main frame arm
On 18, thus completing the expansion of described housing assembly 10.
Similarly, when folding described housing assembly 10, first by the far-end of described second horn 16 from described main frame arm 18
Upper unblock, and so that described second horn 16 is rotated to the position almost parallel with described main frame arm 18 relative to described central part 12,
And the far-end of described second horn 16 and the buckle 120 of described central part 12 are interlocked, then make described two main frame arms
18 is close to described central part 12, until it reaches folded state.Now, the Part I 141 of described first horn 14 is fitted in
Inside described main frame arm 18, the Part III 143 of described first horn 14 is almost parallel with described second horn 16.
Because described first horn 14 is case of bending so that when described housing assembly 10 folds, described main frame arm 18 with
The Part III 143 of described first horn 14 and described second horn 16 be located at Different Plane, it is to avoid main frame arm 18 with described
The interference of the second horn 16 and main frame arm 18 are interfered with central part 12.And described first horn 14 and described second after folding
Horn 16 is defined in the width range that described two main frame arms 18 are limited, the housing assembly width after folding substantially with described
Quite, thickness is roughly equivalent to the thickness after described main frame arm 18 is superimposed, body with described second horn 16 to the width of central part 12
Long-pending relatively small.
It is understood that described quick-release and self-locking mechanism is alternatively arranged on the sleeved part on the second horn 16, such as half
Open sleeved part, in deployed condition, is set on described main frame arm 18；From described deployed condition to described folded state
During folding, described second horn 16 departs from from described main frame arm 18；And in described folded state, described second horn 16 is again
Secondary it is set on described main frame arm 18 to be stabilized in described folded state；When being expanded to described deployed condition from folded state,
Described second horn 16 is set in described main frame arm 18 after departing from from described main frame arm 18 and being expanded to described specified location again
On with lock in described deployed condition.
Refer to shown in Fig. 6 and Fig. 7, be the unmanned plane housing assembly top view of the utility model second embodiment.Phase
Relatively go up described embodiment, described housing assembly also includes assisting horn 15.Described auxiliary horn 15 one end is connected to described
On central part 12, one end is connected on described main frame arm 18.Described auxiliary horn 15 quantity can for one, two, three or
Multiple.Preferably, described auxiliary horn 15 is almost parallel with the Part I 141 of described first horn 14 and Part III 143.
Described auxiliary horn 15 and described first horn 14, described main frame arm 18 form bar linkage structure, assist described first horn and institute
State expansion and the folding of main frame arm.It is understood that for ease of launching and folding, described auxiliary horn 15 can also be using fast
Tear self-locking mechanism open to be detachably fastened on described main frame arm 18 or on described central part 12.
It is understood that in certain embodiments, described second horn 16 can omit, and described first horn 14 can set
Put at the geometric center of described main frame arm 18.Between described central part 12 and described first horn 14, described first horn 14
The company that and described main frame arm 18 between, locked mechanism all can be set to lock between described central part 12 and described first horn 14
Connect and described first horn 14 and described main frame arm 18 between connection.It is appreciated that although institute in embodiment shown in the drawings
State the first horn 14, the second horn 16 is separately positioned on the relative both ends of described main frame arm 18, but in other embodiment
In, described first horn 14, described second horn 16 all may be provided at the middle part of described main frame arm 18.
It is understood that in certain embodiments, described main frame arm 18 can omit, and described dynamical system can directly set
Put the distal portion in described first horn 14 and described second horn 16.
In the above-described embodiments, described first horn 14, described second horn 16, described secondary arm 15 are all referred to alternatively as
Prop up horn, the quantity of described horn can be not limited to the quantity in described embodiment, can be multiple.Described main frame arm 18 passes through institute
State a horn to be connected with described central part 12.Multiple horns can be arranged around the roll axial symmetry of described central part 12, Duo Gesuo
State main frame arm 18 also to arrange around the roll axial symmetry of described central part 12.In certain embodiments, the plurality of horn becomes
To setting, described in each pair, a horn is arranged around the roll axial symmetry of described central part 12.The plurality of main frame arm is arranged in pairs, often
Described main frame arm is arranged around the roll axial symmetry of described central part 12.
It is understood that in the above-described embodiments, in folded state, described buckle may be provided at described main frame arm 18
On, described second horn 16 can be fastened by buckle and described main frame arm 18 to consolidate described second horn 16 further in described
Folded state.It is understood that described buckle 120 could alternatively be other arbitrarily suitable fixed structures, as long as can make
Described second horn 16 is detachably fastened on described central part 12 or described main frame arm 18, such as snap fit and draw-in groove
Cooperation etc..
In addition, for the person of ordinary skill of the art, it can be made according to technology design of the present utility model
It various corresponding change and deformation, and all these change all should belong to the protection model of the utility model claim with deformation
Enclose.
Claims (30)
1. a kind of housing assembly, for unmanned plane, described housing assembly includes central part and stretches out from described central part
At least two first horns it is characterised in that：Each described first horn includes the Part I away from described central part and institute
State the Part III of central part connection and the Part II connecting Part I and Part III, described Part I and the 3rd
Divide almost parallel, described housing assembly can switch between deployed condition and folded state, wherein in folded state, described
Part I is located at the Different Plane parallel with Part III.
2. housing assembly as claimed in claim 1 it is characterised in that：Described first horn is arranged in pairs, first described in each pair
Horn is arranged around the roll axial symmetry of described central part.
3. housing assembly as claimed in claim 2 it is characterised in that：First horn described in each pair is in described folded state
Angle is less than the angle in described deployed condition.
4. housing assembly as claimed in claim 3 it is characterised in that：In described folded state, the first horn described in each pair
It is parallel to each other；
And/or, in described deployed condition, described in each pair, the angle of the first horn is obtuse angle.
5. housing assembly as claimed in claim 1 it is characterised in that：Described housing assembly also includes main frame arm, and described first
Horn is rotationally connected on described main frame arm away from the other end of described central part, and described main frame arm end is used for for assembling
There is provided thrust to the dynamical system of described unmanned plane.
6. housing assembly as claimed in claim 5 it is characterised in that：Described main frame arm is arranged in pairs, main frame arm described in each pair
Roll axial symmetry setting around described central part.
7. housing assembly as claimed in claim 6 it is characterised in that：Between described in each pair, main frame arm is in described folded state
Away from less than the spacing in described deployed condition.
8. housing assembly as claimed in claim 7 it is characterised in that：Described Part I is connected to the nearly institute of described main frame arm rest
State the inner side of central part.
9. housing assembly as claimed in claim 8 it is characterised in that：In described folded state, described Part I is located at
Inside described main frame arm.
10. housing assembly as claimed in claim 9 it is characterised in that：In described folded state, described Part I and institute
State main frame arm almost parallel.
11. housing assemblies as claimed in claim 10 it is characterised in that：In described folded state, described central part and institute
State main frame arm and be located at Different Plane.
12. housing assemblies as claimed in claim 5 it is characterised in that：In described folded state, described main frame arm is located at described
The over top of central part or the bottom part down of described central part.
13. housing assemblies as claimed in claim 5 it is characterised in that：Described housing assembly also includes the second horn, the second machine
Arm one end is connected on described central part, and the other end is separably attached on described main frame arm.
14. housing assemblies as claimed in claim 13 it is characterised in that：In described folded state, described second horn with
Described Part III is arranged substantially in parallel in described main frame arm side.
15. housing assemblies as claimed in claim 13 it is characterised in that：In described deployed condition, described main frame arm and institute
State the second horn and be located at Different Plane.
16. housing assemblies as claimed in claim 13 it is characterised in that：In described folded state, described main frame arm and institute
State the second horn to be parallel to each other；
Or, in described folded state, described main frame arm and described second horn are located in two different planes respectively.
17. housing assemblies as claimed in claim 13 it is characterised in that：In described deployed condition, described main frame arm and institute
State the first horn and described second horn forms stable triangle mechanism.
18. housing assemblies as claimed in claim 13 it is characterised in that：Described first horn and described second horn are respectively
It is connected with the middle part of described main frame arm；
Or, described first horn and described second horn are connected with the both ends of described main frame arm respectively.
19. housing assemblies as claimed in claim 13 it is characterised in that：Described second horn is connected by quick-release and self-locking mechanism
On described main frame arm.
20. housing assemblies as claimed in claim 19 it is characterised in that：Described quick-release and self-locking mechanism includes being arranged on described
Buckling parts on two horns and described main frame arm one of both person and be arranged on the clamping part in both another one.
21. housing assemblies as claimed in claim 13 it is characterised in that：From described deployed condition to described folded state
During conversion, described second horn is separated with described main frame arm.
22. housing assemblies as claimed in claim 13 it is characterised in that：In described folded state, described second horn can
Discretely it is fixed on described central part or main frame arm.
23. housing assemblies as claimed in claim 22 it is characterised in that：It is provided with solid on described central part or described main frame arm
Fixed structure, in described folded state, described fixed structure and described second horn coordinate and fix described second horn in described
On central part or described main frame arm.
24. housing assemblies as claimed in claim 13 it is characterised in that：Described second horn is arranged in pairs, described in each pair
Two horns are arranged around the roll axial symmetry of described central part.
25. housing assemblies as claimed in claim 1 it is characterised in that：Described housing assembly also includes the second horn, and described
Two horn one end are rotationally connected on described central part, and the other end is provided with for providing thrust to the power of described unmanned plane
System.
26. housing assemblies as claimed in claim 25 it is characterised in that：Described second horn is paired, the second machine described in each pair
Arm is located at described central part opposite sides respectively, and one end away from described central part of the second horn described in each pair is described
The spacing being smaller than in described deployed condition during folded state.
27. housing assemblies as claimed in claim 25 it is characterised in that：In described folded state, the second machine described in each pair
Arm is parallel to each other；
And/or, in described deployed condition, described in each pair, the angle of the second horn is obtuse angle；
And/or, in described folded state, described second horn, described first horn are respectively positioned on the head one of described unmanned plane
The tail side of side or described unmanned plane.
28. housing assemblies as claimed in claim 5 it is characterised in that：Described housing assembly also includes assisting horn, described auxiliary
Horn one end is helped rotationally to be connected on described central part, the other end is rotationally connected on described main frame arm.
29. housing assemblies as claimed in claim 28 it is characterised in that：Described auxiliary horn and the first of described first horn
Part or Part III are almost parallel；
Or, described auxiliary horn is separably attached on described central part or described main frame arm by quick-release and self-locking mechanism.
A kind of 30. unmanned planes, including housing assembly and dynamical system, described dynamical system be arranged on described housing assembly and
For moving described unmanned plane it is characterised in that：Described housing assembly is the frame group described in any one of claim 1 to 29
Part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620804009.2U CN205931230U (en) | 2016-07-28 | 2016-07-28 | Frame subassembly and use unmanned aerial vehicle of this frame subassembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620804009.2U CN205931230U (en) | 2016-07-28 | 2016-07-28 | Frame subassembly and use unmanned aerial vehicle of this frame subassembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205931230U true CN205931230U (en) | 2017-02-08 |
Family
ID=57927508
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620804009.2U Expired - Fee Related CN205931230U (en) | 2016-07-28 | 2016-07-28 | Frame subassembly and use unmanned aerial vehicle of this frame subassembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205931230U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108495786A (en) * | 2017-08-31 | 2018-09-04 | 深圳市大疆创新科技有限公司 | The deformation rack and aircraft of aircraft |
| CN108513555A (en) * | 2017-02-24 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Foldable rack, rack components and unmanned vehicle |
| CN108513559A (en) * | 2017-08-29 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Rack and multi-rotor unmanned aerial vehicle |
| CN109896005A (en) * | 2019-03-26 | 2019-06-18 | 舟山职业技术学校 | A kind of structure improved quadrotor |
| CN110844058A (en) * | 2020-01-06 | 2020-02-28 | 天津微深科技有限公司 | Modular morphing aircraft |
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2016
- 2016-07-28 CN CN201620804009.2U patent/CN205931230U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108513555A (en) * | 2017-02-24 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Foldable rack, rack components and unmanned vehicle |
| CN108513555B (en) * | 2017-02-24 | 2021-11-05 | 深圳市大疆创新科技有限公司 | Foldable rack, rack assembly and unmanned aerial vehicle |
| CN108513559A (en) * | 2017-08-29 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Rack and multi-rotor unmanned aerial vehicle |
| WO2019041126A1 (en) * | 2017-08-29 | 2019-03-07 | 深圳市大疆创新科技有限公司 | Frame and multi-rotor unmanned aerial vehicle |
| CN108513559B (en) * | 2017-08-29 | 2021-03-19 | 深圳市大疆创新科技有限公司 | Frame and many rotor unmanned aerial vehicle |
| CN112793761A (en) * | 2017-08-29 | 2021-05-14 | 深圳市大疆创新科技有限公司 | Frame and unmanned aerial vehicle |
| CN108495786A (en) * | 2017-08-31 | 2018-09-04 | 深圳市大疆创新科技有限公司 | The deformation rack and aircraft of aircraft |
| WO2019041221A1 (en) * | 2017-08-31 | 2019-03-07 | 深圳市大疆创新科技有限公司 | Deformable frame of aerial vehicle and aerial vehicle |
| CN108495786B (en) * | 2017-08-31 | 2022-01-28 | 深圳市大疆创新科技有限公司 | Deformation frame of aircraft and aircraft |
| CN109896005A (en) * | 2019-03-26 | 2019-06-18 | 舟山职业技术学校 | A kind of structure improved quadrotor |
| CN109896005B (en) * | 2019-03-26 | 2023-09-15 | 舟山职业技术学校 | Four rotor crafts of improvement structure |
| CN110844058A (en) * | 2020-01-06 | 2020-02-28 | 天津微深科技有限公司 | Modular morphing aircraft |
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