CN106314767B - A kind of lightweight undercarriage for solar energy unmanned plane - Google Patents
A kind of lightweight undercarriage for solar energy unmanned plane Download PDFInfo
- Publication number
- CN106314767B CN106314767B CN201610917094.8A CN201610917094A CN106314767B CN 106314767 B CN106314767 B CN 106314767B CN 201610917094 A CN201610917094 A CN 201610917094A CN 106314767 B CN106314767 B CN 106314767B
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- China
- Prior art keywords
- ball bearing
- undercarriage
- thrust ball
- connector
- annulus
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Abstract
The invention discloses a kind of lightweight undercarriages for solar energy unmanned plane, comprising: bicycle tyre, bicycle front fork, connection component, undercarriage leg and sleeve；Wherein, the bicycle tyre is connected by bearing with the bicycle front fork；The bicycle front fork is connected by the connection component with the undercarriage leg；The sleeve is sheathed on the outer surface of the undercarriage leg and is connected with the connection component.Bicycle front fork of the invention is connected by connection component with undercarriage leg, while reducing construction weight, also enhances its applicability to flying field, and structure type is simple and manufacturing cost is cheap.
Description
Technical field
The present invention relates to the field of solar powered aircraft more particularly to a kind of lightweight undercarriages for solar energy unmanned plane.
Background technique
Solar powered aircraft mainly has U.S. NASA series, Switzerland Solar Impulse series and Britain both at home and abroad at present
Zephyr series, wherein NASA series unmanned plane undercarriage stretches out two primary load bearing branch by connector from girder forward and downward
Bar installs wheel respectively, and collectively constitutes landing gear structure with other rectifications and support construction, which is primarily adapted for use in
Flying-wing, and structure is complex；And Zephyr series and the solar energy unmanned plane of Google development in the recent period are without undercarriage
Structure provides initial driving force by people or other external force and realizes taking off for unmanned plane, fixed propeller by flame-out in flight
In the position parallel with wing, the form of ground landing is wiped using ventral, this landing mode is primarily adapted for use in that the span is small, weight is low
Solar powered aircraft；It is big that Solar Impulse series belongs to someone's solar powered aircraft its airframe-to-fuel weight ratio, is risen and fallen using extendible
Frame, landing gear structure includes: jack, buffer etc. and main force support structure uses metal material, therefore construction weight is excessive.
And the solar energy unmanned plane span of our hospital's independent research is big, weight is high, according to the landing mode of no landing gear structure, easily makes
It is destroyed at aircraft large range damage, while its airframe-to-fuel weight ratio is low, requires construction weight harsh, and retractable undercarriage is not yet
It is applicable in, therefore uses material of the composite material as undercarriage main force support structure, the cloth below girder to reduce construction weight
Undercarriage is set, wheel is assisted in vertical fin arranged beneath, forms " bicycle " formula undercarriage with undercarriage below girder.
The undercarriage such as is mainly used for the internal field transfer of solar powered aircraft, ground roll-out, takes off, lands at the tasks.And show
The Inspection Aircraft Wheels that some unmanned plane some select diameter small, although weight is lower to the more demanding of flying field；Some choosings
With the big Inspection Aircraft Wheels of diameter, although improving higher to the applicability weight in place.There is presently no a kind of unmanned planes
Landing gear structure reaches that structure type is simple, weight is low, strong applicability, the convenient and low-cost requirement of maintenance and repair.
Summary of the invention
Technical problem solved by the present invention is compared with the prior art, providing a kind of for the light of solar energy unmanned plane
Matter undercarriage, so that structure type is simple, weight is low, strong applicability, maintenance and repair are convenient and low in cost.
The object of the invention is achieved by the following technical programs: a kind of lightweight undercarriage for solar energy unmanned plane,
It include: bicycle tyre, bicycle front fork, connection component, undercarriage leg and sleeve；Wherein, the bicycle tyre passes through
Bearing is connected with the bicycle front fork；The bicycle front fork is connected by the connection component with the undercarriage leg
It connects；The sleeve is sheathed on the outer surface of the undercarriage leg and is connected with the connection component.
In the above-mentioned lightweight undercarriage for solar energy unmanned plane, the radius of the bicycle tyre is 15cm-
25cm。
In the above-mentioned lightweight undercarriage for solar energy unmanned plane, before the center of circle to the bicycle of the bicycle tyre
The distance range of the bottom end of the axis of fork is 20cm -30cm.
In the above-mentioned lightweight undercarriage for solar energy unmanned plane, the connection component includes: the first thrust ball bearing,
A connection piece, cylinder, the second connector, internal screw thread bushing, band cap screw rod and the second thrust ball bearing；Wherein, it described first pushes away
Power ball bearing is connected with the lower end of the axis of the bicycle front fork；First connector is sheathed on the axis, and described first
Connector is mutually crimped with the upper surface of first thrust ball bearing；The cylindrical sleeve is set to the axis and connect with described first
Part mutually crimps；Second thrust ball bearing is connected with the upper end of the axis of the bicycle front fork；The second connector set
Set on the axis, second connector is connected with the upper end of the cylinder, also, second connector and described second
The lower end surface of thrust ball bearing mutually crimps；The sleeve is connected with first connector；The internal screw thread bushing is set to
In the axis, the band cap screw rod is connect with the internal screw thread bush threads, and the cap with cap screw rod is stuck in described
The upper surface of two thrust ball bearings.
In the above-mentioned lightweight undercarriage for solar energy unmanned plane, first connector includes: rounded projections, circle
Detent block and annulus；Wherein, the rounded projections are connected with the internal circle of the annulus, it is described circle detent block with it is described
The upper surface of annulus is connected, and the center of circle of the rounded projections, the center of circle of the round detent block and the annulus
The center of circle coincides；The lower end surface of the rounded projections is mutually crimped with the upper surface of first thrust ball bearing；The annulus
Upper surface mutually crimped with the cylinder, also, the cylinder is located at the outside of the round detent block, the internal diameter of the cylinder
It is equal with the outer diameter of the round detent block.
In the above-mentioned lightweight undercarriage for solar energy unmanned plane, second connector includes: the second round detent block
With the second annulus；Wherein, the described second round detent block is connected with the upper surface of second annulus, also, described second
The center of circle of round detent block and the center of circle of second annulus coincide；Described second round detent block is placed on second thrust
Ball bearing, and the internal diameter of the described second round detent block is equal with the outer diameter of second thrust ball bearing；Second circle
Ring is connected with the cylinder, and the upper surface of second annulus is mutually crimped with the lower end of second thrust ball bearing.
In the above-mentioned lightweight undercarriage for solar energy unmanned plane, further includes: nut；Wherein, the nut is sheathed on institute
The screw rod with cap screw rod is stated, and between the cap with cap screw rod and internal screw thread bushing.
Compared with prior art, the present invention has the following advantages:
(1) present invention also enhances it while reducing construction weight by bicycle tyre and bicycle front fork
To the applicability of flying field, and structure type is simple and manufacturing cost is cheap；
(2) connection component form of the invention is simple, improves the convenience of connection structure examination and maintenance.
Detailed description of the invention
Fig. 1 shows the structural representation of the lightweight undercarriage for solar energy unmanned plane of the embodiment of the present invention offer
Figure；
In the lightweight undercarriage for solar energy unmanned plane provided Fig. 2 shows the embodiment of the present invention, connection component
Structural schematic diagram；
Fig. 3 is shown in the lightweight undercarriage for solar energy unmanned plane of the embodiment of the present invention offer, internal screw thread lining
The structural schematic diagram that set, nut are connected with cap screw rod；
Fig. 4 is shown in the lightweight undercarriage for solar energy unmanned plane of the embodiment of the present invention offer, internal screw thread lining
Set is squeezed into the structural schematic diagram of bicycle front fork；
Fig. 5 is shown in the lightweight undercarriage for solar energy unmanned plane of the embodiment of the present invention offer, the first connection
The structural schematic diagram of part；
Fig. 6 is shown in the lightweight undercarriage for solar energy unmanned plane of the embodiment of the present invention offer, the second connection
The structural schematic diagram of part；
Fig. 7 is shown in the lightweight undercarriage for solar energy unmanned plane of the embodiment of the present invention offer, the knot of sleeve
Structure schematic diagram.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings:
Fig. 1 shows the structural representation of the lightweight undercarriage for solar energy unmanned plane of the embodiment of the present invention offer
Figure.As shown in Figure 1, the lightweight undercarriage for solar energy unmanned plane includes bicycle tyre 1, bicycle front fork 2, connection group
Part, undercarriage leg 11 and sleeve 12.Wherein,
Bicycle tyre 1 is connected by bearing with bicycle front fork 2.It is to be appreciated that bicycle tyre 1 passes through axis
Holding the mode being connected with bicycle front fork 2 is well known mode, is no longer described in detail in the present embodiment.The present embodiment
The absorption of energy when the landing of solar energy unmanned plane may be implemented in the buffer capacity of bicycle tyre itself, so that advantageous protect
Solar energy unmanned plane.
Bicycle front fork 2 is connected by connection component with undercarriage leg 11.
Sleeve 12 is sheathed on the outer surface of undercarriage leg 11 and is connected with connection component.Specifically, 12 sets of sleeve exists
Sleeve 12 and undercarriage leg 11 are fixed together, sleeve by the outer surface of undercarriage leg 11 by epoxide-resin glue
12 are threadedly coupled with connection component.The structural schematic diagram of sleeve 12 is as shown in Figure 7.
When work, bicycle tyre 1, bicycle front fork 2, connection component, carbon pipe 11 and sleeve 12 have been collectively constituted and have been used for
The unmanned plane undercarriage of solar energy unmanned plane, bicycle tyre 1 can be good at being applicable in flying field.
The bicycle front fork of the present embodiment is connected by connection component with undercarriage leg, and construction weight is being reduced
Meanwhile its applicability to flying field is also enhanced, and structure type is simple and manufacturing cost is cheap.
In above-described embodiment, the radius of bicycle tyre 1 is 15cm -25cm.Specifically, the half of bicycle tyre 1
Diameter range is selected as 15cm -25cm, so that tire can be good at adapting to place.
In above-described embodiment, the distance range of the bottom end of the axis 21 in the center of circle of bicycle tyre 1 to bicycle front fork 2 is
20cm—30cm.Specifically, the bottom end of axis 21 of the center of circle of bicycle tyre 1 to bicycle front fork 2 apart from range of choice is
20cm -30cm enhances its applicability to flying field.
In the lightweight undercarriage for solar energy unmanned plane provided Fig. 2 shows the embodiment of the present invention, connection component
Structural schematic diagram.As shown in Fig. 2, connection component includes the first thrust ball bearing 3, the first connector 4, the connection of cylinder 5, second
Part 6, internal screw thread bushing 7, band cap screw rod 9 and the second thrust ball bearing 10.Specifically, the first thrust ball bearing 3 and the second thrust
What ball bearing 10 was well known to those skilled in the art, the present embodiment is no longer described in detail.Wherein,
First thrust ball bearing 3 is connected with the lower end of the axis 21 of bicycle front fork 2.When it is implemented, the first thrust ball
Bearing 3 is set in the outer surface of the lower end of axis 21, so that the first thrust ball bearing 3 is fixedly connected with the lower end of axis 21.
First connector 4 is sheathed on axis 21, and the first connector 4 is mutually crimped with the upper surface of the first thrust ball bearing 3.Specifically
, since the diameter of the cross section of the diameter and axis 21 of the center opening of the first connector 4 is roughly equal, so being pushed away by first
Power ball bearing 3 can be by the end caught thereon of the first connector 4.
Cylinder 5 is sheathed on axis 21 and crimps with 4 phase of the first connector.
Second thrust ball bearing 10 is connected with the upper end of the axis 21 of bicycle front fork 2.When it is implemented, the second thrust ball
Bearing 10 is set in the outer surface of the upper end of axis 21, so that the second thrust ball bearing 10 is fixedly connected with the upper end of axis 21.
Second connector 6 is sheathed on axis 21, and the second connector 6 is connected with the upper end of cylinder 5, also, the second connector 6
It is mutually crimped with the lower end surface of the second thrust ball bearing 10.Specifically, the diameter of the center opening of the second connector 6 and the cross of axis 21
The diameter in section is roughly equal, and the outer end of the second connector 6 is connected with the upper end of cylinder 5, the second connector 6 and the second thrust
The lower end surface of ball bearing 10 mutually crimps, so that cylinder 5 plays the role of support, the second thrust ball axis to the second connector 6
Hold 10 upper ends for being stuck in the second connector 6.
Sleeve 12 is connected with the first connector 4.When it is implemented, sleeve 12 offers the first threaded hole, it is corresponding,
First connector 4 offers the second threaded hole corresponding with the first threaded hole, and screw rod passes through the first threaded hole and the second screw thread
Sleeve 12 is connected by hole with the first connector 4.
As shown in Figure 2, Figure 3 and Figure 4, internal screw thread bushing 7 is set in axis 21, band cap screw rod 9 and 7 screw thread of internal screw thread bushing
Connection, and the cap with cap screw rod 9 is stuck in the upper surface of the second thrust ball bearing 10.Specifically, since axis 21 is hollow, general
Internal screw thread bushing 7 is expressed in axis 21, and internal screw thread bushing 7 is located at upper end and the axis 21 of the upper end of axis 21 and internal screw thread bushing 7
Upper end maintain an equal level, internal screw thread bushing 7 be it is hollow, inner wall is provided with screw thread, the inner wall spiral shell with cap screw rod 9 Yu internal screw thread bushing 7
Line connection, so that the cap with cap screw rod 9 is stuck in the upper surface of the second thrust ball bearing 10, so that axis 21 will not be due to
Gravity drops and is detached from the second thrust ball bearing 10 and the first thrust ball bearing 3.The present embodiment by internal screw thread bushing,
Nut and loosening when solving the problems, such as that bicycle front fork is connected by connection component with undercarriage leg with cap screw rod.
Fig. 5 is shown in the lightweight undercarriage of solar energy unmanned plane provided in an embodiment of the present invention, the knot of the first connector
Structure schematic diagram.As shown in figure 5, the first connector 4 includes: rounded projections 41, round detent block 42 and annulus 43.Wherein,
Rounded projections 42 are connected with the internal circle of annulus 43, and round detent block 42 is connected with the upper surface of annulus 43
It connects, and the center of circle in the center of circle of rounded projections 41, the center of circle of round detent block 42 and annulus 43 coincides.
The lower end surface of rounded projections 41 is mutually crimped with the upper surface of the first thrust ball bearing 3.Specifically, due to round convex
41 protrusion of portion is played, so that the lower end of rounded projections 41 forms a circular trough, circular trough and 3 phase of the first thrust ball bearing
Matching, the first thrust ball bearing 3 can be embedded in the circular trough.
The upper surface of annulus 43 is crimped with 5 phase of cylinder, also, cylinder 5 is located at the outside of round detent block 42, cylinder 5
Internal diameter is equal with the outer diameter of round detent block 42.Specifically, cylinder 5 is in contact with the upper surface of annulus 43, annulus 43 gives cylinder 5
A upward support force is provided, the internal diameter of cylinder 5 is equal with the outer diameter of round detent block 42, and round detent block 42 will be to justify
Cylinder 5 positions, prevent cylinder 5 is from moving left and right.
Fig. 6 is shown in the lightweight undercarriage of solar energy unmanned plane provided in an embodiment of the present invention, the knot of the second connector
Structure schematic diagram.As shown in fig. 6, the second connector 6 includes: the second round detent block 61 and the second annulus 62.Wherein,
Second round detent block 61 is connected with the upper surface of the second annulus 62, also, the circle of the second round detent block 61
The center of circle of the heart and the second annulus 62 coincides.
Second round detent block 61 is placed on the second thrust ball bearing 10, and the internal diameter and second of the second round detent block 61
The outer diameter of thrust ball bearing 10 is equal.Specifically, outer surface of second round 61 sets of block of the detent in the second thrust ball bearing 10, the
The outer diameter of the internal diameter and the second thrust ball bearing 10 of two round detent blocks 61 is roughly equal, also, the second thrust ball bearing 10
Lower end is in contact with the upper surface of the second annulus 62, to pass through the second round detent block 61 and the second annulus 62 for the second thrust
Ball bearing 10 is fixed on the specific position of axis 21.
Second annulus 62 is connected with cylinder 5, the lower end phase of the upper surface of the second annulus 62 and the second thrust ball bearing 10
Crimping.Specifically, the lower end of the second annulus 62 is connected with the upper end of cylinder 5, to have by cylinder 5 to the second annulus 62 a
Supporting role.
As shown in Figures 2 and 3, which further includes nut 8, wherein 8 sets of nut
Set on the screw rod with cap screw rod 9, and between the cap with cap screw rod 9 and internal screw thread bushing 7.Specifically, nut 8 with cap spiral shell
The screw flight of bar 9 connects, and nut 8 is positioned at the cap with cap screw rod 9 and internal screw thread bushing 7 between, the upper surface of nut 8 and with cap
The contact of the lower end surface of the cap of screw rod 9 tightly, the lower end surface of nut 8 and the upper surface of the second thrust ball bearing 10 tight contact between.
When due to vibration, band cap screw rod 9 can be detached from internal screw thread bushing 7, and the presence of nut 8 makes band cap screw rod 9 not
It can be detached from internal screw thread bushing 7,8 pairs of nut are played locking function with cap screw rod 9.
Bicycle front fork of the invention is connected by connection component with undercarriage leg, and the same of construction weight is being reduced
When, its applicability to flying field is also enhanced, and structure type is simple and manufacturing cost is cheap；And connection component form
Simply, the convenience of connection structure examination and maintenance is improved
Embodiment described above is the present invention more preferably specific embodiment, and those skilled in the art is in this hair
The usual variations and alternatives carried out in bright technical proposal scope should be all included within the scope of the present invention.
Claims (6)
1. a kind of lightweight undercarriage for solar energy unmanned plane, characterized by comprising: before bicycle tyre (1), bicycle
Pitch (2), connection component, undercarriage leg (11) and sleeve (12)；Wherein,
The bicycle tyre (1) is connected by bearing with the bicycle front fork (2)；
The bicycle front fork (2) is connected by the connection component with the undercarriage leg (11)；
The sleeve (12) is sheathed on the outer surface of the undercarriage leg (11) and is connected with the connection component；
Wherein, the connection component includes: the first thrust ball bearing (3), the first connector (4), cylinder (5), the second connector
(6), internal screw thread bushing (7), band cap screw rod (9) and the second thrust ball bearing (10)；Wherein,
First thrust ball bearing (3) is connected with the lower end of the axis (21) of the bicycle front fork (2)；
First connector (4) is sheathed on the axis (21), first connector (4) and first thrust ball bearing
(3) upper surface mutually crimps；
The cylinder (5) is sheathed on the axis (21) and mutually crimps with first connector (4)；
Second thrust ball bearing (10) is connected with the upper end of the axis (21) of the bicycle front fork (2)；
Second connector (6) is sheathed on the axis (21), the upper end phase of second connector (6) and the cylinder (5)
Connection, also, second connector (6) is mutually crimped with the lower end surface of second thrust ball bearing (10)；
The sleeve (12) is connected with first connector (4)；
The internal screw thread bushing (7) is set in the axis (21), the band cap screw rod (9) and internal screw thread bushing (7) spiral shell
Line connection, and the cap of the band cap screw rod (9) is stuck in the upper surface of second thrust ball bearing (10).
2. the lightweight undercarriage according to claim 1 for solar energy unmanned plane, which is characterized in that the bicycle quick
The radius of tire (1) is 15cm -25cm.
3. the lightweight undercarriage according to claim 1 for solar energy unmanned plane, which is characterized in that the bicycle quick
The center of circle of tire (1) to the bicycle front fork (2) axis (21) bottom end distance range be 20cm -30cm.
4. the lightweight undercarriage according to claim 1 for solar energy unmanned plane, which is characterized in that first connection
Part (4) includes: rounded projections (41), round detent block (42) and annulus (43)；Wherein,
The rounded projections (41) are connected with the internal circle of the annulus (43), the circle detent block (42) and the circle
The upper surface of ring (43) is connected, and the center of circle of the rounded projections (41), the round detent block (42) the center of circle with
The center of circle of the annulus (43) coincides；
The lower end surface of the rounded projections (41) is mutually crimped with the upper surface of first thrust ball bearing (3)；
The upper surface of the annulus (43) is mutually crimped with the cylinder (5), also, the cylinder (5) is located at the round detent
The outside of block (42), the internal diameter of the cylinder (5) are equal with the outer diameter of the round detent block (42).
5. the lightweight undercarriage according to claim 1 for solar energy unmanned plane, which is characterized in that second connection
Part (6) includes: the second round detent block (61) and the second annulus (62)；Wherein,
Described second round detent block (61) is connected with the upper surface of second annulus (62), also, described second is round
The center of circle of detent block (61) and the center of circle of second annulus (62) coincide；
Described second round detent block (61) is placed on second thrust ball bearing (10), and the described second round detent block
(61) internal diameter is equal with the outer diameter of second thrust ball bearing (10)；
Second annulus (62) is connected with the cylinder (5), and the upper surface of second annulus (62) is pushed away with described second
The lower end of power ball bearing (10) mutually crimps.
6. the lightweight undercarriage according to claim 1 for solar energy unmanned plane, which is characterized in that further include: nut
(8)；Wherein, the nut (8) is sheathed on the screw rod of the band cap screw rod (9), and be located at the cap of the band cap screw rod (9) with it is interior
Between screw-thread bush (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610917094.8A CN106314767B (en) | 2016-10-20 | 2016-10-20 | A kind of lightweight undercarriage for solar energy unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610917094.8A CN106314767B (en) | 2016-10-20 | 2016-10-20 | A kind of lightweight undercarriage for solar energy unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106314767A CN106314767A (en) | 2017-01-11 |
| CN106314767B true CN106314767B (en) | 2019-02-19 |
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ID=57819185
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| CN201610917094.8A Active CN106314767B (en) | 2016-10-20 | 2016-10-20 | A kind of lightweight undercarriage for solar energy unmanned plane |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190921220A (en) * | 1909-09-16 | 1911-05-25 | James Dennis Roots | An Improved Flying Machine. |
| CN1161286A (en) * | 1996-12-11 | 1997-10-08 | 石家智 | Vehicle convertible into aircraft |
| CN102730183A (en) * | 2012-07-03 | 2012-10-17 | 北京航空航天大学 | Novel solar airplane |
| CN104071273A (en) * | 2013-03-26 | 2014-10-01 | 叶礼发 | Novel three-wheel baby carrier with rear-control steering |
| CN204606044U (en) * | 2015-02-11 | 2015-09-02 | 蔡志忠 | A kind of detachable mini-motorcycle |
-
2016
- 2016-10-20 CN CN201610917094.8A patent/CN106314767B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190921220A (en) * | 1909-09-16 | 1911-05-25 | James Dennis Roots | An Improved Flying Machine. |
| CN1161286A (en) * | 1996-12-11 | 1997-10-08 | 石家智 | Vehicle convertible into aircraft |
| CN102730183A (en) * | 2012-07-03 | 2012-10-17 | 北京航空航天大学 | Novel solar airplane |
| CN104071273A (en) * | 2013-03-26 | 2014-10-01 | 叶礼发 | Novel three-wheel baby carrier with rear-control steering |
| CN204606044U (en) * | 2015-02-11 | 2015-09-02 | 蔡志忠 | A kind of detachable mini-motorcycle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106314767A (en) | 2017-01-11 |
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