CN208021774U - Small General Aircraft support device - Google Patents
Small General Aircraft support device Download PDFInfo
- Publication number
- CN208021774U CN208021774U CN201820506123.6U CN201820506123U CN208021774U CN 208021774 U CN208021774 U CN 208021774U CN 201820506123 U CN201820506123 U CN 201820506123U CN 208021774 U CN208021774 U CN 208021774U
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- China
- Prior art keywords
- aircraft
- leg
- supporting rod
- support device
- connect
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Abstract
The utility model discloses a kind of Small General Aircraft support devices, including pedestal, aircraft bracket and the bolt for being set to aircraft bracket and being connect with aircraft for realizing aircraft bracket, the holder that pedestal includes supporting rod and connect with supporting rod and be used to provide a supporting role, holder setting is multiple, and aircraft bracket is set on supporting rod.The Small General Aircraft support device of the utility model can use in the case of surface condition inspection, and use is easy to carry, and movement is simple and convenient, improves the convenience used.
Description
Technical field
The utility model belongs to General Aviation technical field of auxiliary equipment, specifically, the utility model is related to a kind of small
Type general-purpose aircraft support device.
Background technology
Existing Small General Aircraft support device is all a kind of cart type and with the structure of support top, this support
Device is mainly using more convenient under conditions of more smooth.But under conditions of meadow, sand ground and ice and snow road, device moves
Dynamic more inconvenient, the place for needing searching more smooth when in use could use, while there is also carrying and transport are relatively more tired
Difficult problem.
Utility model content
The utility model aims to solve at least one of the technical problems existing in the prior art.For this purpose, the utility model carries
For a kind of Small General Aircraft support device, it is therefore an objective to improve the convenience used.
To achieve the goals above, the technical solution that the utility model is taken is：Small General Aircraft support device, including
Pedestal, aircraft bracket and the bolt for being set to aircraft bracket and being connect with aircraft for realizing aircraft bracket, pedestal include support
Bar and the holder for being connect with supporting rod and being used to provide a supporting role, holder setting is multiple, and aircraft bracket is set on supporting rod.
The aircraft bracket is U-shaped structure and aircraft bracket opening upwards.
The bolt is equipped with the limited block for playing position-limiting action in the axial direction, and limited block is rotation connection with bolt.
The holder include the first leg being connect with the supporting rod and the second supporting leg and with first leg and second
The bottom plate of supporting leg connection.
The upper end of the first leg is connect with the supporting rod, and the lower end of first leg is connect with the bottom plate, described
The upper end of second supporting leg is connect with supporting rod and the upper end of the second supporting leg be located at first leg upper end lower section, the second supporting leg
Lower end and the lower end of bottom plate connection and the second supporting leg are located between the lower end and supporting rod of first leg.
The holder is arranged three, and three holders are uniformly distributed for the circumferential direction along the supporting rod.
The Small General Aircraft support device of the utility model can use in the case of surface condition inspection, use
Easy to carry, movement is simple and convenient, improves the convenience used.
Description of the drawings
This specification includes the following drawings, and shown content is respectively：
Fig. 1 is the structural schematic diagram of the utility model Small General Aircraft support device；
Fig. 2 is the front view of the utility model Small General Aircraft support device；
In figure label for：1, limited block；2, supporting rod；3, aircraft bracket；301, the first connecting plate；302, the second connection
Plate；303, third connecting plate；4, bolt；401, pin body；402, draw ring；5, bottom plate；6, first leg；7, the second supporting leg.
Specific implementation mode
Below against attached drawing, by the description of the embodiment, making to specific embodiment of the present utility model further detailed
Thin explanation, it is therefore an objective to help those skilled in the art to the design of the utility model, technical solution have it is more complete, accurate and
Deep understanding, and contribute to its implementation.
As depicted in figs. 1 and 2, the utility model provides a kind of Small General Aircraft support device, including pedestal, aircraft
Bracket 3 and the bolt 4 for being set to aircraft bracket 3 and being connect with aircraft for realizing aircraft bracket 3, pedestal include 2 He of supporting rod
The holder for being connect with supporting rod 2 and being used to provide a supporting role, holder setting is multiple, and aircraft bracket 3 is set on supporting rod 2.
Specifically, as depicted in figs. 1 and 2, aircraft bracket 3 is U-shaped structure and 3 opening upwards of aircraft bracket, aircraft support
Seat 3 is made of sequentially connected first connecting plate 301, the second connecting plate 302 and third connecting plate 303, the first connecting plate 301
It is to be oppositely arranged and the first connecting plate 301 and third connecting plate 303 are parallel, the second connecting plate 302 with third connecting plate 303
Between the first connecting plate 301 and third connecting plate 303 and the second connecting plate 302 and the first connecting plate 301 and third connecting plate
303 be that vertical connection, the first connecting plate 301 and third connecting plate 303 extend towards the top of the second connecting plate 302, forms U-shaped
A through-hole for allowing bolt 4 to pass through is respectively set on the first connecting plate 301 and third connecting plate 303 in the aircraft bracket 3 of structure,
The through-hole is circular hole and the axis of through-hole is parallel with the second connecting plate 302.
As depicted in figs. 1 and 2, bolt 4 is located at the top of the second connecting plate 302, the axis of bolt 4 and the second connecting plate
302 is parallel, and bolt 4 includes sequentially connected draw ring 402 and pin body 401, and pin body 401 is cylinder, draw ring 402
For cirque structure, draw ring 402 is fixedly connected with one end of bolt 4 and draw ring 402 is located at the outside of aircraft bracket 3, draw ring 402
Axis and pin body 401 axis perpendicular, by draw ring 402 convenient for control bolt 4 it is movable along the axial direction, aircraft tool
There is the axis hole for allowing the pin body 401 of bolt 4 to be inserted into.Bolt 4 is equipped with the limited block 1 for playing position-limiting action in the axial direction,
Limited block 1 is rotation connection with bolt 4.Limited block 1 and draw ring 402 are respectively arranged at one end of pin body 401, draw ring 402
Overall diameter be more than the diameter of through-hole being arranged on the first connecting plate 301, to which draw ring 402 and limited block 1 match, Ke Yi
Position-limiting action is played to bolt 4 on axial, bolt 4 can be prevented to be detached from after aircraft bracket 3 is connect with aircraft, is improved to aircraft
The reliability of support.
As depicted in figs. 1 and 2, the end of pin body 401 is equipped with the storage tank for allowing limited block 1 to be embedded in, which is
In the groove that the end face of pin body 401 starts to be formed axially towards the internal recess of pin body 401, which is simultaneously
Open slot so that limited block 1 can be dismantled with bolt 4, easy to disassemble.Limited block 1 is embedded in storage tank and limited block 1 is by turning
Axis is connect with pin body 401, the axis perpendicular of the axis and pin body 401 of the shaft, and the length of limited block 1 is more than the
The diameter for the through-hole being arranged on three connecting plates 303, in a state of use, the axis of the length direction and pin body 401 of limited block 1
Line is perpendicular, limited block 1 and the outside positioned at aircraft bracket 3, and then can play position-limiting action to bolt 4 in the axial direction.
As depicted in figs. 1 and 2, holder includes the first leg 6 being connect with supporting rod 2 and the second supporting leg 7 and with first
The bottom plate 5 of supporting leg 6 and the connection of the second supporting leg 7.The upper end of first leg 6 is connect with supporting rod 2, the lower end and bottom of first leg 6
Plate 5 connects, and the upper end of the second supporting leg 7 is connect with supporting rod 2 and the upper end of the second supporting leg 7 is located under the upper end of first leg 6
Side, the lower end of the second supporting leg 7 is connect with bottom plate 5 and the lower end of the second supporting leg 7 be located at first leg 6 lower end and supporting rod 2 it
Between.The length of first leg 6 is more than the length of the second supporting leg 7, and the second supporting leg 7 is located at the top of first leg 6, and supporting rod 2 is
Cylinder, the upper end of supporting rod 2 is fixedly connected with the second connecting plate 302 and supporting rod 2 and the second connecting plate 302 are perpendicular, branch
The axis of strut 2 and with the axis perpendicular of bolt 4, the lower end of supporting rod 2 is fixedly connected with the second supporting leg 7.First leg 6
It is acute angle, the length direction and supporting rod of the second supporting leg 7 to have angle and the angle between length direction and the axis of supporting rod 2
It is acute angle, the folder between the length direction and the axis of supporting rod 2 of first leg 6 to have angle and the angle between 2 axis
Angle is less than the angle between the length direction and the axis of supporting rod 2 of the second supporting leg 7, and first leg 6 and the second supporting leg 7 are to tilt
Setting, the stability of the pedestal of formation is good, and support reliability is high, improves the structural strength of entire support device.
As depicted in figs. 1 and 2, bottom plate 5 is located at the obliquely downward of supporting rod 2, and bottom plate 5 is tablet, bottom plate 5 and the second connecting plate
302 is parallel, bottom plate 5 and the lower section positioned at first leg 6 and the second supporting leg 7, bottom plate 5 and first leg 6 and the second supporting leg 7
Lower end is fixedly connected.The setting of bottom plate 5, it is ensured that the stability of support device and the adaptability to ground.
As depicted in figs. 1 and 2, in the present embodiment, holder is arranged three altogether, and three holders are the circumferential direction along supporting rod 2
It is uniformly distributed, forms supported at three point, stability is more preferable.
The utility model is exemplarily described above in association with attached drawing.Obviously, the utility model implements not
It is limited by aforesaid way.As long as using the various unsubstantialities of the methodology and technical solution progress of the utility model
Improvement；Or it is not improved, above-mentioned design and technical solution by the utility model directly apply to other occasions, at this
Within the protection domain of utility model.
Claims (6)
1. Small General Aircraft support device, it is characterised in that：Including pedestal, aircraft bracket and it is set to aircraft bracket and is used for
Realize that the bolt that aircraft bracket is connect with aircraft, pedestal include supporting rod and connect with supporting rod and be used to provide a supporting role
Holder, holder setting is multiple, and aircraft bracket is set on supporting rod.
2. Small General Aircraft support device according to claim 1, it is characterised in that：The aircraft bracket is U-shaped knot
Structure and aircraft bracket opening upwards.
3. Small General Aircraft support device according to claim 1 or 2, it is characterised in that：The bolt, which is equipped with, to be used
The limited block of position-limiting action in the axial direction, limited block are rotation connection with bolt.
4. Small General Aircraft support device according to claim 1 or 2, it is characterised in that：The holder includes and institute
State the first leg and the second supporting leg and the bottom plate being connect with first leg and the second supporting leg that supporting rod connects.
5. Small General Aircraft support device according to claim 4, it is characterised in that：The upper end of the first leg with
Supporting rod connection, the lower end of first leg are connect with the bottom plate, the upper end of second supporting leg connect with supporting rod and
The upper end of second supporting leg is located at the lower section of the upper end of first leg, and the lower end of the second supporting leg connect with bottom plate and under the second supporting leg
End is between the lower end and supporting rod of first leg.
6. Small General Aircraft support device according to claim 5, it is characterised in that：The holder setting three, three
A holder is uniformly distributed for the circumferential direction along the supporting rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820506123.6U CN208021774U (en) | 2018-04-11 | 2018-04-11 | Small General Aircraft support device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820506123.6U CN208021774U (en) | 2018-04-11 | 2018-04-11 | Small General Aircraft support device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208021774U true CN208021774U (en) | 2018-10-30 |
Family
ID=63908615
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820506123.6U Active CN208021774U (en) | 2018-04-11 | 2018-04-11 | Small General Aircraft support device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208021774U (en) |
-
2018
- 2018-04-11 CN CN201820506123.6U patent/CN208021774U/en active Active
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|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |