CN206367576U - The unmanned plane of slidingtype horn - Google Patents
The unmanned plane of slidingtype horn Download PDFInfo
- Publication number
- CN206367576U CN206367576U CN201621385917.9U CN201621385917U CN206367576U CN 206367576 U CN206367576 U CN 206367576U CN 201621385917 U CN201621385917 U CN 201621385917U CN 206367576 U CN206367576 U CN 206367576U
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- Prior art keywords
- horn
- slide rail
- unmanned plane
- fuselage
- slidingtype
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- 230000007246 mechanism Effects 0.000 claims abstract description 68
- 230000008602 contraction Effects 0.000 claims description 8
- 239000000725 suspension Substances 0.000 claims description 8
- 239000000203 mixture Substances 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 10
- 210000002683 foot Anatomy 0.000 description 7
- 238000003780 insertion Methods 0.000 description 3
- 230000037431 insertion Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
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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
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/50—Foldable or collapsible UAVs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/293—Foldable or collapsible rotors or rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
Abstract
The utility model provides a kind of unmanned plane of slidingtype horn, including fuselage and it is arranged at multiple horns of fuselage left and right side, it is characterized in that, horn described in wherein at least two is connected by sliding track mechanism with sliding machine body respectively, when the unmanned plane works, it is in deployed condition that two horns stretch out fuselage by sliding track mechanism respectively, and when unmanned plane does not work, two horns are shunk in fuselage by sliding track mechanism.The utility model compact conformation, occupy little space, volume can be significantly reduced in off working state, be easy to user's storage, store, carry and transport.
Description
Technical field
The utility model is related to unmanned air vehicle technique field, and in particular to a kind of unmanned plane of slidingtype horn.
Background technology
Unmanned plane is the unmanned vehicle manipulated using radio robot and self-contained program's control device, at present
It is most of to be used in combination with capture apparatus, applied to patrolling and take photo by plane.However, traditional unmanned plane is not mostly foldable or passes through rotation
Poststack of transferring is in irregular shape, and space-consuming is still very big, is unfavorable for the Miniaturization Design of unmanned plane volume, so as to be taken to user
Brought inconvenience when band and storage.
Therefore, volume when how preferably to reduce unmanned plane in a non-operative state, is that unmanned plane industry is continued to optimize
With the direction of development.
Utility model content
The purpose of this utility model is to provide a kind of unmanned plane of slidingtype horn, its compact conformation, occupies little space,
Volume can be significantly reduced in off working state, is easy to user's storage, stores, carry and transport.
In order to solve the above-mentioned technical problem, the utility model provides a kind of unmanned plane of slidingtype horn, including fuselage and
Multiple horns of fuselage left and right side are arranged at, horn described in wherein at least two is connected by sliding track mechanism and sliding machine body respectively
Connect, when the unmanned plane works, it is in deployed condition that two horns stretch out fuselage by sliding track mechanism respectively, works as unmanned plane
Two horns are shunk in fuselage by sliding track mechanism when not working.
Preferably, the sliding track mechanism is made up of the slide rail and horn on fuselage, and the horn, which is slided, is located at slide rail
On, when the unmanned plane works, the horn is slided along slide rail stretches out fuselage in deployed condition, when the unmanned plane does not work
When, the horn is slided along slide rail to be shunk in fuselage.
Preferably, open slot is provided with close to one end of the slide rail on the fuselage, it is described when the unmanned plane works
One end of horn, which is slided, stretches out the slide rail and open slot, when the unmanned plane does not work, and the horn, which is slided, to be shunk in cunning
In rail and open slot.
Preferably, it is set in parallel or is staggered between the multiple slide rail set on the fuselage.
Preferably, the sliding track mechanism includes the first slide rail on horn, the open slot on fuselage and is located at
The second slide rail in open slot, first slide rail is slided on the second slide rail, when the unmanned plane works, the horn
One end is slided by first and second slide rail stretches out open slot in deployed condition, and when the unmanned plane does not work, the horn passes through
First and second slide rail, which is slided, to be shunk in open slot.
Preferably, first slide rail is arranged on horn close to one end of fuselage.
Preferably, first slide rail and the second slide rail are concave-convex fit structure or socket join structure.
Preferably, it is set in parallel or is staggered between multiple second slide rail set on the fuselage.
Preferably, the Power Component of flying power can be provided for unmanned plane by being separately installed with multiple horns, described
Power Component is slided in unmanned plane off working state by the sliding track mechanism to be shunk in the open slot.
Preferably, the blade that the Power Component includes the actuating unit being fixed on horn and driven by actuating unit can
The propeller of folding, each actuating unit is individually fixed in the suspension end of extended fuselage on each horn.
Preferably, foot pad is provided below in the suspension end of the horn.
Preferably, the sliding track mechanism is in firm shape provided with making when horn expansion relative with fuselage or contraction state
The stop mechanism of state.
After such scheme, the unmanned plane of the utility model slidingtype horn is by said structure design, and it is in work
When, each horn and fuselage are in deployed condition, with ensure unmanned plane can smooth flight, and in a non-operative state, at least
A pair of horns, which can be received, to be hidden in fuselage interior, or all horns are shunk in fuselage interior, no more than the external boundary of fuselage, are made
Unmanned plane volume significantly reduces, and is easy to user to store unmanned plane, stores, carrying and transporting.
Brief description of the drawings
Fig. 1 is the deployed condition dimensional structure diagram of unmanned aerial vehicle example one of the utility model slidingtype horn；
Fig. 2 is the deployed condition dimensional structure diagram of unmanned aerial vehicle example two of the utility model slidingtype horn；
Fig. 3 looks up stereochemical structure signal for the deployed condition of unmanned aerial vehicle example two of the utility model slidingtype horn
Figure；
Fig. 4 is the contraction state elevational schematic view of unmanned aerial vehicle example two of the utility model slidingtype horn；
Fig. 5 is the deployed condition dimensional structure diagram of unmanned aerial vehicle example three of the utility model slidingtype horn；
Fig. 6 looks up stereochemical structure signal for the deployed condition of unmanned aerial vehicle example three of the utility model slidingtype horn
Figure；
Fig. 7 is the stop mechanism structural representation of the unmanned aerial vehicle example three of the utility model slidingtype horn；
Fig. 8 is the deployed condition dimensional structure diagram of unmanned aerial vehicle example four of the utility model slidingtype horn；
Fig. 9 is the contraction state dimensional structure diagram of unmanned aerial vehicle example four of the utility model slidingtype horn.
Embodiment
The utility model is illustrated below according to accompanying drawing illustrated embodiment.This time disclosed embodiment can consider in institute
It is to illustrate to have aspect, without limitation.Scope of the present utility model is not limited by the explanation of implementation below, only by right
Shown in the scope of claim, and including having all changes in the same meaning and right with right
Shape.
The deployed condition dimensional structure diagram of unmanned aerial vehicle example one of the utility model slidingtype horn as shown in Figure 1,
Including fuselage 1 and multiple horns 2 of the left and right side of fuselage 1 are arranged at, the present embodiment horn 2 is set to two pairs.Wherein it is located at front portion
Together with a pair of horns 2 of left and right side are slidably connected by the first sliding track mechanism and the second sliding track mechanism with fuselage 1 respectively.
First sliding track mechanism includes being arranged at the first open slot 3 of the front side end of fuselage 1, is arranged under front left horn 2
In first slide rail 4 of surface right-hand member and the second slide rail 5 being arranged on the downside inwall of the first open slot 3, this embodiment, first opens
The shape of cross section of mouthful groove 3 is square, and the left and right side of insertion fuselage 1, and the first slide rail 4 is that cross section is T-shaped and along right and left
To the open slot of extension, the second slide rail 5 is that cross section is T-shaped and the fin that extends in left-right direction.First slide rail 4 is slided and is located at
On second slide rail 5, when unmanned plane normal work, the first slide rail 4 of the right-hand member of horn 2 slides to horn 2 to the left along the second slide rail 5
Left side, horn 2 is in deployed condition with fuselage 1, and when unmanned plane is in off working state, the first slide rail 4 is slided to the right along the second slide rail 5
Dynamic retract into is concealed in the first open slot 3, and it is no more than the outer rim of fuselage 1.
The first open slot 3 that second sliding track mechanism includes being arranged on fuselage 1, it is arranged at the upper surface of horn 2 on the right side of front portion
In 3rd slide rail 6 of left end and the 4th slide rail 7 being arranged in the upper inside walls of the first open slot 3, this embodiment, the 3rd slide rail 6
The open slot for being inverted T-shaped for cross section and extending in left-right direction, the 4th slide rail 7 is that cross section is inverted T-shaped and in left-right direction
The fin of extension.3rd slide rail 6 is slidably connected on the 4th slide rail 7, when unmanned plane normal work, and the 3rd of the left end of horn 2 the
Slide rail 6 slides to the right the right side of horn 2 along the 4th slide rail 7, and horn 2 is in deployed condition with fuselage 1, when unmanned plane is in inoperative shape
During state, the 3rd slide rail 6 is slided to retract into and concealed in the first open slot 3 to the left along the 4th slide rail 7, and it is no more than fuselage 1
Outer rim, the present embodiment, the second slide rail 5 is respectively arranged at from the 4th slide rail 7 on the different walls of first open slot 3, and it can also
It is arranged in same wall surface, but the second slide rail 5 avoids setting on the same track as far as possible with the 4th slide rail 7, therefore can select
To be arranged in parallel.
The Power Component of flying power can be provided for unmanned plane by being separately installed with four horns 2.Power Component includes solid
Due to the actuating unit 8 on horn 2 and the folding propeller 9 of blade driven by actuating unit 8, wherein actuating unit is optional
Select and use motor.Each actuating unit 8 is individually fixed in the suspension end on four horns 2.The suspension end lower surface of each horn 2 is set respectively
It is equipped with foot pad 10.The bottom surface of all foots pad 10 is set must be concordant, and all foots pad 10 protrude from the left and right side of fuselage 1, use
Buffering and support when unmanned plane lands or places.
During work, when unmanned plane is in state of flight, two horns 2 positioned at anterior left and right side pass through first respectively
Sliding track mechanism and the second sliding track mechanism, which are slided, stretches out fuselage 1, and it is in deployed condition with fuselage 1 to make two horns 2, positioned at rear side
Two horns 2 are always maintained at deployed condition；And when unmanned plane is in non-state of flight, positioned at two machines of anterior left and right side
Arm 2 is shunk in the first open slot 3 of fuselage 1, while propeller 9 by the first sliding track mechanism and the second sliding track mechanism respectively
Blade also shrink, Power Component is slided with horn 2 to be shunk in the first open slot 3, no more than the border of fuselage 1, from
And significantly reduce the volume of unmanned plane.
The deployed condition of unmanned aerial vehicle example two solid of shown the utility model slidingtype horn is tied as shown in Figure 2, Figure 3 and Figure 4
Structure schematic diagram, deployed condition look up dimensional structure diagram and contraction state elevational schematic view, including fuselage 1 and are arranged at machine
Multiple horns 2 of the left and right side of body 1, the present embodiment horn 2 is set to two pairs.Wherein it is located at a pair of horns 2 of anterior left and right side
Together with being slidably connected respectively with fuselage 1 by the first sliding track mechanism and the second sliding track mechanism.
First sliding track mechanism includes being arranged at the first open slot 3 of the front side end of fuselage 1, is arranged under front left horn 2
In first slide rail 4 of surface right-hand member and the second slide rail 5 being arranged on the downside inwall of the first open slot 3, this embodiment, first opens
The shape of cross section of mouthful groove 3 is square, and the left and right side of insertion fuselage 1, and the first slide rail 4 is that cross section is T-shaped and along right and left
To the open slot of extension, the second slide rail 5 is that cross section is T-shaped and the fin that extends in left-right direction.First slide rail 4 is slided and is located at
On second slide rail 5, when unmanned plane normal work, the first slide rail 4 of the right-hand member of horn 2 slides to horn 2 to the left along the second slide rail 5
Left side, horn 2 is in deployed condition with fuselage 1, and when unmanned plane is in off working state, the first slide rail 4 is slided to the right along the second slide rail 5
Dynamic retract into is concealed in the first open slot 3, and it is no more than the outer rim of fuselage 1.
The first open slot 3 that second sliding track mechanism includes being arranged on fuselage 1, it is arranged at the upper surface of horn 2 on the right side of front portion
In 3rd slide rail 6 of left end and the 4th slide rail 7 being arranged in the upper inside walls of the first open slot 3, this embodiment, the 3rd slide rail 6
The open slot for being inverted T-shaped for cross section and extending in left-right direction, the 4th slide rail 7 is that cross section is inverted T-shaped and in left-right direction
The fin of extension.3rd slide rail 6 is slidably connected on the 4th slide rail 7, when unmanned plane normal work, and the 3rd of the left end of horn 2 the
Slide rail 6 slides to the right the right side of horn 2 along the 4th slide rail 7, and horn 2 is in deployed condition with fuselage 1, when unmanned plane is in inoperative shape
During state, the 3rd slide rail 6 is slided to retract into and concealed in the first open slot 3 to the left along the 4th slide rail 7, and it is no more than fuselage 1
Outer rim, the present embodiment, the second slide rail 5 is respectively arranged at from the 4th slide rail 7 on the different walls of first open slot 3, and it can also
It is arranged in same wall surface, but the second slide rail 5 avoids setting on the same track as far as possible with the 4th slide rail 7, therefore can select
To be arranged in parallel.
Two horns 2 positioned at rear portion left and right side are slided by the 3rd sliding track mechanism and the 4th sliding track mechanism with fuselage 1 respectively
It is dynamic to link together.
3rd sliding track mechanism includes being arranged at the second open slot 11 of the rear side end of fuselage 1, is arranged under rear left horn 2
In 5th slide rail 12 of surface right-hand member and the 6th slide rail 13 being arranged on the downside inwall of the second open slot 11, this embodiment, the
The shape of cross section of two open slots 11 is square, and the left and right side of insertion fuselage 1, and the 5th slide rail 12 is that cross section is T-shaped and edge
The open slot of left and right directions extension, the 6th slide rail 13 is that cross section is T-shaped and the fin that extends in left-right direction.5th slide rail 12
Slide on the 6th slide rail 13, when unmanned plane normal work, the 5th slide rail 12 of the right-hand member of horn 2 along the 6th slide rail 13 to the left
Slide to the left side of horn 2, horn 2 is in deployed condition with fuselage 1, when unmanned plane is in off working state, the 5th slide rail 12 is along the
Six slide rails 13 are slided to retract into and concealed in the second open slot 11, and it is no more than the outer rim of fuselage 1.
4th sliding track mechanism include be arranged on fuselage 1 the second open slot 11, be arranged at the upper surface of rear right horn 2
In 7th slide rail 14 of left end and the 8th slide rail 15 being arranged in the upper inside walls of the second open slot 11, this embodiment, the 7th slides
Rail 14 is that cross section is inverted T-shaped and the open slot that extends in left-right direction, and the 8th slide rail 15 is that cross section is inverted T-shaped and along left and right
The fin of direction extension.7th slide rail 14 is slided on the 8th slide rail 15, when unmanned plane normal work, the left end of horn 2
7th slide rail 14 slides to the right the right side of horn 2 along the 8th slide rail 15, and horn 2 is in deployed condition with fuselage 1, when unmanned plane is non-
During working condition, the 7th slide rail 14 is slided to retract into and concealed in the second open slot 11 to the left along the 8th slide rail 15, and it does not surpass
The outer rim of fuselage 1 is crossed, the present embodiment, the 6th slide rail 13 is respectively arranged at the different walls of the second open slot 11 from the 8th slide rail 15
On, it can also be arranged in same wall surface, but the 6th slide rail 13 avoids setting on the same track as far as possible with the 8th slide rail 15,
Therefore it can select to be arranged in parallel or be staggered.
In the present embodiment, on the first sliding track mechanism, the second sliding track mechanism, the 3rd sliding track mechanism and the 4th sliding track mechanism respectively
Provided with stop mechanism when making four horns 2 with the expansion relatively of fuselage 1 or contraction state in steady status.Due to the first slide rail machine
Set stop mechanism structure is identical on structure, the second sliding track mechanism, the 3rd sliding track mechanism and the 4th sliding track mechanism, thus just with
The stop mechanism being arranged on the first sliding track mechanism is illustrated, other to repeat no more.
With reference to shown in Fig. 2 and Fig. 7, stop mechanism includes two pairs of projections 16 for being arranged at the left and right side of the second slide rail 5 and symmetrical
Two opening slot structures on the left and right end of the first slide rail 4 are arranged at, each pair projection 16 is symmetricly set in the forward and backward of the second slide rail 5
Side, each opening slot structure includes being arranged at the 3rd open slot 17 of the left or right bottom of the first slide rail 4, a left side for the first slide rail 4
The part that end or right-hand member are located at below the 3rd open slot 17 symmetrically offers a pair of open slots 18 of C-shaped the 4th in forward and backward, when first
Slide rail 4 along the second slide rail 5 slide into any pair of 16 position of projection when, this pair of projection 16 is caught in a pair on the first slide rail 4
In four open slots 18, it is in steady status with fuselage 1 to make the horn 2.
The Power Component of flying power can be provided for unmanned plane by being separately installed with four horns 2.Power Component includes solid
Due to the actuating unit 8 on horn 2 and the folding propeller 9 of blade driven by actuating unit 8, wherein actuating unit is optional
Select and use motor.Each actuating unit 8 is individually fixed in the suspension end on four horns 2.The suspension end lower surface of each horn 2 is set respectively
It is equipped with foot pad 10.The bottom surface of all foots pad 10 is set must be concordant, and all foots pad 10 protrude from the left and right side of fuselage 1, use
Buffering and support when unmanned plane lands or places.
During work, when unmanned plane is in state of flight, with reference to shown in Fig. 2 and Fig. 3, four horns 2 pass through first respectively
Sliding track mechanism, the second sliding track mechanism, the 3rd sliding track mechanism and the 4th sliding track mechanism, which are slided, stretches out fuselage 1, makes four horns 2 and machine
Body 1 is in deployed condition；And when unmanned plane is in non-state of flight, with reference to shown in Fig. 4, four horns 2 pass through first respectively
Sliding track mechanism, the second sliding track mechanism, the 3rd sliding track mechanism and the 4th sliding track mechanism shrink the first open slot 3 and in fuselage 1
In two open slots 11, while the blade of the propeller 9 of each Power Component also shrinks, each Power Component is in company with correspondence horn
2 slips are shunk in the first open slot 3 and the second open slot 11, no more than the border of fuselage 1, so as to significantly reduce unmanned plane
Volume, set respectively additionally, due on the first sliding track mechanism, the second sliding track mechanism, the 3rd sliding track mechanism and the 4th sliding track mechanism
Be equipped with stop mechanism, thus four horns 2 no matter in deployed condition or contraction state all without departing from the first open slot 3 and second
Open slot 11, i.e., without departing from fuselage 1.
As shown in Figure 5, Figure 6, the deployed condition stereochemical structure of unmanned aerial vehicle example three of the utility model slidingtype horn is shown
It is intended to and deployed condition looks up dimensional structure diagram, and withs reference to Fig. 7 shown in, most of structure and above-mentioned reality of the present embodiment
The structure for applying example two is identical, and something in common is repeated no more, and is a difference in that：Second slide rail 5 and second of the first sliding track mechanism is slided
4th slide rail 7 of rail mechanism be may be contained within the rear wall of the first open slot 3, and the second slide rail 5 is set with the 4th slide rail 7 in parallel
Put；6th slide rail 13 of the 3rd sliding track mechanism and the 8th slide rail 15 of the 4th sliding track mechanism may be contained within before the second open slot 11
On the wall of side, and the 6th slide rail 13 is set in parallel with the 8th slide rail 15.
Because the course of work and the course of work of above-described embodiment two of the present embodiment are essentially identical, here is omitted.
The deployed condition stereochemical structure of unmanned aerial vehicle example four of the utility model slidingtype horn is shown as shown in Figure 8 and Figure 9
It is intended to and contraction state dimensional structure diagram, most of structure is identical with structure described in above-described embodiment two in the present embodiment,
It is a difference in that：Together with the sliding track mechanism that four horns 2 are misplaced by intersection respectively is slidably connected with fuselage 1.
Sliding track mechanism includes the slide rail 19 and horn 2 close to the diagonal position of fuselage 1 on fuselage 1, slide rail 19 and fuselage 1
The inner chamber of fuselage 1 is set and stretched at an angle, horn 2 is slided on slide rail 19, slide rail 19 and horn 2 in this embodiment
For socket join structure.The slide rail 19 of two anterior sliding track mechanisms of fuselage 1 is arranged in being staggered, the rear portion of fuselage 1 is arranged at
The slide rail 19 of two sliding track mechanisms is in be staggered.Open slot 20 is offered respectively in the front and back ends of fuselage 1, each slide rail 19
One end is opened on the wall of corresponding opening groove 20 respectively, and the other end stretches into the inner chamber of fuselage 1.When unmanned plane works, the phase of horn 2
Slide rail 19 is slided and stretches out fuselage 1 in deployed condition, when unmanned plane does not work, horn 2 is slided along slide rail 19 to be shunk in slide rail
19 and open slot 20 in.
By horn 2 using the benefit that is staggered be the increase in adjustment axis away from flexibility（Wheelbase is exactly that paddle components are arrived
The distance of other paddle components）, in the case where condition is certain, rational wheelbase can properly increase the flying quality of unmanned plane,
Include the life-span of flight stability, flight time and power part.
Those skilled in the art will readily occur to its of the present invention after considering specification and putting into practice invention disclosed herein
Its embodiment.The application be intended to the present invention any modification, purposes or adaptations, these modifications, purposes or
Person's adaptations follow the general principle of the present invention and including undocumented common knowledge or usual in the art
Technological means.Description and embodiments be considered only as it is exemplary, true scope and spirit of the invention by following right will
Ask and point out.
It should be appreciated that the invention is not limited in the precision architecture for being described above and being shown in the drawings, and
And various modifications and changes can be being carried out without departing from the scope.The scope of the present invention is only limited by appended claim.
Claims (12)
1. a kind of unmanned plane of slidingtype horn, including fuselage and the multiple horns for being arranged at fuselage left and right side, its feature exist
In horn described in wherein at least two is connected by sliding track mechanism with sliding machine body respectively, when the unmanned plane works, two
It is in deployed condition that the horn stretches out fuselage by sliding track mechanism respectively, and when unmanned plane does not work, two horns pass through cunning
Rail mechanism
Shrink in fuselage.
2. the unmanned plane of slidingtype horn according to claim 1, it is characterised in that the sliding track mechanism is by located at fuselage
On slide rail and horn composition, the horn slided on slide rail, and when the unmanned plane works, the horn is slided along slide rail
The dynamic fuselage that stretches out is in deployed condition, when the unmanned plane does not work, and the horn is slided along slide rail to be shunk in fuselage.
3. the unmanned plane of slidingtype horn according to claim 2, it is characterised in that close to the slide rail on the fuselage
One end be provided with open slot, when the unmanned plane work, the stretching slide rail and open slot are slided in one end of the horn, when
When the unmanned plane does not work, the horn, which is slided, to be shunk in slide rail and open slot.
4. the unmanned plane of slidingtype horn according to claim 3, it is characterised in that the multiple cunnings set on the fuselage
It is set in parallel or is staggered between rail.
5. the unmanned plane of slidingtype horn according to claim 1, it is characterised in that the sliding track mechanism includes being located at machine
The first slide rail on arm, the open slot on fuselage and the second slide rail in open slot, first slide rail are slided and set
In on the second slide rail, when the unmanned plane works, described horn one end is slided by first and second slide rail stretches out open slot in exhibition
Open state, when the unmanned plane does not work, the horn is slided by first and second slide rail to be shunk in open slot.
6. the unmanned plane of slidingtype horn according to claim 5, it is characterised in that first slide rail is arranged at horn
Upper one end close to fuselage.
7. the unmanned plane of slidingtype horn according to claim 6, it is characterised in that first slide rail and the second slide rail
For concave-convex fit structure or socket join structure.
8. the unmanned plane of slidingtype horn according to claim 5, it is characterised in that multiple set on the fuselage
It is set in parallel or is staggered between two slide rail.
9. the unmanned plane of the slidingtype horn according to claim any one of 3-8, it is characterised in that on multiple horns
The Power Component of flying power can be provided for unmanned plane by being separately installed with, and the Power Component leads in unmanned plane off working state
Cross the sliding track mechanism and slide and shrink in the open slot.
10. the unmanned plane of slidingtype horn according to claim 9, it is characterised in that the Power Component includes fixing
In the actuating unit on horn and the folding propeller of blade driven by actuating unit, each actuating unit is fixed respectively
In the suspension end of extended fuselage on each horn.
11. the unmanned plane of slidingtype horn according to claim 10, it is characterised in that below the suspension end of the horn
It is provided with foot pad.
12. the unmanned plane of the slidingtype horn according to any one of claim 1,2,3,4,5,6,7,8,10,11, its feature
It is, the sliding track mechanism is provided with the stop bit machine in steady status when making horn expansion relative with fuselage or contraction state
Structure.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621385917.9U CN206367576U (en) | 2016-12-16 | 2016-12-16 | The unmanned plane of slidingtype horn |
| PCT/CN2017/116455 WO2018108148A1 (en) | 2016-12-16 | 2017-12-15 | Unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621385917.9U CN206367576U (en) | 2016-12-16 | 2016-12-16 | The unmanned plane of slidingtype horn |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206367576U true CN206367576U (en) | 2017-08-01 |
Family
ID=59392893
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621385917.9U Active CN206367576U (en) | 2016-12-16 | 2016-12-16 | The unmanned plane of slidingtype horn |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN206367576U (en) |
| WO (1) | WO2018108148A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018108148A1 (en) * | 2016-12-16 | 2018-06-21 | 普宙飞行器科技（深圳）有限公司 | Unmanned aerial vehicle |
| CN108668691A (en) * | 2018-05-23 | 2018-10-19 | 刘冉 | A kind of afforestation device and its working method |
| WO2019242621A1 (en) * | 2018-06-22 | 2019-12-26 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle and body assembly thereof |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9573683B2 (en) * | 2014-04-28 | 2017-02-21 | Arch-Aerial, Llc | Collapsible multi-rotor UAV |
| CN204197289U (en) * | 2014-11-05 | 2015-03-11 | 成都好飞机器人科技有限公司 | A kind of rack construction of many rotor wing unmanned aerial vehicles |
| CN205044967U (en) * | 2015-09-21 | 2016-02-24 | 温州乐享科技信息有限公司 | Unmanned aerial vehicle with reserve screw |
| CN205168898U (en) * | 2015-10-06 | 2016-04-20 | 深圳九星智能航空科技有限公司 | Environmental monitoring unmanned aerial vehicle |
| CN205469802U (en) * | 2016-01-26 | 2016-08-17 | 李军辉 | High performance shock attenuation unmanned aerial vehicle |
| CN206367576U (en) * | 2016-12-16 | 2017-08-01 | 普宙飞行器科技（深圳）有限公司 | The unmanned plane of slidingtype horn |
-
2016
- 2016-12-16 CN CN201621385917.9U patent/CN206367576U/en active Active
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2017
- 2017-12-15 WO PCT/CN2017/116455 patent/WO2018108148A1/en active Application Filing
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018108148A1 (en) * | 2016-12-16 | 2018-06-21 | 普宙飞行器科技（深圳）有限公司 | Unmanned aerial vehicle |
| CN108668691A (en) * | 2018-05-23 | 2018-10-19 | 刘冉 | A kind of afforestation device and its working method |
| WO2019242621A1 (en) * | 2018-06-22 | 2019-12-26 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle and body assembly thereof |
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| Publication number | Publication date |
|---|---|
| WO2018108148A1 (en) | 2018-06-21 |
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