CN107117286A - Collapsible unmanned plane and its method for folding - Google Patents
Collapsible unmanned plane and its method for folding Download PDFInfo
- Publication number
- CN107117286A CN107117286A CN201710301432.XA CN201710301432A CN107117286A CN 107117286 A CN107117286 A CN 107117286A CN 201710301432 A CN201710301432 A CN 201710301432A CN 107117286 A CN107117286 A CN 107117286A
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- CN
- China
- Prior art keywords
- connector
- pull bar
- unmanned plane
- paddle arm
- fixed bin
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Agricultural Machines (AREA)
- Toys (AREA)
Abstract
The present invention provides a kind of collapsible unmanned plane and its method for folding, and collapsible unmanned plane includes fuselage, and the both sides of fuselage are respectively connected with rotating shaft, rotating shaft and are rotatably provided with paddle arm component, and paddle arm component includes fixed bin and the paddle arm in fixed bin；Fuselage is provided with fold mechanism, fold mechanism includes pull bar, the first end of pull bar connects the first end of connector, second end of connector is arranged on fixed bin, connector includes articulated section, articulated section is arranged between the first end of connector and the second end of connector, articulated section rotates around the axis, the first end of connector can be rotated around the first end of pull bar, using above structure, driving fold mechanism makes connector drive fixed bin to rotate, paddle arm on fixed bin is folded into different angles, facilitate unmanned machine operation, it is easy to operate, it is the folding that all paddle arm on fixed bin can be achieved to rotate fixed bin, it is rapidly completed the folding of paddle arm, effectively improve operating efficiency.
Description
Technical field
The present invention relates to unmanned plane field, more particularly, to a kind of collapsible unmanned plane and its method for folding.
Background technology
Unmanned plane is the general designation of unmanned vehicle, and it is provided with the equipment such as automatic pilot, presetting apparatus.Ground
Dough figurine person by equipment such as radars, it is tracked, positioned, remote control, remote measurement and Digital Transmission.Compared with manned aircraft, it
There is small volume, it is low cost, easy to use.Wing-folding formula unmanned plane passes through Foldable square under different flight demands
Formula change wing shapes, wing all expansion in favor of taking off or cruising, wing shrink in favor of at a high speed or maneuvering flight and
Space is saved in storage.
But there is problems with traditional unmanned plane：1st, volume is larger, it has not been convenient to carry；When the 2nd, folding, it is still necessary to artificial
Folded manually, inefficiency；3rd, it is necessary to individually be folded to paddle arm in unmanned plane folding process so that folding
Folded process carries out slow, influence operating efficiency.
The content of the invention
The main object of the present invention be to provide it is a kind of can fast folding paddle arm collapsible unmanned plane and its method for folding.
To realize above-mentioned main purpose, the collapsible unmanned plane that the present invention is provided, including：
Fuselage, the both sides of fuselage are respectively connected with rotating shaft；
Paddle arm component, paddle arm component includes fixed bin and the paddle arm in fixed bin；Paddle arm component can turn around the shaft
It is dynamic；
Fold mechanism, fold mechanism includes pull bar, and the first end of pull bar connects the first end of connector, the second of connector
End is arranged on fixed bin, and connector includes articulated section, and articulated section is arranged on the first end of connector and the second end of connector
Between, articulated section is rotated around the axis, and the first end of connector can be rotated around the first end of pull bar.
From such scheme, fold mechanism is driven, pull bar promotes connector to make the first end of connector around the of pull bar
One end is rotated, and the rotation of connector first end drives the rotation of articulated section and the second end, so that drive fixed bin to rotate around the axis,
Paddle arm installed in fixed bin is moved with the rotation of fixed bin, until the angle of paddle arm and fuselage reaches predetermined angle.Can
According to the different demands of flight, paddle arm is folded into different angles, facilitates unmanned machine operation, it is easy to operate, rotate fixed bin
The folding of all paddle arm on fixed bin can be achieved, is rapidly completed the folding of paddle arm, effectively improves operating efficiency.
Further scheme is that the first end of pull bar and the second end of pull bar are equipped with perforate, the first end of connector
Provided with the first perforate, perforate in pull bar first end with the first perforate is concentric sets, perforate has with running through in the first perforate
Connecting rod.
It can be seen that, connecting rod through perforate and the second perforate, completes the connection between pull bar and connector simultaneously.
Further scheme is variant part to be provided between the first end of pull bar and the second end of pull bar, variant part is radially
Width be more than the first end width radially of pull bar, the width of variant part radially is more than the second end of pull bar radially
Width；The side of pull bar is connected with gag lever post.
It can be seen that, pull bar is in addition to playing a part of promoting connector rotation, and the setting of variant part and gag lever post can make on pull bar
Pull bar plays a part of unmanned plane anti-crash, during crash, paddle arm auto-folder, in the presence of gag lever post, pull bar gram
Friction working and deformation buffer impulsive force are taken, so as to play a part of anti-crash.
Further scheme is that the second end connection drive mechanism of pull bar, the drive mechanism includes screw mandrel and is arranged
Sliding block on screw mandrel, the sliding block connects the first connector, and first connector connects the second end of the pull bar, described
Screw mandrel connecting power device.
It can be seen that, when screw mandrel rotates, the sliding block being set on screw mandrel moves along a straight line along the direction of principal axis of screw mandrel, from
And shift the pull bar being connected with sliding block onto, in the presence of power set, utilize screw mandrel connecting rod structure pushing drawing rod so that fold
Mechanism auto-folder, the step of removing hand foldable accelerates operating efficiency.
Further scheme is that drive mechanism also includes the mounting bracket being fixed on fuselage, and it is mutual that mounting bracket includes two panels
Form mounting groove between parallel installation sheet, two panels installation sheet, be provided with screw mandrel in mounting groove, the direction of principal axis of screw mandrel and mounting groove
Bearing of trend is identical, and two panels installation sheet is equipped with groove, and the bearing of trend of groove is parallel with the direction of principal axis of screw mandrel, the first connector
Through the second end of groove cylinder lever connecting rod.
As can be seen here, the installation sheet being parallel to each other by two panels constitutes mounting bracket, simple in construction, few using part, effectively subtracts
Few fuselage bears a heavy burden, and the first connector is connected with pull bar through groove, the range of movement of pull bar is limited so that the fortune of pull bar
Dynamic direction is parallel with the direction of motion of sliding block, and two panels installation sheet is equipped with groove, and sliding block is all connected with first close to the both sides of groove
Connector, the first connector of both sides extends through groove and is connected with pull bar, forms double selection structures.
Further scheme is that bearing block is provided with mounting groove, and screw mandrel is provided between bearing block, and bearing block is fixed on machine
With.
Further scheme is that screw mandrel is connected through bearing block with power set, is also set between bearing block and power set
There is shaft coupling.
As can be seen here, shaft coupling completes the connection of screw mandrel and power set so that driving shaft and screw mandrel in power set
Connection.
The method for folding of the collapsible unmanned plane of the present invention, collapsible unmanned plane is to use above-mentioned collapsible unmanned plane；
Method for folding comprises the following steps：
S1, driving fold mechanism, make the first end of connector be rotated around one end of drawing；
S2, the second end of the rotational band follower link of the first end of connector rotate around the axis, so as to drive fixed bin to turn
It is dynamic, until paddle arm and the angle of fuselage reach predetermined angle.
It can be seen that, realize the paddle arm of unmanned plane in a dimension according to the different demands of flight in the presence of fold mechanism
Under folding, to a greater degree adapt to flight operation, effectively improve operating efficiency.
Brief description of the drawings
Fig. 1 is the structure chart of collapsible unmanned aerial vehicle example of the invention.
Fig. 2 is schematic enlarged-scale view at A in Fig. 1.
Fig. 3 is the stereogram of the pull bar in collapsible unmanned aerial vehicle example of the invention.
Below in conjunction with drawings and Examples, the invention will be further described.
Embodiment
The collapsible unmanned plane of the present invention is applied in unmanned plane field, can be according to different flight demands, in the mistake of flight
Automatically adjusting for paddle arm folding angles is carried out in journey, aerial mission can be rapidly adapted to, operating efficiency is effectively improved.
Referring to Fig. 1, collapsible unmanned plane of the invention, including fuselage 1, the both sides in the radial direction of fuselage 1 are respectively connected with
Paddle arm component is rotationally provided with rotating shaft 2, rotating shaft 2, paddle arm component includes fixed bin 3 and paddle arm 7, and fixed bin 3 is provided with oar
Paddle arm 7 is installed, paddle arm installing port is consistent with paddle arm quantity in arm installing port 4, paddle arm installing port 4.
Fig. 2 is participated in, unmanned plane includes fold mechanism, and fold mechanism includes pull bar 5, the connection connection of first end 51 of pull bar 5
The first end 60 of part 6, the second end 61 of connector 6 is arranged on fixed bin 3, and connector 6 includes articulated section, and articulated section is arranged on
Between the first end 60 of connector 6 and the second end 61 of connector 6, in the present embodiment, the second end 61 of connector 6 is used as hinge
Socket part, articulated section 2 is rotated around the shaft, and the first end 60 of connector 6 can be rotated around the first end 51 of pull bar 5；Drive fold mechanism,
Pull bar 5 promotes connector 6 first end 60 of connector 6 is rotated around the first end 51 of pull bar 5, the first end 60 of connector 6
The rotation for driving the second end 61 is rotated, so as to drive fixed bin 32 to rotate around the shaft, the paddle arm 7 installed in fixed bin 3 is with solid
Determine the rotation of box 3 and move, until the angle of paddle arm 7 and fuselage 1 reaches predetermined angle, it is that can be achieved to be arranged on to rotate fixed bin
The folding of all paddle arm on fixed bin, is rapidly completed the folding of paddle arm, effectively improves operating efficiency.The first end 51 of pull bar 5
Perforate 50 is equipped with the second end 52 of pull bar 5, during the first end 60 of connector 6 is rotated, the first end of connector 6
60 rotation axis is the axial line of the perforate 50 of the first end 51 of pull bar 5.Perforate 50 in the first end 51 of pull bar 5 is with being connected
The concentric connection of the first perforate in the first end 60 of part 6, runs through opening in the first end 51 of pull bar 5 simultaneously using connecting rod 8
Hole 50 and the first perforate in the first end 60 of connector 6, complete the connection between pull bar 5 and connector 6, the quantity of pull bar 5
For two, the both sides of connector 6 are separately positioned on, formation is double to push away fold mechanism.
Drive mechanism includes fixed mounting bracket on the fuselage 1, and mounting bracket includes the installation sheet 92 that two panels is parallel to each other, by
The composition mounting bracket of installation sheet 92 that two panels is parallel to each other, it is simple in construction, it is few using part, effectively reduce fuselage and bear a heavy burden；Two panels is pacified
Mounting groove 93 is formed between load 10, the two ends of mounting groove 93 are equipped with bearing block 96,96 points of the bearing block at the two ends of mounting groove 93
Fuselage 1 is not fixed on；Screw mandrel 9 is provided with mounting groove 93, the direction of principal axis of screw mandrel 9 is identical with the bearing of trend of mounting groove 93, screw mandrel 9
Groove is equipped with provided between the bearing block 96 at the two ends of mounting groove 93, being arranged with screw mandrel 9 on sliding block 90, two panels installation sheet 92
94, the both sides of sliding block 90 towards groove 94 are all connected with the first connector 95, and the first connector 95 of both sides extends through groove 94
The first end of cylinder lever connecting rod 5.The installation sheet 92 being parallel to each other by two panels constitutes mounting bracket, simple in construction, few using part, effectively
Reduce fuselage to bear a heavy burden, the first connector 95 is connected with pull bar 5 through groove 94, limits the range of movement of pull bar 5 so that
The direction of motion of pull bar 5 is parallel with the direction of motion of sliding block 90, and two panels installation sheet 92 is equipped with groove 94, and sliding block 90 is close to groove
94 both sides are all connected with the first connector 95, and the first connector 95 of both sides extends through groove 94 and is connected with pull bar 5, form double
Selection structure.Pull bar connects drive device, can be achieved automatically to fold fold mechanism, improves operating efficiency.
One end connecting power device 91 of screw mandrel 9, wherein power set 91 are reducing motor, and screw mandrel 9 runs through bearing block 96
It is connected with power set 3, shaft coupling 97 is additionally provided between bearing block 96 and power set 91, shaft coupling 97 completes screw mandrel 9 with moving
The connection of power apparatus 91 so that the driving shaft in power set 91 couples with screw mandrel 9.
Referring to Fig. 3, the first groove 53, the quantity of the first groove 53 are equipped with the end 52 of first end 51 and second of pull bar 5
For two.The side of pull bar 5 is provided with gag lever post 55, and the direction of principal axis of gag lever post 55 is parallel with the direction of principal axis of pull bar 5, gag lever post 55
Two ends are respectively connected with fastener 54, and the fastener 1 of the two ends connection of gag lever post 55 extends through two the first grooves 53, to ensure
In the presence of gag lever post 55 fastener 54 can produce friction in the first groove 53, to ensure in unmanned plane by impacting
During, pull bar 5 can overcome friction working, so as to slow down impact.It is provided between the end 52 of first end 51 and second of pull bar 5
Variant part, the width of variant part radially is more than the width of first end 51, and the width of variant part radially is more than the second end 52
Width, variant part include the first protruding block 56 and the second protruding block 57, the first protruding block 56 is with the second protruding block 57 with spacing
Bar 55 is that symmetry axis both sides are symmetrical arranged, and variant part also includes the first hollow bulb 58, and it is raised that the first hollow bulb 58 is arranged on first
Between the protruding block 57 of block 56 and second, the setting of the first hollow bulb 58 ensures that elastic draw bar 5 has maximum deformation range.The
One protruding block 56 and the second protruding block 57 are curved, and the peak of the first protruding block 56 and the second protruding block 57 is elastic deformation
Point, pull bar 5 starts both sides with the peak of the first protruding block 56 and the second protruding block 57 and is stretched deformation.Rushed in unmanned plane
When percussion life is fallen, the folding of paddle arm drives pull bar 5 to stretch, and causes pull bar 5 to deform, and impact energy is absorbed when pull bar 5 is deformed and is tried hard to keep
The parts such as paddle arm are protected, so as to slow down impulsive force, it is to avoid unmanned plane is impaired serious.
Under the driving of power set 91, the screw mandrel 9 in mounting groove 93 is rotated, and straight line is done using frictional force band movable slider 90
Motion, sliding block 90 drives the pull bar 5 of connection sliding block 90, the position-limiting action of the second end of pull bar 5 in groove 94 during moving
Under, moved along a straight line along groove 94, the first end of pull bar 5 promotes the first end of connector 6 to be rotated around the first end of pull bar, even
Second end of fitting 6 is as the first end of connector 6 is rotated and is rotated, so as to drive paddle arm component 2 to rotate around the shaft, until oar
The angle of arm and fuselage reaches predetermined angle, so as to complete to fold.Under the driving of power set 91, bar linkage structure is automatically performed
Jackknife action, paddle arm 7 can be folded into different angles, facilitate unmanned machine operation automatically according to the different demands of flight, without
Folded manually, it is easy to operate, effectively improve operating efficiency.
The method for folding of the collapsible unmanned plane of the present invention, comprises the following steps：
S1, driving fold mechanism, make the first end of connector be rotated around one end of drawing；
S2, the second end of the rotational band follower link of the first end of connector rotate around the axis, so as to drive fixed bin to turn
It is dynamic, until paddle arm and the angle of fuselage reach predetermined angle.
It can be seen that, realize the paddle arm of unmanned plane in a dimension according to the different demands of flight in the presence of fold mechanism
Under folding, to a greater degree adapt to flight operation, effectively improve operating efficiency.
Finally it is emphasized that the invention is not restricted to above-mentioned embodiment, the type of such as connector, the first end of pull bar
It should also include within the scope of the invention as claimed with the change such as the connected mode of connector first end.
Claims (8)
1. collapsible unmanned plane, it is characterised in that including：
Fuselage, the both sides of the fuselage are respectively connected with rotating shaft；
Paddle arm component, the paddle arm component includes fixed bin and the paddle arm in the fixed bin, and the paddle arm component can
Around the axis of rotation；
Fold mechanism, the fold mechanism includes pull bar and connector, and the first end of the pull bar connects the of the connector
One end, the second end of the connector is arranged on the fixed bin, and the connector includes articulated section, and the articulated section is set
Between the first end of the connector and the second end of the connector, the articulated section can be described around the axis of rotation
The first end of connector can be rotated around the first end of the pull bar.
2. collapsible unmanned plane according to claim 1, it is characterised in that：
Second end of the first end of the pull bar and the pull bar is equipped with perforate, and the first end of the connector is provided with first
The perforate and the concentric setting of first perforate in perforate, the pull bar first end, the perforate are opened with described first
Running through in hole has connecting rod.
3. collapsible unmanned plane according to claim 2, it is characterised in that：
Variant part is provided between the first end of the pull bar and the second end of the pull bar, the width of the variant part radially is big
In the first end width radially of the pull bar, the width of the variant part radially is more than the second end of the pull bar radially
On width；The side of the pull bar is connected with gag lever post.
4. collapsible unmanned plane according to claim 3, it is characterised in that：
The second end connection drive mechanism of the pull bar, the drive mechanism includes screw mandrel and the sliding block being set on screw mandrel,
The sliding block connects the first connector, and first connector connects the second end of the pull bar, the screw mandrel connection power dress
Put.
5. collapsible unmanned plane according to claim 4, it is characterised in that：
The drive mechanism also includes the mounting bracket being fixed on the fuselage, and the mounting bracket includes the peace that two panels is parallel to each other
Form mounting groove between load, installation sheet described in two panels, be provided with the screw mandrel in the mounting groove, the direction of principal axis of the screw mandrel with
The bearing of trend of the mounting groove is identical, and installation sheet described in two panels is equipped with groove, the bearing of trend of the groove and the silk
The direction of principal axis of bar is parallel, and first connector connects the second end of the pull bar through the groove.
6. collapsible unmanned plane according to claim 5, it is characterised in that：
Bearing block is provided with the mounting groove, the screw mandrel is provided between the bearing block, and the bearing block is fixed on described
On fuselage.
7. collapsible unmanned plane according to claim 6, it is characterised in that：
The screw mandrel is connected through the bearing block with the power set, is also set between the bearing block and the power set
There is shaft coupling.
8. the method for folding of collapsible unmanned plane, it is characterised in that the collapsible unmanned plane is to use the claims 1-7
The described collapsible unmanned plane of any one；
The method for folding comprises the following steps：
S1, the driving fold mechanism, make the first end of the connector be rotated around the first end of the pull bar；
S2, the rotation of the first end of the connector drive the second end of the connector around the axis of rotation, so as to drive
The fixed bin is rotated, until the paddle arm and the angle of the fuselage reach predetermined angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710301432.XA CN107117286B (en) | 2017-05-02 | 2017-05-02 | Folding unmanned aerial vehicle and folding method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710301432.XA CN107117286B (en) | 2017-05-02 | 2017-05-02 | Folding unmanned aerial vehicle and folding method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107117286A true CN107117286A (en) | 2017-09-01 |
| CN107117286B CN107117286B (en) | 2023-07-04 |
Family
ID=59726608
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710301432.XA Active CN107117286B (en) | 2017-05-02 | 2017-05-02 | Folding unmanned aerial vehicle and folding method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107117286B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592025A (en) * | 2018-11-15 | 2019-04-09 | 航天恒星科技有限公司 | More rotor unmanned aircrafts, external member and its foldable rotor assemblies |
| CN111649057A (en) * | 2020-07-08 | 2020-09-11 | 珠海市双捷科技有限公司 | Rotating shaft for remote control of unmanned aerial vehicle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6604706B1 (en) * | 1998-08-27 | 2003-08-12 | Nicolae Bostan | Gyrostabilized self propelled aircraft |
| CN106043704A (en) * | 2016-07-25 | 2016-10-26 | 淮安市创翔农业技术推广服务有限公司 | Unmanned aerial vehicle for plant protection |
| CN106347625A (en) * | 2016-10-26 | 2017-01-25 | 成都市优艾维机器人科技有限公司 | Unmanned aerial vehicle linkage folding mechanism |
| CN206679257U (en) * | 2017-05-02 | 2017-11-28 | 珠海市双捷科技有限公司 | Collapsible unmanned plane |
-
2017
- 2017-05-02 CN CN201710301432.XA patent/CN107117286B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6604706B1 (en) * | 1998-08-27 | 2003-08-12 | Nicolae Bostan | Gyrostabilized self propelled aircraft |
| CN106043704A (en) * | 2016-07-25 | 2016-10-26 | 淮安市创翔农业技术推广服务有限公司 | Unmanned aerial vehicle for plant protection |
| CN106347625A (en) * | 2016-10-26 | 2017-01-25 | 成都市优艾维机器人科技有限公司 | Unmanned aerial vehicle linkage folding mechanism |
| CN206679257U (en) * | 2017-05-02 | 2017-11-28 | 珠海市双捷科技有限公司 | Collapsible unmanned plane |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592025A (en) * | 2018-11-15 | 2019-04-09 | 航天恒星科技有限公司 | More rotor unmanned aircrafts, external member and its foldable rotor assemblies |
| CN111649057A (en) * | 2020-07-08 | 2020-09-11 | 珠海市双捷科技有限公司 | Rotating shaft for remote control of unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107117286B (en) | 2023-07-04 |
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