CN205971817U - A unmanned aerial vehicle that is used for unmanned aerial vehicle's undercarriage subassembly and has it - Google Patents
A unmanned aerial vehicle that is used for unmanned aerial vehicle's undercarriage subassembly and has it Download PDFInfo
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- CN205971817U CN205971817U CN201620520111.XU CN201620520111U CN205971817U CN 205971817 U CN205971817 U CN 205971817U CN 201620520111 U CN201620520111 U CN 201620520111U CN 205971817 U CN205971817 U CN 205971817U
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- lift arm
- undercarriage
- unmanned plane
- landing gear
- buffer unit
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Abstract
The utility model discloses an unmanned aerial vehicle's undercarriage subassembly and the unmanned aerial vehicle who has it for unmanned aerial vehicle's undercarriage subassembly, include: base and undercarriage, undercarriage include a lift arm and the 2nd lift arm, but a lift arm's first end pivot ground connect on the base, but a lift arm's second end do not link to each other with the 2nd lift arm pivot ground, a lift arm is constructed into to the undercarriage and the 2nd lift arm is movable between the retracted position central with being close to the base of the expansion position of keeping away from the base center. According to the utility model discloses a life -span that is used for unmanned aerial vehicle's undercarriage subassembly, and unmanned aerial vehicle can pack up the undercarriage when flight, can launch the undercarriage when descending, has reduced the whole volume when unmanned aerial vehicle flies, has greatly reduced potential safety hazard and windage, has improved unmanned aerial vehicle's security, and has improved the stationarity when unmanned aerial vehicle lands, has protected the fuselage effectively, has lengthened unmanned aerial vehicle.
Description
Technical field
The utility model is related to vehicle technology field, especially relates to a kind of landing gear assembly for unmanned plane and tool
There is its unmanned plane.
Background technology
In correlation technique, landing gear assembly is aircraft such as unmanned plane etc. to be parked, slides on ground, takeoff and anding is sliding when running
For supporting aircraft gravity, bear the device of respective loads.However, the undercarriage in landing gear assembly can not be folded back into mostly
Receive, take up room larger, increased the hidden danger in flight course.
Utility model content
The utility model is intended at least solve one of technical problem present in prior art.For this reason, it is of the present utility model
One purpose is to propose a kind of landing gear assembly for unmanned plane, this be used for unmanned plane landing gear assembly can with folding and unfolding,
Reduce the volume in flight for the unmanned plane, safe and windage is little.
Another purpose of the present utility model is to propose a kind of unmanned plane with above-mentioned landing gear assembly.
According to the utility model first aspect for unmanned plane landing gear assembly, including：Pedestal；And undercarriage, institute
State undercarriage and include the first lift arm and the second lift arm, the first end of described first lift arm is pivotably coupled to described base
On seat, the second end of described first lift arm is pivotly connected with described second lift arm, and described undercarriage is configured to described
First lift arm and described second lift arm are in the expanded position away from described base central and the receipts adjacent to described base central
Rise movable between position, described undercarriage is multiple and the plurality of undercarriage being provided at circumferentially spaced along described pedestal.
According to the landing gear assembly for unmanned plane of the present utility model, by by first lift arm and second of undercarriage
Lift arm is configured to the first lift arm and the second lift arm receipts in the expanded position away from base central and neighbouring base central
Rise movable between position.Thus, unmanned plane can pack up undercarriage in flight, can launch undercarriage in landing, from
And reduce overall volume during unmanned plane during flying, significantly reduce potential safety hazard and windage, improve the safety of unmanned plane
Property, and improve stationarity during UAV Landing, it is effectively protected fuselage, extend the life-span of unmanned plane.
In addition, according to the landing gear assembly for unmanned plane of the present utility model, can also have the technology added as follows
Feature：
According to some embodiments of the present utility model, described in when described undercarriage is located at described expanded position, second rises and falls
The free end of arm is less than the bottom surface of described pedestal.
According to some embodiments of the present utility model, described in when described undercarriage is located at described stowed position, second rises and falls
The free end of arm is higher than the top surface of described pedestal.
Further, the described landing gear assembly for unmanned plane also includes：Buffer unit, described buffer unit is located at institute
State between the first lift arm and described second lift arm, described buffer unit is configured to when described UAV Landing be described nothing
Man-machine offer buffering.
According to some embodiments of the present utility model, one of in described first lift arm and described second lift arm
On be formed with guide, the first end of described buffer unit is movably arranged in described guide, the of described buffer unit
Two ends are connected with another in described first lift arm and described second lift arm.
Specifically, the first end of described buffer unit is provided with the first grab, and the second end of described buffer unit is provided with second
Grab, described another in described first lift arm and described second lift arm is provided with snap ring, and described first grab is removable
It is located in described guide, described second grab is connected with described snap ring dynamicly.
Alternatively, described buffer unit is spring.
Specifically, described undercarriage is movable between described expanded position and described stowed position by driving means,
Wherein said driving means include：Motor, described motor is located on described pedestal, and described motor is provided with output shaft；With driven
Assembly, described driven subassembly is respectively connected with described output shaft and described first lift arm.
Further, described driving means also include traction component, and described traction component is located on described undercarriage, described
Traction component is configured to drive described second to rise and fall when described expanded position moves to described stowed position when described undercarriage
Arm pivots towards the direction of neighbouring described first lift arm with respect to described first lift arm, when described undercarriage is packed up from described
Position drives described second lift arm to be directed away from described with respect to described first lift arm when moving to described expanded position
The direction of one lift arm pivots.
Specifically, described traction component includes：First traction component, described first traction component includes the first line wheel and
One draught line, described first line wheel is located on described undercarriage, and the first end of described first draught line is fixed on described second
Fall on arm, the second end of described first draught line bypasses described first line wheel and is wrapped on described output shaft.
Further, described traction component also includes the second traction component, and described second traction component includes the second line wheel
With the second draught line, described second line wheel is located on described undercarriage, and the first end of described second draught line is fixed on described
On two lift arms, the second end of described second draught line bypasses described second line wheel and is wrapped on described output shaft, and described first
The draught line and described second draught line winding direction on described output shaft is contrary.
Alternatively, described first draught line is located at the top of described first lift arm and described second lift arm, and described the
Two draught lines are located at the lower section of described first lift arm and described second lift arm.
Specifically, described driven subassembly includes intermeshing driving gear and driven gear, described driving gear and institute
State output shaft to fix, described driven gear is connected with described first lift arm.
According to the unmanned plane of the utility model second aspect, including according to the above-mentioned first aspect of the utility model
Landing gear assembly for unmanned plane.
Additional aspect of the present utility model and advantage will be set forth in part in the description, partly will be from explained below
In become obvious, or recognized by practice of the present utility model.
Brief description
Above-mentioned and/or additional aspect of the present utility model and advantage will from reference to the description to embodiment for the accompanying drawings below
Become obvious and easy to understand, wherein：
Fig. 1 is for the structural representation of the landing gear assembly of unmanned plane according to the utility model embodiment, wherein rises
The frame that falls is located at expanded position；
Fig. 2 is the top view of the landing gear assembly for unmanned plane shown in Fig. 1；
Fig. 3 is another structural representation according to the utility model embodiment for the landing gear assembly of unmanned plane,
Wherein undercarriage is located at stowed position；
Fig. 4 is the top view of the landing gear assembly for unmanned plane shown in Fig. 3.
Reference：
Landing gear assembly 100,
Pedestal 1,
Undercarriage 2, the first lift arm 21, snap ring 211, the second lift arm 22, guide 221, the 3rd grab 222, the 4th
Grab 223,
Buffer unit 3, the first grab 31, the second grab 32,
Motor 4, driving gear 51, driven gear 52, driven gear shaft 521, output shaft 6,
First traction component 7, the first line wheel 71, the first draught line 72,
Second traction component 8, the second line wheel 81, the second draught line 82.
Specific embodiment
Embodiment of the present utility model is described below in detail, the example of described embodiment is shown in the drawings, wherein ad initio
To the element that same or similar label represents same or similar element or has same or like function eventually.Below by ginseng
The embodiment examining Description of Drawings is exemplary, is only used for explaining the utility model, and it is not intended that to of the present utility model
Limit.
In description of the present utility model it is to be understood that term " " center ", " longitudinal ", " horizontal ", " length ", " width
Degree ", " thickness ", " on ", D score, " top ", " bottom ", " interior ", " outward ", " clockwise ", the orientation of instruction or the position such as " counterclockwise "
Relation is based on orientation shown in the drawings or position relationship, is for only for ease of description the utility model and simplifies description, and not
It is instruction or the hint device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore not
It is understood that to be to restriction of the present utility model.Additionally, term " first ", " second " are only used for describing purpose, and it is not intended that
Indicate or hint relative importance or the implicit quantity indicating indicated technical characteristic.Thus, define " first ", "
Two " feature can be expressed or implicitly include one or more this feature.In description of the present utility model, unless
It is otherwise noted, " multiple " are meant that two or more.
In description of the present utility model, it should be noted that unless otherwise clearly defined and limited, term " peace
Dress ", " being connected ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or integratedly
Connect；Can be to be mechanically connected or electrically connect；Can be to be joined directly together it is also possible to be indirectly connected to by intermediary,
It can be the connection of two element internals.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
Concrete meaning in the utility model for the language.
In the utility model, unless otherwise clearly defined and limited, fisrt feature second feature it " on " or it
D score can include the first and second feature directly contacts it is also possible to include the first and second features not to be directly contact but logical
Cross the other characterisation contact between them.And, fisrt feature second feature " on ", " top " and " above " include the
One feature is directly over second feature and oblique upper, or to be merely representative of fisrt feature level height be higher than second feature.First is special
Levy second feature " under ", " lower section " and " below " include fisrt feature directly over second feature and oblique upper, or only
Represent that fisrt feature level height is less than second feature.
Below with reference to Fig. 1-Fig. 4, the landing gear assembly 100 for unmanned plane according to the utility model embodiment is described.
As Figure 1-Figure 4, the landing gear assembly for unmanned plane according to the utility model first aspect embodiment
100, including：Pedestal 1 and undercarriage 2.Wherein, unmanned plane can be connected with pedestal 1.Alternatively, the cross section of pedestal 1 can be with shape
Become square, but not limited to this.For example, the cross section of pedestal 1 may be formed as circle etc..
Specifically, undercarriage 2 includes the first lift arm 21 and the second lift arm 22, the first end (example of the first lift arm 21
As the lower end in Fig. 1) be pivotably coupled on pedestal 1, second end (for example, the upper end in Fig. 1) of the first lift arm 21 with
Second lift arm 22 is pivotly connected, and undercarriage 2 is configured to the first lift arm 21 and the second lift arm 22 away from pedestal 1
Movable between the stowed position at the expanded position of the heart and neighbouring pedestal 1 center.
Alternatively, the first end of the first lift arm 21 can be pivotably connected with pedestal 1 by pivotal axis or hinge etc.,
But not limited to this.Similarly, pivotal axis or hinge etc. and the second lift arm 22 can also be passed through in the second end of the first lift arm 21
It is pivotably connected, structure is simple, facilitates implementation.
For example, after unmanned plane takes off, the first lift arm 21 can be turned towards the direction near pedestal 1 center with opposite base 1
Dynamic, the second lift arm 22 can rotate so that the first lift arm by the first lift arm 21 relatively towards the direction at close pedestal 1 center
21 and second lift arm 22 be located at the stowed position (as shown in Figure 3 and Figure 4) at neighbouring pedestal 1 center.Thus, undercarriage can be made
The small volume of assembly 100, thus reducing overall volume during unmanned plane during flying, reducing windage, significantly reducing peace
Full hidden danger, improves the security of unmanned plane.
In descent, the direction that the first lift arm 21 can be directed away from pedestal 1 center with opposite base 1 turns unmanned plane
Dynamic, the direction that the second lift arm 22 can be directed away from pedestal 1 center relative to the first lift arm 21 rotates so that the first lift arm
21 and second lift arm 22 be located remotely from the expanded position (as depicted in figs. 1 and 2) at pedestal 1 center, thus, unmanned plane can be made
Grease it in, protects fuselage.
According to the utility model embodiment for unmanned plane landing gear assembly 100, by by the first of undercarriage 2
Fall arm 21 and the second lift arm 22 is configured to the first lift arm 21 and the second lift arm 22 in the expanded position away from pedestal 1 center
And movable between the stowed position at pedestal 1 center, unmanned plane can pack up undercarriage 2 in flight, can in landing
To launch undercarriage 2, thus reducing overall volume during unmanned plane during flying, significantly reducing potential safety hazard and windage, carrying
The high security of unmanned plane, and improve stationarity during UAV Landing, it is effectively protected fuselage, extend unmanned plane
Life-span.
According to some embodiments of the present utility model, the freedom of the second lift arm 22 when undercarriage 2 is located at expanded position
End (for example, lower end in Fig. 1) is less than the bottom surface of pedestal 1.For example, referring to Fig. 1, when UAV Landing, the second lift arm 22
Free end land, after being hit, angle between the first lift arm 21 and the second lift arm 22 increases, the second lift arm 22 phase
The direction that first lift arm 21 is directed away from pedestal 1 center rotates so that the free end of the second lift arm 22 is less than pedestal 1
Bottom surface.Thus, improve security during unmanned plane landing, protect fuselage.
Alternatively, the free end of the second lift arm 22 can be formed as arcwall face, but not limited to this.Thus, reduce
Frictional force between two lift arms 22 and ground, improves stationarity during unmanned plane landing.
It is, of course, understood that at least one disk-like structure can also be arranged in the free end of the second lift arm 22, by
This, can increase the free end of the second lift arm 22 and the contact area on ground, equally can improve flat during unmanned plane landing
Stability.For example, disk-like structure can be disk, and disk can be one or multiple.
According to some embodiments of the present utility model, the freedom of the second lift arm 22 when undercarriage 2 is located at stowed position
End is higher than the top surface of pedestal 1.For example, referring to Fig. 3, after unmanned plane takes off, the first lift arm 21 can be with opposite base 1 towards close
The direction at pedestal 1 center rotates, and the second lift arm 22 can the first lift arm 21 turn towards the direction near pedestal 1 center relatively
Dynamic, the angle between the first lift arm 21 and the second lift arm 22 reduces so that the free end of the second lift arm 22 is higher than pedestal 1
Top surface.Thus, the volume of landing gear assembly 100 can further be reduced, thus when further reducing unmanned plane during flying
Volume, improve security.
Alternatively, the length of the second lift arm 22 is more than the length of the first lift arm 21, but not limited to this.Thus, when rise
When the frame 2 that falls is packed up, can further reduce taking up room of undercarriage 2, and when undercarriage 2 launches, be easy to second and rise and fall
The free end of arm 22 lands.
Further, the landing gear assembly 100 for unmanned plane also includes buffer unit 3.Specifically, buffer unit 3 can
To be located between the first lift arm 21 and the second lift arm 22, buffer unit 3 is configured to carry for unmanned plane when UAV Landing
For buffering.For example, referring to Fig. 1 and Fig. 3, buffer unit 3 can be located at below the first lift arm 21 and the second lift arm 22.Optional
Ground, buffer unit 3 can be spring etc., but not limited to this.Thus, it is possible to reduce impulsive force during UAV Landing and inside unit
The vibrations of device, extend the life-span of unmanned plane.
For example, when UAV Landing, the free end of the second lift arm 22 lands, after being hit, the second lift arm 22 court
Rotate to the direction (for example, clockwise etc.) away from the first lift arm 21, the first lift arm 21 and the second lift arm 22 it
Between angle increase so that buffer unit 3 such as spring etc. is stretched, the second lift arm 22 with respect to the first lift arm 21 turn
Dynamic limited, such that it is able to being that unmanned plane provides buffering by buffer unit 3, reduce impact it is ensured that unmanned plane can steadily
Land, protects fuselage.
According to some embodiments of the present utility model, the one of upper shape in the first lift arm 21 and the second lift arm 22
Become to have shifting chute 221, the first end of buffer unit 3 is movably arranged in guide 221, the second end of buffer unit 3 and the
One lift arm 21 is connected with another in the second lift arm 22.Wherein guide 221 can be shifting chute, slide rail etc., but not
It is limited to this.
Specifically, guide 221 can be located on the first lift arm 21 it is also possible to be located on the second lift arm 22.Wherein,
When guide 221 is located on the first lift arm 21, the second end of buffer unit 3 is connected with the second lift arm 22, works as guide
221 when being located on the second lift arm 22, and the second end of buffer unit 3 is connected with the first lift arm 21.For example, referring to Fig. 1 and Tu
3, the second lift arm 22 is formed with guide 221.Guide 221 can be located at the lower section of the second lift arm 22, and guide
221 can extend along the length direction of the second lift arm 22.Now, the first end of buffer unit 3 such as spring movably sets
In guide 221, the second end of buffer unit 3 is connected with the first lift arm 21.
Specifically, the first end of buffer unit 3 is provided with the first grab 31, and the second end of buffer unit 3 is provided with the second card
Hook 32, above-mentioned another in the first lift arm 21 and the second lift arm 22 is provided with snap ring 211, and the first grab 31 is movably
It is located in guide 221, the second grab 32 is connected with snap ring 221.Wherein, the first grab 31 can move in guide 221,
Second grab 32 can put in snap ring 211, the second end of buffer unit 3 is connected to the first lift arm 21 and second and rises and falls
Above-mentioned in arm 22 is on another.
Wherein, when being formed at guide 221 on the first lift arm 21, the second lift arm 22 is provided with snap ring 211, when
When being formed with guide 221 on the second lift arm 22, the first lift arm 21 is provided with snap ring 211.Thus, it is easy to buffer unit
3 are connected on undercarriage 2, thus in UAV Landing, can provide buffering by buffer unit 3 for unmanned plane.
For example, during UAV Landing, when that is, undercarriage 2 launches, the folder between the first lift arm 21 and the second lift arm 22
Angle is gradually increased, and buffer unit 3 is stretched with the rotation limiting the second lift arm 22 with respect to the first lift arm 21, is unmanned plane
Buffering is provided, reduces impact it is ensured that unmanned plane can protect fuselage with grease it in；After unmanned plane takes off, undercarriage 2 is gradually received
Rise, the angle between the second lift arm 22 and the first lift arm 21 is gradually reduced, and the first end of buffer unit 3 is along guide 221
Such as slide rail etc. moves down, until undercarriage 2 is retracted to extreme position.Thus, it is possible to ensure buffer unit 3 in undercarriage 2
During packing up all the time in the raw.
According to some embodiments of the present utility model, undercarriage 2 pass through driving means expanded position and stowed position it
Between movable, wherein driving means include：Motor 4 and driven subassembly.Specifically, motor 4 can be located on pedestal 1, on motor 4
It is provided with output shaft 6 such as wire wheel axis etc., wherein, output shaft 6 can be connected with the motor shaft on motor 4.Driven subassembly and output
Axle 6 and the first lift arm 21 are respectively connected with.
Specifically, driven subassembly can include intermeshing driving gear 51 and driven gear 52, driving gear 51 with
Output shaft 6 is fixedly connected, and driven gear 52 is connected with the first lift arm 21, and for example, driven gear 52 can pass through driven gear
Axle 521 is connected with the first lift arm 21.
According to some embodiments of the present utility model, motor 4 has and rotates and reverse two kinds of way of outputs, and unmanned plane takes off
Afterwards, motor 4 can rotate forward, and drive driving gear 51 to drive driven gear 52 to rotate by output shaft 6 and for example rotate clockwise, make
Obtain the first lift arm 21 to rotate towards the direction near pedestal 1 center, so that the first lift arm 21 withdraws into pedestal 1；Unmanned
During machine landing, motor 4 can invert, and drives driving gear 51 to drive driven gear 52 and above-mentioned rotation direction by output shaft 6
Contrary direction for example rotates counterclockwise so that the direction that the first lift arm 21 is directed away from pedestal 1 center rotates, so that first
Lift arm 21 rotates to pedestal 1 outside.
Here, it should be noted that for described " interior ", " outward " in the application be opposite base 1 center, wherein,
" interior " refers to the direction near pedestal 1 center, and " outward " refers to the direction away from pedestal 1 center.
Further, driving means also include traction component, and traction component can be located on undercarriage 2, traction component structure
Cause to drive the second lift arm 22 to stowed position when expanded position moves with respect to the first lift arm 21 direction when undercarriage 2
The direction of neighbouring first lift arm 21 pivots, and drives the second lift arm from stowed position when undercarriage 2 moves to expanded position
22 directions being directed away from the first lift arm 21 with respect to the first lift arm 21 pivot.
Specifically, with reference to Fig. 1 and Fig. 3, traction component includes：First traction component 7 and the second traction component 8.Wherein,
First traction component 7 includes the first line wheel 71 and the first draught line 72, and the first line wheel 71 is located on undercarriage 2.For example, First Line
Wheel 71 can be located at the second end of the first lift arm 21.The first end of the first draught line 72 is fixed on the second lift arm 22,
Second end of the first draught line 72 bypasses the first line wheel 71 and is wrapped on output shaft 6.Wherein, the second lift arm 22 can be arranged
3rd grab 222, the first end of the first draught line 72 can be fixed on the 3rd grab 222.
Second traction component 8 includes the second line wheel 81 and the second draught line 82, and the second line wheel 81 is located on undercarriage 2.Example
As the second line wheel 81 can be located at the middle part of the first lift arm 21.The first end of the second draught line 82 is fixed on the second lift arm
On 22, the second end of the second draught line 82 bypasses the second line wheel 81 and is wrapped on output shaft 6.Wherein, can on the second lift arm 22
To arrange the 4th grab 223, the first end of the second draught line 82 can be fixed on the 4th grab 223.
Specifically, the first draught line 72 and the second draught line 82 winding direction on output shaft 6 is contrary.For example, when
When one draught line 72 is wrapped on output shaft 6 along clockwise direction, the second draught line 82 can be wrapped in defeated in the counterclockwise direction
On shaft 6；When the first draught line 72 is wrapped on output shaft 6 in the counterclockwise direction, the second draught line 82 can be along clockwise
Direction is wrapped on output shaft 6.Alternatively, the first draught line 72 is located at the top of the first lift arm 21 and the second lift arm 22,
Second draught line 82 is located at the lower section of the first lift arm 21 and the second lift arm 22.
For example, after unmanned plane takes off, motor 4 can rotate forward, and drives driving gear 51 to drive driven tooth by output shaft 6
Wheel 52 rotates and for example rotates clockwise so that the first lift arm 21 rotates towards the direction near pedestal 1 center, makes first to rise and fall
Arm 21 withdraws into pedestal 1.Output shaft 6 drives the second lift arm 22 first lift arm 21 relatively by tightening up the second draught line 82
Rotate towards the direction near pedestal 1 center, so that the second lift arm 22 is inwardly withdrawn.Now, the first draught line 72 is by around feedback
Shaft 6, the first end of buffer unit 3 such as spring, along slide downward such as guide 221 such as slide rails, is packed up up to undercarriage 2
To extreme position.
During unmanned plane landing, motor 4 can invert, and drives driving gear 51 to drive driven gear 52 by output shaft 6
The direction contrary with above-mentioned rotation direction for example rotates counterclockwise so that the first lift arm 21 is directed away from the side at pedestal 1 center
To rotation, the first lift arm 21 is made to rotate to pedestal 1 outside.Output shaft 6 tightens up the first draught line 72, pulls the second lift arm 22
Outwards launch, now, the second draught line 82 is retracted output shaft 6, and the first end of buffer unit 3 is along guide 221 such as slide rail
Deng upward sliding, and gradually it is stretched, until undercarriage 2 is expanded to extreme position, prepare landing buffer.
According to some embodiments of the present utility model, undercarriage 2 is multiple and multiple undercarriages 2 along between the circumference of pedestal 1
Every setting.For example, in the example of Fig. 2 and Fig. 4, the cross section of pedestal 1 is formed as square, and undercarriage 2 is four, and four are risen
Fall frame 2 along the circumferential uniform intervals setting of pedestal 1.Specifically, the first end of the first lift arm 21 can be located at pedestal 1 length of side
On center line.Thus, can further improve stationarity during UAV Landing, and structure is simple, low cost.
It is, of course, understood that the particular location of the quantity of undercarriage 2 and undercarriage 2 can be according to the actual requirements
Adjusted design, the utility model is not especially limited to this.
According to the utility model embodiment for the landing gear assembly 100 of unmanned plane, unmanned plane can be made in flight
Pack up undercarriage 2, launch undercarriage 2 when unmanned plane lands, thus, reduce overall volume during unmanned plane during flying, greatly
Reduce potential safety hazard and windage, improve the security of unmanned plane, and improve stationarity during UAV Landing, effectively
Protect fuselage, extend the life-span of unmanned plane.Additionally, by arranging between the first lift arm 21 and the second lift arm 22
Buffer unit 3, in UAV Landing, absorbs impact, provides buffering for unmanned plane it is ensured that unmanned plane can be protected with grease it in
Shield fuselage.
According to the unmanned plane of the utility model second aspect embodiment, including real according to the above-mentioned first aspect of the utility model
Apply the landing gear assembly 100 for unmanned plane of example.
According to the unmanned plane of the utility model second aspect embodiment, by setting according to the above-mentioned first party of the utility model
The landing gear assembly 100 for unmanned plane of face embodiment, landing gear assembly 100 can folding and unfolding, cushioning effect can be played again, carry
The high security of unmanned plane.
In the description of this specification, reference term " embodiment ", " some embodiments ", " illustrative examples ",
The description of " example ", " specific example " or " some examples " etc. means specific features, the knot describing with reference to this embodiment or example
Structure, material or feature are contained at least one embodiment of the present utility model or example.In this manual, to above-mentioned art
The schematic representation of language is not necessarily referring to identical embodiment or example.And, the specific features of description, structure, material or
Person's feature can combine in any one or more embodiments or example in an appropriate manner.Although there has been shown and described that
Embodiment of the present utility model, it will be understood by those skilled in the art that：Without departing from principle of the present utility model and
These embodiments can be carried out in the case of objective with multiple changes, modification, replacement and modification, scope of the present utility model is by weighing
Profit requires and its equivalent limits.
Claims (14)
1. a kind of landing gear assembly for unmanned plane is it is characterised in that include：
Pedestal；With
Undercarriage, described undercarriage includes the first lift arm and the second lift arm, and the first end of described first lift arm is pivotable
Be connected on described pedestal, the second end of described first lift arm is pivotly connected with described second lift arm, described
The framework that falls causes described first lift arm and described second lift arm in the expanded position away from described base central and neighbouring institute
State movable between the stowed position of base central, described undercarriage is the week along described pedestal for the multiple and the plurality of undercarriage
To interval setting.
2. the landing gear assembly for unmanned plane according to claim 1 is located at institute it is characterised in that working as described undercarriage
The free end stating the second lift arm described in during expanded position is less than the bottom surface of described pedestal.
3. the landing gear assembly for unmanned plane according to claim 1 is located at institute it is characterised in that working as described undercarriage
The free end stating the second lift arm described in during stowed position is higher than the top surface of described pedestal.
4. the landing gear assembly for unmanned plane according to any one of claim 1-3 is it is characterised in that wrap further
Include：
Buffer unit, described buffer unit is located between described first lift arm and described second lift arm, described buffer unit
It is configured to provide buffering when described UAV Landing for described unmanned plane.
5. the landing gear assembly for unmanned plane according to claim 4 is it is characterised in that described first lift arm and institute
State in the second lift arm one of on be formed with guide, the first end of described buffer unit be movably arranged at described in lead
Into part, the second end of described buffer unit is connected with another in described first lift arm and described second lift arm.
6. the landing gear assembly for unmanned plane according to claim 5 it is characterised in that described buffer unit first
End is provided with the first grab, and the second end of described buffer unit is provided with the second grab, and described first lift arm and described second rises and falls
Described another in arm is provided with snap ring, and described first grab is movably arranged in described guide, described second grab
It is connected with described snap ring.
7. the landing gear assembly for unmanned plane according to claim 4 is it is characterised in that described buffer unit is bullet
Spring.
8. the landing gear assembly for unmanned plane according to claim 1 is it is characterised in that described undercarriage passes through to drive
Dynamic device is movable between described expanded position and described stowed position, and wherein said driving means include：
Motor, described motor is located on described pedestal, and described motor is provided with output shaft；With
Driven subassembly, described driven subassembly is respectively connected with described output shaft and described first lift arm.
9. the landing gear assembly for unmanned plane according to claim 8 is it is characterised in that described driving means are further
Including traction component, described traction component is located on described undercarriage, and described traction component is configured to when described undercarriage is from institute
State and when expanded position moves to described stowed position, drive described second lift arm with respect to described first lift arm towards neighbouring
The direction of described first lift arm pivots, and drives institute from described stowed position when described undercarriage moves to described expanded position
State the direction pivot that the second lift arm is directed away from described first lift arm with respect to described first lift arm.
10. the landing gear assembly for unmanned plane according to claim 9 is it is characterised in that described traction component includes：
First traction component, described first traction component includes the first line wheel and the first draught line, and described first line wheel is located at institute
State on undercarriage, the first end of described first draught line is fixed on described second lift arm, the second of described first draught line
End bypasses described first line wheel and is wrapped on described output shaft.
11. landing gear assemblies for unmanned plane according to claim 10 are it is characterised in that described traction component enters one
Step includes：
Second traction component, described second traction component includes the second line wheel and the second draught line, and described second line wheel is located at institute
State on undercarriage, the first end of described second draught line is fixed on described second lift arm, the second of described second draught line
End bypasses described second line wheel and is wrapped on described output shaft, and described first draught line and described second draught line are in described output
Winding direction on axle is contrary.
12. landing gear assemblies for unmanned plane according to claim 11 are it is characterised in that described first draught line position
In the top of described first lift arm and described second lift arm, described second draught line is located at described first lift arm and described
The lower section of the second lift arm.
13. landing gear assemblies for unmanned plane according to claim 8 are it is characterised in that described driven subassembly includes
Intermeshing driving gear and driven gear, described driving gear is fixed with described output shaft, described driven gear with described
First lift arm is connected.
A kind of 14. unmanned planes are it is characterised in that include the rising for unmanned plane according to any one of claim 1-13
Fall frame assembly.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620520111.XU CN205971817U (en) | 2016-05-31 | 2016-05-31 | A unmanned aerial vehicle that is used for unmanned aerial vehicle's undercarriage subassembly and has it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620520111.XU CN205971817U (en) | 2016-05-31 | 2016-05-31 | A unmanned aerial vehicle that is used for unmanned aerial vehicle's undercarriage subassembly and has it |
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| Publication Number | Publication Date |
|---|---|
| CN205971817U true CN205971817U (en) | 2017-02-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620520111.XU Active CN205971817U (en) | 2016-05-31 | 2016-05-31 | A unmanned aerial vehicle that is used for unmanned aerial vehicle's undercarriage subassembly and has it |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109305334A (en) * | 2018-11-05 | 2019-02-05 | 深圳市金鑫城纸品有限公司 | A kind of unmanned plane with alleviation impact force function |
| CN109305332A (en) * | 2018-11-05 | 2019-02-05 | 深圳市金鑫城纸品有限公司 | It is a kind of with alleviate impact force and undercarriage can draw-in and draw-off function unmanned plane |
| CN109305335A (en) * | 2018-11-05 | 2019-02-05 | 深圳市金鑫城纸品有限公司 | One kind being based on the retractable unmanned plane of mechanically operated undercarriage |
| WO2019080170A1 (en) * | 2017-10-27 | 2019-05-02 | 罗伟 | Unmanned aerial vehicle having multi-buffering landing gear |
| WO2019137078A1 (en) * | 2018-01-15 | 2019-07-18 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN112793766A (en) * | 2021-02-04 | 2021-05-14 | 郑州航空工业管理学院 | Unmanned aerial vehicle is patrolled and examined to undercarriage folded cascade |
| EP4257485A1 (en) * | 2022-04-06 | 2023-10-11 | Goodrich Corporation | Landing gear actuation system |
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2016
- 2016-05-31 CN CN201620520111.XU patent/CN205971817U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019080170A1 (en) * | 2017-10-27 | 2019-05-02 | 罗伟 | Unmanned aerial vehicle having multi-buffering landing gear |
| WO2019137078A1 (en) * | 2018-01-15 | 2019-07-18 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN109305334A (en) * | 2018-11-05 | 2019-02-05 | 深圳市金鑫城纸品有限公司 | A kind of unmanned plane with alleviation impact force function |
| CN109305332A (en) * | 2018-11-05 | 2019-02-05 | 深圳市金鑫城纸品有限公司 | It is a kind of with alleviate impact force and undercarriage can draw-in and draw-off function unmanned plane |
| CN109305335A (en) * | 2018-11-05 | 2019-02-05 | 深圳市金鑫城纸品有限公司 | One kind being based on the retractable unmanned plane of mechanically operated undercarriage |
| CN112793766A (en) * | 2021-02-04 | 2021-05-14 | 郑州航空工业管理学院 | Unmanned aerial vehicle is patrolled and examined to undercarriage folded cascade |
| EP4257485A1 (en) * | 2022-04-06 | 2023-10-11 | Goodrich Corporation | Landing gear actuation system |
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