CN217381098U - Stroke limiting protection device for aviation hydraulic component - Google Patents

Stroke limiting protection device for aviation hydraulic component Download PDF

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Publication number
CN217381098U
CN217381098U CN202220755014.4U CN202220755014U CN217381098U CN 217381098 U CN217381098 U CN 217381098U CN 202220755014 U CN202220755014 U CN 202220755014U CN 217381098 U CN217381098 U CN 217381098U
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hydraulic
seat
terminal surface
surface under
column
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CN202220755014.4U
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Chinese (zh)
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徐斯恒
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Suzhou Hengkai Machinery Co ltd
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Suzhou Hengkai Machinery Co ltd
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    • 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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Abstract

The utility model provides a spacing protection device of stroke for aviation hydraulic part, include: footstock, screw thread post, spacing seat, backing ring, stop collar, clamp, deformation piece, slowly-releasing board, hydraulic pressure post and base, the screw thread post is installed to the terminal surface under the footstock, spacing seat is installed in the screw thread post outside, the backing ring is installed to terminal surface under the spacing seat, the hydraulic pressure post is installed to the terminal surface under the screw thread post, the base is installed to the terminal surface under the hydraulic pressure post, the stop collar is a cylindricality structure, the inside hollow structure that is of stop collar, the interior side of stop collar is seted up and is equipped with the inside screw groove, compare with prior art, the utility model discloses following beneficial effect has: through using spacing seat, can carry out the position to aviation hydraulic pressure part and prescribe a limit to, through using the hydraulic pressure post, can carry out abundant slowly-releasing to the weight of footstock upper end, improve the utility model discloses the effect of position injecture and slowly-releasing.

Description

Stroke limiting protection device for aviation hydraulic component
Technical Field
The utility model belongs to the technical field of aviation hydraulic pressure part, a spacing protection device is related to, specifically speaking relates to a spacing protection device of stroke for aviation hydraulic pressure part.
Background
Each part in the aviation hydraulic accessory is characterized by small volume and high precision, and needs to bear complex service conditions in work, so that the high-strength and good toughness of the part is ensured in the aspects of material selection and heat treatment requirement determination, but the limit size of the aviation hydraulic part in the prior art cannot be quickly adjusted, and meanwhile, the inside of a hydraulic column cannot be effectively protected, so that the problems are solved by a stroke limit protection device for the aviation hydraulic part urgently.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a spacing protection device of stroke for aviation hydraulic part, the problem of proposing among the above-mentioned background art is solved to not enough to prior art exists.
The utility model discloses a following technical scheme realizes: a stroke limit protection device for aviation hydraulic parts comprises: the hydraulic support comprises a top seat, a threaded column, a limiting seat, a backing ring, a hydraulic column and a base, wherein the threaded column is installed on the lower end face of the top seat, the limiting seat is installed on the outer side of the threaded column, the backing ring is installed on the lower end face of the limiting seat, the hydraulic column is installed on the lower end face of the threaded column, and the base is installed on the lower end face of the hydraulic column.
As a preferred embodiment, the limiting seat comprises a limiting sleeve, a clamp body, a deformation block, a slow release plate and a cushion block in actual use, the clamp body is installed on the lower end face of the limiting sleeve in actual use, the deformation block is installed on the lower end face of the clamp body in actual use, the slow release plate is installed on the lower end face of the deformation block in actual use, and the cushion block is installed on the lower end face of the slow release plate in actual use.
As a preferred embodiment, the stop collar is a cylindrical structure in actual use, the inside of the stop collar is a hollow structure in actual use, the inner side of the stop collar is provided with an inner groove in actual use, the stop collar is meshed with the threaded column in actual use, the deformation block is made of rubber in actual use, the cross section of the deformation block is a corrugated structure in actual use, and the cushion block is a rubber round block in actual use.
As a preferred embodiment, the hydraulic column comprises a connecting column, a sealing seat, a piston, a guide pipe, a bottom plate, a spring, an upper hydraulic seat, a middle hydraulic column, a lower hydraulic seat and a hydraulic oil bin in actual use, the hydraulic column is a movable mechanism in actual use, and the interior of the hydraulic column is a hollow structure in actual use.
As a preferred embodiment, a seal seat is installed on the lower end face of the connecting column in actual use, a piston is installed on the lower end face of the seal seat in actual use, a guide pipe is installed on the lower end face of the piston in actual use, a bottom plate is installed on the lower end face of the guide pipe in actual use, a spring is installed on the lower end face of the bottom plate in actual use, an upper hydraulic seat is installed on the upper end of the inner side of the spring in actual use, a middle pressure column is installed on the lower end face of the upper hydraulic seat in actual use, a lower hydraulic seat is installed on the lower end face of the middle pressure column in actual use, and a hydraulic oil sump is opened on the lower end face of the lower hydraulic seat in actual use.
As a preferred embodiment, the connecting column is fixedly connected with the threaded column in actual use, the diameter of the cross section of the inner side of the backing ring is smaller than the diameter of the cross section of the connecting column and larger than the diameter of the cross section of the threaded column in actual use, two sets of ring bodies are installed in the piston in actual use, the ring bodies are hermetically connected with the inner wall of the hydraulic column in actual use, the specifications of the upper hydraulic seat and the lower hydraulic seat in actual use are the same, the interior of the middle pressure column is of a hollow structure in actual use, and the interior of the hydraulic oil bin, the interior of the lower hydraulic seat, the interior of the middle pressure column and the interior of the upper hydraulic seat are communicated with each other in actual use.
After the technical scheme is adopted, the beneficial effects of the utility model are that: through using spacing seat, can carry out the position to aviation hydraulic pressure part and prescribe a limit to, through using the hydraulic pressure post, can carry out abundant slowly-releasing to the weight of footstock upper end, improve the utility model discloses the effect of position injecture and slowly-releasing.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive exercise.
Fig. 1 is a schematic structural view of the stroke limiting protection device for an aviation hydraulic component of the present invention;
fig. 2 is a front sectional view of a limit seat and a hydraulic column in the stroke limit protection device for an aviation hydraulic component of the present invention;
FIG. 3 is an enlarged view of the position A of the stroke limiting protection device for an aviation hydraulic component of the present invention;
in the figure: 1-top seat, 2-threaded column, 3-limiting seat, 4-backing ring, 5-hydraulic column, 6-base, 31-limiting sleeve, 32-clamp, 33-deformation block, 34-slow release plate, 35-cushion block, 51-connecting column, 52-sealing seat, 53-piston, 54-guide tube, 55-bottom plate, 56-spring, 57-upper hydraulic seat, 58-middle pressure column, 59-lower hydraulic seat and 501-hydraulic oil bin.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Referring to fig. 1-3, a stroke limiting protection device for an aviation hydraulic component includes: top seat 1, screw thread post 2, spacing seat 3, backing ring 4, hydraulic pressure post 5 and base 6, screw thread post 2 is installed to the terminal surface under 1 of top seat, and spacing seat 3 is installed in the 2 outsides of screw thread post, and backing ring 4 is installed to the terminal surface under 3 of spacing seat, and hydraulic pressure post 5 is installed to the terminal surface under 2 screw thread posts, and base 6 is installed to the terminal surface under 5 hydraulic pressure posts.
Spacing seat 3 includes stop collar 31, clamp 32, shape change piece 33, slowly-releasing board 34 and cushion 35 in the in-service use, and clamp 32 is installed in the in-service use to the terminal surface under the stop collar 31, and shape change piece 33 is installed in the in-service use to the terminal surface under the clamp 32, and slowly-releasing board 34 is installed in the in-service use to the terminal surface under shape change piece 33, and cushion 35 is installed in the in-service use to the terminal surface under slowly-releasing board 34.
Stop collar 31 is a cylindricality structure in the in-service use, the inside hollow structure that is in the in-service use of stop collar 31, the inside inner screw groove has been seted up in the in-service use of stop collar 31, stop collar 31 and screw post 2 intermeshing in the in-service use, deformation piece 33 manufacturing material is a rubber in the in-service use, deformation piece 33 cross section is a ripple structure in the in-service use, cushion 35 is a rubber circle piece in the in-service use, can carry out the position to aviation hydraulic pressure part and prescribe a limit to.
The hydraulic column 5 comprises a connecting column 51, a sealing seat 52, a piston 53, a guide pipe 54, a bottom plate 55, a spring 56, an upper hydraulic seat 57, a middle hydraulic column 58, a lower hydraulic seat 59 and a hydraulic oil bin 501 in practical use, the hydraulic column 5 is a movable mechanism in practical use, and the interior of the hydraulic column 5 is a hollow structure in practical use.
The lower end face of the connecting column 51 is provided with a sealing seat 52 in actual use, the lower end face of the sealing seat 52 is provided with a piston 53 in actual use, the lower end face of the piston 53 is provided with a guide pipe 54 in actual use, the lower end face of the guide pipe 54 is provided with a bottom plate 55 in actual use, the lower end face of the bottom plate 55 is provided with a spring 56 in actual use, the upper end of the inner side of the spring 56 is provided with an upper hydraulic seat 57 in actual use, the lower end face of the upper hydraulic seat 57 is provided with a middle pressure column 58 in actual use, the lower end face of the middle pressure column 58 is provided with a lower hydraulic seat 59 in actual use, and the lower end face of the lower hydraulic seat 59 is provided with a hydraulic oil sump 501 in actual use.
The connecting column 51 is fixedly connected with the threaded column 2 in actual use, the diameter of the cross section of the inner side of the backing ring 4 is smaller than that of the connecting column 51 and larger than that of the cross section of the threaded column 2 in actual use, two groups of ring bodies are installed inside the piston 53 in actual use, the ring bodies are hermetically connected with the inner wall of the hydraulic column 5 in actual use, the upper hydraulic seat 57 is the same as the internal specification of the lower hydraulic seat 59 in actual use, the upper hydraulic seat 57 is the same as the specification of the lower hydraulic seat 59 in actual use, the internal part of the middle pressure column 58 is of a hollow structure in actual use, the internal part of the hydraulic oil bin 501, the internal part of the lower hydraulic seat 59, the internal part of the middle pressure column 58 and the internal part of the upper hydraulic seat 57 are communicated with each other in actual use, and the weight of the upper end of the top seat 1 can be sufficiently slowly released.
As an embodiment of the present invention: in actual use, when a worker uses a hydraulic component, the footstock 1 is fixedly connected with the bottom of the component needing slow release, and the base 6 is horizontally fixed with the ground, so that installation can be completed, the component needing slow release extrudes the footstock 1, the footstock 1 is stressed to move downwards and extrude the threaded column 2, the threaded column 2 drives the limiting seat 3 to move downwards, the lower end of the threaded column 2 extrudes the upper end of the connecting column 51, the connecting column 51 moves downwards and extrudes the piston 53 to descend, two groups of ring bodies are installed in the piston 53 in actual use, the ring bodies are hermetically connected with the inner wall of the hydraulic column 5 in actual use, the piston 53 descends and simultaneously increases the air pressure inside the hydraulic column 5, the piston extrudes the bottom plate 55 and the spring 56 and compresses the spring 56, and the hydraulic oil bin 501, the lower hydraulic seat 59, the middle pressure column 58 and the upper hydraulic seat 57 are communicated with each other in actual use, can carry out abundant slowly-releasing to the weight of footstock 1 upper end, go up hydraulic pressure seat 57 and hydraulic pressure seat 59 can carry out further second grade slowly-releasing through the extrusion of bottom plate 55 and the compression of spring 56 down, thereby guarantee the normal operating of hydraulic pressure part, when the staff need limit hydraulic pressure post 5 stroke length, rotatory stop collar 31, make stop collar 31 rotate around the 2 outsides of screw thread post, make the distance between cushion 35 and backing ring 4 reduce, can restrict and reduce the extrusion stroke of screw thread post 2, when the distance between cushion 35 and the backing ring 4 increases, can restrict and increase the extrusion stroke of screw thread post 2, and is convenient and fast.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (6)

1. A stroke limit protection device for aviation hydraulic parts comprises: footstock (1), screw thread post (2), spacing seat (3), backing ring (4), hydraulic pressure post (5) and base (6), its characterized in that: screw post (2) are installed to terminal surface under footstock (1), spacing seat (3) are installed in screw post (2) outside, backing ring (4) are installed to terminal surface under spacing seat (3), hydraulic pressure post (5) are installed to terminal surface under screw post (2), base (6) are installed to terminal surface under hydraulic pressure post (5).
2. The stroke limit protection device for the aviation hydraulic component according to claim 1, wherein: spacing seat (3) include stop collar (31), clamp (32), shape change piece (33), slowly-releasing board (34) and cushion (35), clamp (32) are installed to the terminal surface under stop collar (31), shape change piece (33) are installed to the terminal surface under clamp (32), slowly-releasing board (34) are installed to the terminal surface under shape change piece (33), cushion (35) are installed to the terminal surface under slowly-releasing board (34).
3. The stroke limit protection device for the aviation hydraulic component according to claim 2, wherein: the limiting sleeve (31) is of a cylindrical structure, a hollow structure is arranged inside the limiting sleeve (31), an inner groove is formed in the inner side of the limiting sleeve (31), the limiting sleeve (31) is meshed with the threaded column (2), the deformation block (33) is made of rubber, the cross section of the deformation block (33) is of a corrugated structure, and the cushion block (35) is a rubber round block.
4. The stroke limit protection device for the aviation hydraulic component according to claim 1, wherein: the hydraulic column (5) comprises a connecting column (51), a sealing seat (52), a piston (53), a guide pipe (54), a bottom plate (55), a spring (56), an upper hydraulic seat (57), a middle pressure column (58), a lower hydraulic seat (59) and a hydraulic oil bin (501), the hydraulic column (5) is a movable mechanism, and the interior of the hydraulic column (5) is of a hollow structure.
5. The stroke limit protection device for the aviation hydraulic component according to claim 4, wherein: seal receptacle (52) are installed to the terminal surface under spliced pole (51), piston (53) are installed to the terminal surface under seal receptacle (52), pipe (54) are installed to the terminal surface under piston (53), bottom plate (55) are installed to the terminal surface under pipe (54), spring (56) are installed to the terminal surface under bottom plate (55), hydraulic pressure seat (57) are installed to spring (56) inboard upper end, go up hydraulic pressure seat (57) and install well pressure post (58) down the terminal surface, hydraulic pressure seat (59) are installed down to well pressure post (58) lower terminal surface, hydraulic pressure oil sump (501) have been seted up to terminal surface under well pressure seat (59).
6. The stroke limit protection device for the aviation hydraulic component according to claim 4, wherein: the utility model discloses a hydraulic oil tank, including spliced pole (51), backing ring (4), piston (53), ring (58), interior side cross section diameter of backing ring (4) is less than spliced pole (51) cross section diameter and is greater than threaded column (2) cross section diameter, piston (53) internally mounted has two sets of rings, ring and hydraulic column (5) inner wall sealing connection, it is the same with lower hydraulic seat (59) inside specification to go up hydraulic seat (57), it is the same with lower hydraulic seat (59) specification to go up hydraulic seat (57), the inside hollow structure that is of well head (58), inside, the inside all intercommunication each other of lower hydraulic seat (59), well head (58) inside and the interior of last hydraulic seat (57) of hydraulic oil bin (501).
CN202220755014.4U 2022-03-31 2022-03-31 Stroke limiting protection device for aviation hydraulic component Active CN217381098U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202220755014.4U CN217381098U (en) 2022-03-31 2022-03-31 Stroke limiting protection device for aviation hydraulic component

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202220755014.4U CN217381098U (en) 2022-03-31 2022-03-31 Stroke limiting protection device for aviation hydraulic component

Publications (1)

Publication Number Publication Date
CN217381098U true CN217381098U (en) 2022-09-06

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ID=83104877

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202220755014.4U Active CN217381098U (en) 2022-03-31 2022-03-31 Stroke limiting protection device for aviation hydraulic component

Country Status (1)

Country Link
CN (1) CN217381098U (en)

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