CN207403927U - A kind of shock absorption buffering mechanism of large size fixed-wing unmanned plane - Google Patents
A kind of shock absorption buffering mechanism of large size fixed-wing unmanned plane Download PDFInfo
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- CN207403927U CN207403927U CN201721367802.1U CN201721367802U CN207403927U CN 207403927 U CN207403927 U CN 207403927U CN 201721367802 U CN201721367802 U CN 201721367802U CN 207403927 U CN207403927 U CN 207403927U
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- piston
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- hydraulic cylinder
- shock absorption
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Abstract
The utility model discloses a kind of safe and reliable, stable bufferings, and damping efficiency height is at low cost, suitable for the shock absorption buffering mechanism of large-scale fixed-wing unmanned plane.Including oil hydraulic cylinder, the preceding end closure of oil hydraulic cylinder, open rearward end, hollow piston is inserted into the rear end of oil hydraulic cylinder, the preceding end closure of piston, open rearward end, the hollow piston tube of the rear end grafting of piston, the front opening of piston tube, end closure afterwards, the front end of piston tube is inserted into hollow piston, the inner cavity of piston is made to be connected with the inner cavity of piston tube, the rear end of piston tube is equipped with air valve, axially disposed installation through-hole on the front bulkhead of piston, main damping hole and secondary damping hole, insertion spring last item in installation through-hole, the front end of spring last item sets spacing head, the rear end of spring last item sets locking nut, the part that spring last item is located in piston is cased with valve successively from front to back, valve spring, all secondary damping holes are blocked under valve normality, main damping hole maintains a normally open.
Description
Technical field
The utility model is related to mountainous region region of high stress tunnel construction and coal mining field, more particularly to a kind of large-scale solid
Determine the shock absorption buffering mechanism of wing unmanned plane.
Background technology
Unmanned plane can be divided into large-scale unmanned plane and small drone by take-off weight.Small drone undercarriage is generally adopted
With truss structure, either elastic device is made of metal steel pipe or spring member, by the elastoplasticity of structure during aircraft landing
It deforming to absorb landing work(, buffering efficiency is low, and aircraft is also easy to produce rebound phenomena, and when the plastic deformation of structure reaches certain journey
Component is needed replacing when spending.Large-scale unmanned plane take-off weight bigger (generally in more than 500kg), for small drone is avoided to land
When the shortcomings that, generally use oil-gas type buffer.Oil-gas type buffer can be divided into stand oil cellular type and become oilhole formula, stand oil cellular type pressure
Load is uneven in compression process, neglects high bottom suddenly, damping, buffering process is unstable, greatly reduces the effect of damping；And become oilhole formula
It is more efficient although damping, buffering process is made to become steady, it is complicated, it is of high cost.
Utility model content
The purpose of the utility model is to overcome the deficiencies in the prior art, provide a kind of safe and reliable, stable buffering, damping
It is efficient, it is at low cost, suitable for the shock absorption buffering mechanism of large-scale fixed-wing unmanned plane.
What the purpose of this utility model was realized in：
A kind of shock absorption buffering mechanism of large size fixed-wing unmanned plane, including tubular oil hydraulic cylinder, before the oil hydraulic cylinder
Hollow piston, the preceding end closure of the piston, open rearward end, institute are inserted into end closure, open rearward end, the rear end of the oil hydraulic cylinder
The hollow piston tube of the rear end grafting of piston is stated, the front opening of the piston tube, rear end closure, the front end of the piston tube is inserted
Enter in hollow piston, the inner cavity of piston is made to be connected with the inner cavity of piston tube, the rear end of the piston tube is equipped with air valve, the work
Axially disposed installation through-hole, main damping hole and several secondary damping holes, the interior insertion bullet of the installation through-hole on the front bulkhead of plug
Spring last item, the front end of the spring last item set spacing head, and the rear end of the spring last item sets locking nut, spring last item position
Valve, valve spring are cased with successively from front to back in the part in piston, due to the effect of valve spring, are blocked under valve normality all
Secondary damping hole, the main damping hole maintains a normally open；It is hydraulic fluid chamber between the front bulkhead of the oil hydraulic cylinder and piston nose wall,
And full of hydraulic oil, it is oil gas chamber between the piston nose wall and piston tube aft bulkhead, and is full of hydraulic oil and gas.
Further, the rear end of the oil hydraulic cylinder connects tubular oil pressure seal casinghousing, and the piston tube passes through oil pressure
Seal casinghousing, the inner cavity front end of the oil pressure seal casinghousing set end cap seal circle, the intracavity posterior end of the oil pressure seal casinghousing
Oil-scraping ring is set, is formed between oil pressure seal casinghousing and piston tube and sealed；The end cap seal circle is located at oil pressure seal casinghousing
In the preceding seal groove that inner cavity front end is set, support ring is additionally provided in preceding seal groove, the support collar bearing is located at end cap seal
Rear is enclosed, the oil-scraping ring is located in the rear seal groove of intracavity posterior end setting of oil pressure seal casinghousing, is also set up in rear seal groove
There is oil immersed type bearing, the oil immersed type bearing is located in front of oil-scraping ring.
Further, after the piston and piston tube press fitting, by the fixed pin axially position of radial direction, in the piston tube
Spring pressuring ring is socketed, the spring pressuring ring is between piston, oil pressure seal casinghousing.
Further, the piston nose outer circumferential surface sets piston packing, is formed between oil hydraulic cylinder, piston and sealed, and
Oil pressure seal casinghousing and the periphery of oil hydraulic cylinder contact portion set O-ring seal, are formed between oil hydraulic cylinder, oil pressure seal casinghousing
Sealing.
Further, the main damping hole and piston coaxial, the quantity of the installation through-hole is two, two installation through-holes
Main damping hole both sides are symmetrically set in, the pair damping hole is divided into two groups corresponding with installation through-hole, and each group pair damping hole edge is corresponding
Installation through-hole is circumferentially uniformly distributed.
Further, it is solid for installing to be provided with the otic placode of through hole respectively for the oil hydraulic cylinder front end and piston tube rear end
Determine shock absorption buffering mechanism.
Further, the oil hydraulic cylinder cylinder head sets the cavity for loss of weight, which is located in front of hydraulic fluid chamber, empty
Chamber, hydraulic fluid chamber set isolation board, and the front opening of the cavity passes through oil column end cap seal.
Further, the end cap is connected through a screw thread with oil hydraulic cylinder, end cap periphery corresponding with the oil pressure inside wall of cylinder
Face is equipped with seal groove, installs O-ring seal in the seal groove, is formed between end cap and oil hydraulic cylinder and sealed.
By adopting the above-described technical solution, the utility model has the advantages that：
This shock absorption buffering mechanism uses the piston of press mounting structure, changes the area of damping hole in device work process, makes it
It raises and becomes larger with oil pressure in compression travel, and flow back and gradually reduce with fluid in extension stroke, to improve oil
Resistance and speed when liquid stream is through damping hole, increase the consumption of energy, and then the landing mission of unmanned plane is made to become more steady,
It is safer reliable.The present apparatus is at low cost, stable buffering, and damping efficiency is high, securely and reliably, be highly suitable for large-scale fixed-wing without
It is man-machine, there is higher actual application value.
Description of the drawings
Fig. 1 is the structure diagram of the utility model；
Fig. 2 is the A-A schematic cross-sectional views of Fig. 1；
Fig. 3 is the B-B schematic cross-sectional views of Fig. 1.
Reference numeral
In attached drawing, end cap 1, piston 2, oil hydraulic cylinder 3, oil immersed type bearing 4, oil pressure seal casinghousing 5, spring pressuring ring 6, piston tube
7, spring last item 8, valve 9, valve spring 10, fixed pin 11, O-ring seal 12, support ring 13, oil-scraping ring 14, air valve 15, locking
Nut 16, gasket 17, end cap seal circle 18, piston packing 19, fuse 20, axle sleeve 21.
Specific embodiment
The utility model is further described below in conjunction with attached drawing.
Shown in Fig. 1, oil column end cap 1 is connected through a screw thread with oil hydraulic cylinder 3, and 1 outer surface of oil column end cap is equipped with seal groove, in slot
Install O-ring seal 12.
Piston tube 7 should be first inserted into oil pressure seal casinghousing 5 before oil column piston 2 is installed, and reserves installation oil at one end
Length needed for column piston 2.5 two ends of oil pressure seal casinghousing are respectively equipped with seal groove, interior installing oil-scraping ring 14 and end cap seal
Circle 18, the two size will be bonded piston tube 7, ensure can be effectively in Seal Oil means of press seals housing 5 fluid and interfere piston
Pipe 7 freely stretches in oil pressure seal casinghousing 5.Support ring 13 is equipped in 18 place slot of end cap seal circle, to end cap sealing ring 18
It shields.14 left side of oil-scraping ring is equipped with oil immersed type bearing 4, support base when stretching as piston tube 7 with oil column piston 2.
Shown in Fig. 1,2,3, oil column piston 2 use press mounting structure, end face be equipped with symmetrical installation through-hole (A holes in Fig. 3), two
Root spring last item 8 penetrates oil column piston 2 by A holes, installs valve 9, valve spring 10, axis successively on the screw rod of spring last item 8
Set 21, gasket 17, are then fixed by locking nut 16, the pretightning force of spring should meet shock absorption buffering mechanism be compressed to it is pre-
Oil pressure can further compress valve spring 10 when positioning is put, and jack valve 9, so as to open the secondary resistance of the distribution of the plum blossom-shaped around A holes
Buddhist nun hole (C holes in Fig. 3).C holes are the key structures of shock absorption buffering mechanism, are evenly arranged around A holes are rounded, can realize damping
The change of hole area.Main damping hole (B holes in figure) is equipped among 2 end face of oil column piston, normally compress when shock absorption buffering mechanism or
During elongation, fluid is flowed by B holes between hydraulic fluid chamber (E chambers) and oil gas chamber (D chambers), forms damping action.
Shown in Fig. 1, the oil column piston 2 after press fitting is connected by fixed pin 11 with the through hole of 7 end of piston tube, and oil column is lived
Spring pressuring ring 6 is equipped between plug 2 and piston tube 7, when avoiding the shock absorption buffering mechanism from too extending, oil column piston 2 and 7 end of piston tube
Face direct metal collision, plays buffer protection function.
2 outer surface of oil column piston is equipped with seal groove, inside sets piston packing 19, piston packing 19 and 3 inner cavity of oil hydraulic cylinder
It fits closely, ensures that oil column piston 2 is free to slide in 3 intracavitary of oil hydraulic cylinder.
Before connection oil hydraulic cylinder 3 with oil pressure seal casinghousing 5, first oil hydraulic cylinder 3 is placed vertically, and liquid is full of in its intracavitary
Then the component of oil pressure seal casinghousing 5 and oil column piston 2 is inserted into 3 intracavitary of oil hydraulic cylinder by pressure oil, component will be protected in insertion process
It is vertical to hold, and during oil column piston 2 reaches 3 lowest position of oil hydraulic cylinder, hydraulic oil passes through 7 end of piston tube and air valve
The scavenging action of the threaded hole of 15 connections ensures that all air are excluded in component in installation process full of piston tube 7
Outside.Oil pressure seal casinghousing 5 is connected after reaching precalculated position by screw thread with oil hydraulic cylinder 3 simultaneously, and junction is equipped with O-ring seal
12, play the role of sealing fluid pressure oil.Air valve 15 is finally installed on 7 ends screw hole of piston tube, and will using fuse 20
It is locked.Such fuse is steel wire, is matched with locking nut, can wear the hole on locking nut, is then bundled in solid
Determine in structure, make the locking nut on air valve 15 not rotatable, referring to Fig. 1.Then air charging system is connected, then opens air valve 15,
The drying nitrogen being filled with into piston tube 7, until cavity pressure reaches predetermined value.E intracavitary is ultimately formed full of hydraulic oil, and D
Then a part is hydraulic oil to intracavitary, and a part is nitrogen.
The oil hydraulic cylinder cylinder head sets the cavity for loss of weight, which is located in front of hydraulic fluid chamber, cavity, hydraulic fluid chamber
Isolation board is set, and the front opening of the cavity passes through oil column end cap seal.
It,, will by the through hole on oil column end cap 1 and 7 otic placode of piston tube using bolt and nut etc. during using the utility model
The shock absorption buffering mechanism is mounted on large-scale fixed-wing unmanned plane undercarriage, and vertically or diagonally-installed, to ensure that gas is steady
Surely there are D intracavitary.There is the otic placode specially set to be connected with the buffer of damper device on unmanned plane undercarriage, installation is very square
Just.When unmanned plane just lands, fierce due to hitting, shock absorption buffering mechanism compresses rapidly, and the oil pressure rapid increase of intracavitary works as oil
When pressure reaches the predetermined pressure of valve 9, valve 9 is jacked, and C holes are opened, and hydraulic oil not only can also pass through C by B holes
Hole flows to D chambers from E chambers, adds the area of damping hole, it is made not generate oil liquid resistance or generates smaller oil liquid resistance,
It does work mainly by gas compression and consumes landing work(.And in extension stroke, fluid is pushed back by gas, and valve 9 is progressively closed off, with
C holes it is covered, damping hole area greatly reduce, fluid is only capable of flowing to E chambers from B holes by D chambers, increases fluid in extension stroke
Speed and resistance when flowing through oilhole, so as to add the consumption of energy.This structure, which efficiently solves, determines cellular type fluid and delays
Fluid flows through the violent of damping hole speed and rises violent drop phenomenon when rushing device work, realize compression process medium velocity homogenization and stretch
The General Promotion of exhibition process medium velocity makes aircraft more steady during landing, safety and reliability.And by setting C holes
Size and arrangement, different damping, buffering working characteristics can be obtained, suitable for various severe UAV Landing works
Condition.
Finally illustrate, preferred embodiment above is merely intended for describing the technical solutions of the present application, but not for limiting the present application, to the greatest extent
Pipe has been described in detail the utility model by above preferred embodiment, but those skilled in the art should manage
Solution, can in the form and details make it various changes, without departing from the utility model claims book institute
The scope of restriction.
Claims (8)
1. a kind of shock absorption buffering mechanism of large size fixed-wing unmanned plane, including tubular oil hydraulic cylinder, the front end of the oil hydraulic cylinder
Sealing, open rearward end, which is characterized in that hollow piston is inserted into the rear end of the oil hydraulic cylinder, the preceding end closure of the piston, after
End opening, the hollow piston tube of the rear end grafting of the piston, the front opening of the piston tube, rear end closure, the piston
The front end of pipe is inserted into hollow piston, the inner cavity of piston is made to be connected with the inner cavity of piston tube, the rear end of the piston tube is equipped with
Air valve, axially disposed installation through-hole, main damping hole and several secondary damping holes, the installation are logical on the front bulkhead of the piston
Spring last item is inserted into hole, the front end of the spring last item sets spacing head, and the rear end of the spring last item sets locking nut,
The part that spring last item is located in piston is cased with valve, valve spring successively from front to back, due to the effect of valve spring, valve normality
Under block all secondary damping holes, the main damping hole maintains a normally open；Between the front bulkhead of the oil hydraulic cylinder and piston nose wall
It is oil gas chamber between the piston nose wall and piston tube aft bulkhead for hydraulic fluid chamber, and full of hydraulic oil, and full of hydraulic oil
And gas.
A kind of 2. shock absorption buffering mechanism of large-scale fixed-wing unmanned plane according to claim 1, which is characterized in that the oil
The rear end of cylinder pressure connects tubular oil pressure seal casinghousing, and the piston tube passes through oil pressure seal casinghousing, the oil pressure capsul
The inner cavity front end of body sets end cap seal circle, and the intracavity posterior end of the oil pressure seal casinghousing sets oil-scraping ring, forms oil pressure sealing
It is sealed between housing and piston tube；The end cap seal circle is located at the preceding seal groove that the inner cavity front end of oil pressure seal casinghousing is set
It is interior, support ring is additionally provided in preceding seal groove, the support collar bearing is located at end cap seal circle rear, and the oil-scraping ring is located at oil
In the rear seal groove that the intracavity posterior end of means of press seals housing is set, oil immersed type bearing, the oil immersed type are additionally provided in rear seal groove
Bearing is located in front of oil-scraping ring.
A kind of 3. shock absorption buffering mechanism of large-scale fixed-wing unmanned plane according to claim 2, which is characterized in that the work
After plug and piston tube press fitting, by the fixed pin axially position of radial direction, spring pressuring ring, the spring pressure are socketed in the piston tube
Circle is between piston, oil pressure seal casinghousing.
A kind of 4. shock absorption buffering mechanism of large-scale fixed-wing unmanned plane according to claim 2, which is characterized in that the work
It fills in front end outer circumferential surface and piston packing is set, formed between oil hydraulic cylinder, piston and sealed, and oil pressure seal casinghousing is contacted with oil hydraulic cylinder
Partial periphery sets O-ring seal, is formed between oil hydraulic cylinder, oil pressure seal casinghousing and sealed.
A kind of 5. shock absorption buffering mechanism of large-scale fixed-wing unmanned plane according to claim 1, which is characterized in that the master
Damping hole and piston coaxial, the quantity of the installation through-hole is two, and two installation through-holes are symmetrically set in main damping hole both sides, institute
It states secondary damping hole and is divided into two groups corresponding with installation through-hole, each group pair damping hole is circumferentially uniformly distributed along corresponding installation through-hole.
A kind of 6. shock absorption buffering mechanism of large-scale fixed-wing unmanned plane according to claim 1, which is characterized in that the oil
Cylinder pressure front end and piston tube rear end are provided with the otic placode of through hole for installing fixed shock absorption buffering mechanism respectively.
A kind of 7. shock absorption buffering mechanism of large-scale fixed-wing unmanned plane according to claim 1, which is characterized in that the oil
Cylinder pressure cylinder head sets the cavity for loss of weight, which is located in front of hydraulic fluid chamber, and cavity, hydraulic fluid chamber set isolation board, should
The front opening of cavity passes through oil column end cap seal.
A kind of 8. shock absorption buffering mechanism of large-scale fixed-wing unmanned plane according to claim 7, which is characterized in that the end
Lid is connected through a screw thread with oil hydraulic cylinder, and end cap outer circumferential surface corresponding with the oil pressure inside wall of cylinder is equipped with seal groove, the sealing
Installing O-ring seal in slot, forms between end cap and oil hydraulic cylinder and seals.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721367802.1U CN207403927U (en) | 2017-10-23 | 2017-10-23 | A kind of shock absorption buffering mechanism of large size fixed-wing unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721367802.1U CN207403927U (en) | 2017-10-23 | 2017-10-23 | A kind of shock absorption buffering mechanism of large size fixed-wing unmanned plane |
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| CN207403927U true CN207403927U (en) | 2018-05-25 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107600396A (en) * | 2017-10-23 | 2018-01-19 | 重庆通用航空产业集团有限公司 | A kind of shock absorption buffering mechanism of large-scale fixed-wing unmanned plane |
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2017
- 2017-10-23 CN CN201721367802.1U patent/CN207403927U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107600396A (en) * | 2017-10-23 | 2018-01-19 | 重庆通用航空产业集团有限公司 | A kind of shock absorption buffering mechanism of large-scale fixed-wing unmanned plane |
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| GR01 | Patent grant | ||
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| CB03 | Change of inventor or designer information |
Inventor after: Wu Yixiao Inventor after: Xu Liang Inventor after: Chen Guo Inventor after: Zhou Baocheng Inventor after: Hu Hanjie Inventor after: Zeng Xianjun Inventor after: Zhang Jin Inventor after: Huang Shengying Inventor after: Dong Bo Inventor before: Wu Yixiao Inventor before: Xu Liang Inventor before: Chen Guo Inventor before: Zhou Baocheng Inventor before: Hu Hanjie Inventor before: Zeng Xianjun Inventor before: Zhang Jin Inventor before: Huang Shengying Inventor before: Dong Bo |