CN108438212A - A kind of UAV Landing auxiliary device - Google Patents
A kind of UAV Landing auxiliary device Download PDFInfo
- Publication number
- CN108438212A CN108438212A CN201810051718.1A CN201810051718A CN108438212A CN 108438212 A CN108438212 A CN 108438212A CN 201810051718 A CN201810051718 A CN 201810051718A CN 108438212 A CN108438212 A CN 108438212A
- Authority
- CN
- China
- Prior art keywords
- buffing pad
- fuselage
- pedestal
- diameter
- motion bar
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
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
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
-
- 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
- B64C25/66—Convertible alighting gear; Combinations of different kinds of ground or like engaging elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)
Abstract
The invention discloses a kind of UAV Landing auxiliary devices, including fuselage and buffing pad, the outer surface of fuselage, which is symmetrically welded, is equipped with horn, the end of horn is rotatably connected to wing, the lower surface of fuselage is equidistantly integrally formed with pedestal, the lower surface oblique weld of pedestal is equipped with supporting rod, and the end of supporting rod is rotatably connected to buffing pad, and the inside of buffing pad offers cylindrical dashpot；A kind of UAV Landing auxiliary device, including buffing pad are the fixed seat of rectangular-shape, and the lower surface of fuselage is symmetrically arranged with pedestal and supporting rod, and the surface pivots for simultaneously supporting bar are connected with the buffing pad with certain buffer capacity；Buffing pad is internally provided with spring and buffer disc, spring gives buffer disc certain buffer capacity, and the surface vertical welding of simultaneous buffering disk is equipped with motion bar, and the end of motion bar, which is equipped with, connects pawl, connecing pawl can use on the ground of bumpy sections, improve stability when fuselage landing.
Description
Technical field
The present invention relates to unmanned plane equipment technical field, specially a kind of UAV Landing auxiliary device.
Background technology
Unmanned plane is all widely used since its flexibility is high and the requirement of landing condition is relatively low in civil and military
On the way, it even if today more and more ripe in automatic flight control system, such unmanned plane taking off under conditions of complexity and drops
Fall still restrict only its apply in wider field, under conditions of some complexity, especially put down comparing the ground jolted
Takeoff and landing on platform, flight control system and controllers to such unmanned plane are all a huge challenges, traditionally,
Such unmanned plane is based primarily upon artificial vision to control when automatic or manual operation is landed, this product taken a long time
Tired, without the solution of complete set, therefore unmanned plane is easy to tumble, and causes paddle to ruin machine and dies, we carry thus
Go out a kind of UAV Landing auxiliary device for solving the above problems.
Invention content
It is mentioned above in the background art to solve the purpose of the present invention is to provide a kind of UAV Landing auxiliary device
Problem.
To achieve the above object, the present invention provides the following technical solutions：A kind of UAV Landing auxiliary device, including fuselage
And buffing pad, the outer surface of the fuselage, which is symmetrically welded, is equipped with horn, and the end of the horn is rotatably connected to wing, described
Equidistantly integrally formed with pedestal, the lower surface oblique weld of the pedestal is equipped with supporting rod, the branch for the lower surface of fuselage
The end of strut is rotatably connected to buffing pad, and the inside of the buffing pad offers cylindrical dashpot, the bottom of the dashpot
Portion is installed with spring, and the upper surface of the spring is fitted with buffer disc, and the side surface middle part of the buffer disc is vertical
It is installed by welding with motion bar, the upper surface of the buffing pad offers circular loose slot, and the motion bar is set through loose slot
It sets, the end of the motion bar is installed by welding with chassis, and the surface annular on the chassis, which is equidistantly fixedly connected with, connects pawl, described slow
Mounting base is arranged in one side surface vertical welding of red seat, and the surface of the mounting base offers rectangular fluting, the fluting
Inside is installed with shaft, and the surface pivots of the shaft are arranged with idler wheel.
Preferably, the fuselage is the cavity mechanism that lower surface is X-shaped, and the horn shares 4, and is symmetricly set on
Around fuselage flies, the pedestal is circular disk-like structure, and the quantity of the pedestal shares 2, and is symmetricly set under fuselage
Surface both sides.
Preferably, the diameter of the supporting rod is less than the diameter of pedestal, which is the metal fixed link of " L " shape, branch
The end of strut is rotatably connected in the middle part of the side surface of buffing pad, which is the fixed seat of rectangular-shape.
Preferably, the diameter of the dashpot and the diameter of buffer disc are identical, and the length of the dashpot is less than buffing pad
Length, the diameter of the motion bar is identical as the diameter of loose slot, and the length of the motion bar is not less than the half for buffering slot length.
Preferably, the mounting base is square metal fixed seat, and the quantity of the mounting base shares 4, and symmetrically sets two-by-two
The side upper and lower surface in buffing pad is set, mounting base obtains the metal structure that section is spill, the roller surface and mounting base
The tangent setting of inner wall.
Preferably, the diameter on the chassis and the diameter of buffer disc are identical, the quantity for connecing pawl at least 3, and ring
Shape is distributed in around chassis.
Compared with prior art, the beneficial effects of the invention are as follows：
1. buffing pad 6 is the fixed seat of rectangular-shape, the lower surface of fuselage is symmetrically arranged with pedestal and supporting rod, props up simultaneously
The surface pivots of strut are connected with the buffing pad with certain buffer capacity.
2. buffing pad is internally provided with spring and buffer disc, spring gives buffer disc certain buffer capacity, simultaneous buffering disk
Surface vertical welding motion bar is installed, the end of motion bar, which is equipped with, connects pawl, and connecing pawl can use on the ground of bumpy sections, carry
Stability when high fuselage landing.
3. being switchable to idler wheel when road surface is relatively flat equipped with idler wheel in the side of buffing pad in addition, it is made to fall
It can be slided according to actual conditions when ground.
Description of the drawings
Fig. 1 is structure of the invention reverse side schematic diagram；
Fig. 2 is structure enlargement diagram at A in Fig. 1；
Fig. 3 is buffing pad structural schematic diagram of the present invention.
In figure：1 fuselage, 2 horns, 3 wings, 4 pedestals, 5 supporting rods, 6 buffing pads, 7 dashpots, 8 springs, 9 buffer discs, 10
Loose slot, 11 motion bars, 12 chassis, 13 connect pawl, 14 mounting bases, 15 shafts, 16 idler wheels.
Specific implementation mode
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
- 3 are please referred to Fig.1, the present invention provides a kind of technical solution：A kind of UAV Landing auxiliary device, including 1 He of fuselage
Buffing pad 6, the outer surface of fuselage 1, which is symmetrically welded, is equipped with horn 2, and the end of horn 2 is rotatably connected to wing 3, under fuselage 1
Surface is equidistantly integrally formed with pedestal 4, and the lower surface oblique weld of pedestal 4 is equipped with supporting rod 5, and the end of supporting rod 5 turns
Dynamic to be connected with buffing pad 6, the inside of buffing pad 6 offers cylindrical dashpot 7, and the bottom of dashpot 7 is installed with spring
8, the upper surface of spring 8 is fitted with buffer disc 9, and the side surface middle part vertical welding of buffer disc 9 is equipped with motion bar 11, delays
The upper surface of red seat 6 offers circular loose slot 10, and motion bar 11 is arranged through loose slot 10, the end weldering of the motion bar 11
It connects and chassis 12 is installed, the surface annular on chassis 12, which is equidistantly fixedly connected with, connects pawl 13, a side surface vertical welding of buffing pad 6
Setting mounting base 14 is connect, the surface of mounting base 14 offers rectangular fluting, and the inside of fluting is installed with shaft 15, shaft
15 surface pivots are arranged with idler wheel 16.
Further, as shown in Figure 1, fuselage 1 is the cavity mechanism that lower surface is X-shaped, horn 2 shares 4, and symmetrical
Setting is around fuselage 1 flies, and pedestal 4 is circular disk-like structure, and the quantity of the pedestal 4 shares 2, and is symmetricly set on fuselage
1 lower surface both sides；The diameter of supporting rod 5 is less than the diameter of pedestal 4, which is the metal fixed link of " L " shape, support
The end of bar 5 is rotatably connected in the middle part of the side surface of buffing pad 6, which is the fixed seat of rectangular-shape, under fuselage 1
Surface is symmetrically arranged with pedestal 4 and supporting rod, and the surface pivots for simultaneously supporting bar 5 are connected with the buffering with certain buffer capacity
Seat 6.
Further, as shown in Fig. 2, the diameter of dashpot 7 is identical as the diameter of buffer disc 9, the length of the dashpot 7 is small
Identical as the diameter of loose slot 10 in the diameter of the length of buffing pad 6, motion bar 11, the length of the motion bar 11 is not less than buffering
The half of 7 length of slot；Mounting base 14 is square metal fixed seat, and the quantity of the mounting base 14 shares 4, and is symmetrical arranged two-by-two
In the side upper and lower surface of buffing pad 6, mounting base 14 obtains the metal structure that section is spill, 16 surface of idler wheel and mounting base 14
The tangent setting of inner wall；The diameter on chassis 12 is identical as the diameter of buffer disc 9, connects the quantity at least 3 of pawl 13, and annular point
Cloth is around chassis 12, and buffing pad 6 is internally provided with spring 8 and buffer disc 9, and spring 8 gives buffer disc 9 certain buffer capacity
The surface vertical welding of power, simultaneous buffering disk 9 is equipped with motion bar 11, and the end of motion bar 11, which is equipped with, connects pawl 13, and connecing pawl 13 can
It is used on the ground of bumpy sections, improves stability when fuselage 1 lands, be equipped with idler wheel 16 in the side of buffing pad 6 in addition, when
When road surface is relatively flat, it is switchable to idler wheel 16, makes it that can be slided according to actual conditions in landing.
Operation principle：Buffing pad 6 in the present invention is the fixed seat of rectangular-shape, and the lower surface of fuselage 1 is symmetrically arranged with
Pedestal 4 and supporting rod, the surface pivots for simultaneously supporting bar 5 are connected with the buffing pad 6 with certain buffer capacity；Buffing pad 6
It is internally provided with spring 8 and buffer disc 9, spring 8 gives buffer disc 9 certain buffer capacity, the surface vertical welding of simultaneous buffering disk 9
Motion bar 11 is installed, the end of motion bar 11, which is equipped with, connects pawl 13, and connecing pawl 13 can use on the ground of bumpy sections, improve fuselage
Stability when 1 landing, is switchable to idler wheel equipped with idler wheel 16 in the side of buffing pad 6 when road surface is relatively flat in addition
16, make it that can be slided according to actual conditions in landing.
It although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with
Understanding without departing from the principles and spirit of the present invention can carry out these embodiments a variety of variations, modification, replace
And modification, the scope of the present invention is defined by the appended.
Claims (6)
1. a kind of UAV Landing auxiliary device, including fuselage (1) and buffing pad (6), it is characterised in that：The fuselage (1)
Outer surface, which is symmetrically welded, is equipped with horn (2), and the end of the horn (2) is rotatably connected to wing (3), the fuselage (1)
Equidistantly integrally formed with pedestal (4), the lower surface oblique weld of the pedestal (4) is equipped with supporting rod (5), described for lower surface
The end of supporting rod (5) is rotatably connected to buffing pad (6), and the inside of the buffing pad (6) offers cylindrical dashpot (7),
The bottom of the dashpot (7) is installed with spring (8), and the upper surface of the spring (8) is fitted with buffer disc (9), institute
The side surface middle part vertical welding for stating buffer disc (9) is equipped with motion bar (11), and the upper surface of the buffing pad (6) offers
Circular loose slot (10), the motion bar (11) are arranged through loose slot (10), the end welding installation of the motion bar (11)
There is chassis (12), the surface annular of the chassis (12), which is equidistantly fixedly connected with, connects pawl (13), the side of the buffing pad (6)
Surface vertical welding setting mounting base (14), the surface of the mounting base (14) offer rectangular fluting, the fluting it is interior
Portion is installed with shaft (15), and the surface pivots of the shaft (15) are arranged with idler wheel (16).
2. a kind of UAV Landing auxiliary device according to claim 1, it is characterised in that：The fuselage (1) is following table
Face is the cavity mechanism of X-shaped, and the horn (2) shares 4, and is symmetricly set on fuselage (1) and flies surrounding, the pedestal (4)
Quantity for circular disk-like structure, the pedestal (4) shares 2, and is symmetricly set on the lower surface both sides of fuselage (1).
3. a kind of UAV Landing auxiliary device according to claim 1, it is characterised in that：The supporting rod (5) it is straight
Diameter is less than the diameter of pedestal (4), which is the metal fixed link of " L " shape, and the end of supporting rod (5) is rotatably connected on
In the middle part of the side surface of buffing pad (6), which is the fixed seat of rectangular-shape.
4. a kind of UAV Landing auxiliary device according to claim 1, it is characterised in that：The dashpot (7) it is straight
Diameter is identical as the diameter of buffer disc (9), and the length of the dashpot (7) is less than the length of buffing pad (6), the motion bar (11)
Diameter is identical as the diameter of loose slot (10), and the length of the motion bar (11) is not less than the half of dashpot (7) length.
5. a kind of UAV Landing auxiliary device according to claim 1, it is characterised in that：The mounting base (14) is side
The quantity of shape metal fixed seat, the mounting base (14) shares 4, and is symmetricly set on following table on the side of buffing pad (6) two-by-two
Face, mounting base (14) obtain the metal structure that section is spill, and idler wheel (16) surface and the inner wall of mounting base (14) are tangent
Setting.
6. a kind of UAV Landing auxiliary device according to claim 1, it is characterised in that：The diameter of the chassis (12)
It is identical as the diameter of buffer disc (9), the quantity for connecing pawl (13) at least 3, and annular spread is around chassis (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810051718.1A CN108438212A (en) | 2018-01-18 | 2018-01-18 | A kind of UAV Landing auxiliary device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810051718.1A CN108438212A (en) | 2018-01-18 | 2018-01-18 | A kind of UAV Landing auxiliary device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108438212A true CN108438212A (en) | 2018-08-24 |
Family
ID=63191065
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810051718.1A Pending CN108438212A (en) | 2018-01-18 | 2018-01-18 | A kind of UAV Landing auxiliary device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108438212A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE202013105380U1 (en) * | 2013-11-26 | 2014-01-10 | Industrieanlagen-Betriebsgesellschaft Mbh | Chassis for a light aircraft or an unmanned aerial vehicle and aircraft with such a chassis |
| CN104787309A (en) * | 2015-05-12 | 2015-07-22 | 厦门大学 | Landing gear of rotor unmanned aerial vehicle (UAV) |
| CN205113695U (en) * | 2015-11-21 | 2016-03-30 | 长沙学院 | Four rotors aircraft of taking photo by plane |
| CN106828891A (en) * | 2017-03-10 | 2017-06-13 | 太仓韬信信息科技有限公司 | A kind of rotary undercarriage of unmanned plane |
| CN107187588A (en) * | 2017-05-06 | 2017-09-22 | 深圳市雷凌广通技术研发有限公司 | A kind of Intelligent unattended machine with safety and shock-absorption function |
| CN107344614A (en) * | 2017-07-19 | 2017-11-14 | 胡俊 | A kind of undercarriage buffer unit |
-
2018
- 2018-01-18 CN CN201810051718.1A patent/CN108438212A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE202013105380U1 (en) * | 2013-11-26 | 2014-01-10 | Industrieanlagen-Betriebsgesellschaft Mbh | Chassis for a light aircraft or an unmanned aerial vehicle and aircraft with such a chassis |
| CN104787309A (en) * | 2015-05-12 | 2015-07-22 | 厦门大学 | Landing gear of rotor unmanned aerial vehicle (UAV) |
| CN205113695U (en) * | 2015-11-21 | 2016-03-30 | 长沙学院 | Four rotors aircraft of taking photo by plane |
| CN106828891A (en) * | 2017-03-10 | 2017-06-13 | 太仓韬信信息科技有限公司 | A kind of rotary undercarriage of unmanned plane |
| CN107187588A (en) * | 2017-05-06 | 2017-09-22 | 深圳市雷凌广通技术研发有限公司 | A kind of Intelligent unattended machine with safety and shock-absorption function |
| CN107344614A (en) * | 2017-07-19 | 2017-11-14 | 胡俊 | A kind of undercarriage buffer unit |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180824 |
|
| WD01 | Invention patent application deemed withdrawn after publication |