CN215701036U

CN215701036U - Auxiliary installation device of aircraft guide pipe

Info

Publication number: CN215701036U
Application number: CN202121465650.5U
Authority: CN
Inventors: 胡庆宝; 杨毅; 董艳; 朱公旭
Original assignee: Shanghai Aircraft Manufacturing Co Ltd
Current assignee: Shanghai Aircraft Manufacturing Co Ltd
Priority date: 2021-06-30
Filing date: 2021-06-30
Publication date: 2022-02-01
Anticipated expiration: 2031-06-30

Abstract

The utility model relates to the technical field of installation of airplane guide pipes, and particularly discloses an auxiliary installation device of an airplane guide pipe. The auxiliary installation device of the airplane guide pipe comprises a base and a connecting mechanism, wherein the connecting mechanism comprises a first connecting piece and a second connecting piece, the first connecting piece is connected with a sliding sleeve pipe, and the second connecting piece is connected with the guide pipe. Therefore, the sliding sleeve and the guide pipe can be accurately and efficiently assembled together by adjusting the relative position between the first connecting piece and the second connecting piece. The first connecting piece and the second connecting piece are arranged on the base in a sliding mode so as to change the distance between the first connecting piece and the second connecting piece on the horizontal plane. The height of the first connecting piece and the height of the second connecting piece are adjustable, so that the distance between the first connecting piece and the second connecting piece on a vertical plane is changed, the central axis of the sliding sleeve pipe coincides with the central axis of the guide pipe, and the assembling efficiency and the assembling precision between the sliding sleeve pipe and the guide pipe are improved.

Description

Auxiliary installation device of aircraft guide pipe

Technical Field

The utility model relates to the technical field of installation of aircraft ducts, in particular to an auxiliary installation device of an aircraft duct.

Background

In the civil aircraft bleed air system, the sliding sleeve pipe can compensate relative motion and displacement of the guide pipe as a flexible compensation device, so that internal stress of the guide pipe is reduced, permanent deformation cannot occur under the action of load limiting, and axial tension and compression can be realized under the action of pressure. At present, the assembly precision of a sliding sleeve between high-pressure guide pipes is difficult to ensure by single manual operation, the assembly efficiency is low, and the failure frequency is frequent. Accordingly, there is a need for an auxiliary installation device for aircraft ducts that solves the above problems.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide an auxiliary installation device of an aircraft guide pipe, which solves the problems of poor assembly precision and low efficiency between the guide pipe and a sliding sleeve pipe.

In order to achieve the purpose, the utility model adopts the following technical scheme:

an aircraft conduit accessory mounting device for connecting a slip sleeve to a conduit comprising:

a base;

the connecting mechanism comprises a first connecting piece and a second connecting piece, the first connecting piece is connected with the sliding sleeve, and the second connecting piece is connected with the guide pipe; the first connecting piece and the second connecting piece are arranged on the base in a sliding manner; the height of the first connecting piece and the second connecting piece is adjustable.

As an alternative to the above-mentioned auxiliary installation device for an aircraft conduit, the first connecting piece and the second connecting piece each include a limiting piece, the limiting piece is an annular sleeve, and the sliding sleeve or the conduit is sleeved in the annular sleeve to limit the sliding sleeve or the conduit from moving in the axial direction and the radial direction.

As an alternative to the above-mentioned auxiliary installation device for an aircraft conduit, an opening is provided on the limiting member, and the opening divides the limiting member into a first end and a second end; the locating part still includes the retaining member, the retaining member is used for locking the first end with the second end of locating part.

As an alternative of the above auxiliary installation device for an aircraft conduit, a sliding mechanism is arranged between the connection mechanism and the base, and the sliding mechanism is arranged in one-to-one correspondence with the first connection piece and the second connection piece, and is used for realizing the sliding of the first connection piece and the second connection piece on the base.

As an alternative to the above-mentioned auxiliary installation device for an aircraft conduit, the sliding mechanism includes a slide rail and a slide block, and the slide block is slidably disposed on the slide rail along an extending direction of the slide rail; the sliding rail is arranged on the base along the axial direction of the sliding sleeve, the first connecting piece and the second connecting piece both comprise support bodies, and the sliding blocks are connected with the bottom ends of the support bodies.

As an alternative of the above auxiliary installation device for an aircraft conduit, the sliding mechanism further includes a first fastening member, the sliding block is provided with a first through hole, and the first fastening member can be inserted into the first through hole.

As an alternative to the above-described auxiliary mounting device for an aircraft conduit, the position of the bracket body on the slide is adjustable.

As an alternative of the above auxiliary installation device for an aircraft conduit, the bracket body further includes a second fastening piece, a second through hole is formed in the bottom end of the bracket body, and the second fastening piece can be inserted into the second through hole.

As an alternative to the above-mentioned auxiliary installation device for an aircraft conduit, a plurality of bracket bodies are provided on the second connector, and the plurality of bracket bodies are distributed at intervals along the axial direction of the conduit.

As an alternative to the above-mentioned auxiliary installation device for an aircraft conduit, the device further includes a driving mechanism, the first connecting piece is disposed at an output end of the driving mechanism, and the driving mechanism is configured to drive the first connecting piece to slide on the slide rail; and/or

The second connecting piece is arranged at the output end of the driving mechanism, and the driving mechanism is used for driving the second connecting piece to slide on the sliding rail.

The utility model has the beneficial effects that:

according to the auxiliary installation device of the aircraft guide pipe, the first connecting piece is connected with the sliding sleeve pipe, the second connecting piece is connected with the guide pipe, the heights of the first connecting piece and the second connecting piece are adjustable, the sliding sleeve pipe can be aligned with the central axis of the guide pipe, and therefore the assembly precision between the sliding sleeve pipe and the guide pipe is improved. The first connecting piece and the second connecting piece slide on the base, so that the sliding sleeve pipe and the guide pipe are close to each other, and the assembly efficiency between the sliding sleeve pipe and the guide pipe is improved.

Drawings

Fig. 1 is a schematic structural diagram of an auxiliary installation device for an aircraft duct provided by an embodiment of the utility model.

In the figure:

1. sliding the sleeve;

2. a conduit;

3. a base;

4. a connecting mechanism; 41. a first connecting member; 42. a second connecting member; 411. a limiting member; 4111. a locking member; 412. a stent body; 4121. a second fastener;

5. a sliding mechanism; 51. a slide rail; 52. a slider; 521. a first fastener;

6. a drive mechanism; 61. a rotating member; 62. a screw rod; 63. and a support member.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the utility model and are not limiting of the utility model. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.

In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, removably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

In the description of the present embodiment, the terms "upper", "lower", "right", etc. are used in an orientation or positional relationship based on that shown in the drawings only for convenience of description and simplicity of operation, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used only for descriptive purposes and are not intended to have a special meaning.

The embodiment provides an auxiliary installation device of an airplane guide pipe, which is used for connecting a sliding sleeve pipe 1 and a guide pipe 2. Generally, the two guide pipes 2 are respectively connected with two ends of the sliding sleeve pipe 1, and when the guide pipes 2 are in a high-temperature and high-pressure working environment, the two guide pipes 2 are deformed to extrude or pull the sliding sleeve pipe 1, so that the sliding sleeve pipe 1 can be axially compressed or stretched, and relative movement of the two guide pipes 2 caused by deformation is compensated.

The auxiliary installation device of the airplane guide pipe comprises a base 3 and a connecting mechanism 4, wherein the connecting mechanism 4 comprises a first connecting piece 41 and a second connecting piece 42, the first connecting piece 41 is connected with the sliding sleeve pipe 1, and the second connecting piece 42 is connected with the guide pipe 2. Thus, by adjusting the relative position between the first connecting member 41 and the second connecting member 42, the sliding sleeve 1 and the guide tube 2 can be accurately and efficiently assembled. The first connecting member 41 and the second connecting member 42 are slidably disposed on the base 3 to change the distance between the first connecting member 41 and the second connecting member 42 on the horizontal plane. The heights of the first connecting piece 41 and the second connecting piece 42 are adjustable so as to change the distance between the first connecting piece 41 and the second connecting piece 42 on the vertical plane, so that the central axes of the sliding sleeve 1 and the guide pipe 2 are overlapped, and the assembly efficiency and the assembly precision between the sliding sleeve 1 and the guide pipe 2 are improved. When adjusting the relative position between the first connector 41 and the second connector 42, one of the first connector 41 and the second connector 42 can be selected as a reference, and the position or height of the other on the base 3 can be changed, thereby facilitating the assembly between the sliding sleeve 1 and the guide tube 2.

Optionally, the first connecting element 41 and the second connecting element 42 each include a limiting element 411, the limiting element 411 is an annular sleeve, and the sliding sleeve 1 or the guide tube 2 is sleeved in the annular sleeve to limit the axial and radial movement of the sliding sleeve 1 or the guide tube 2, so as to prevent the guide tube 2 or the sliding sleeve 1 from shifting during the assembly process, and reduce the assembly accuracy. In order to ensure that the limiting members 411 tightly limit the sliding sleeve 1 or the guide tube 2 in the axial direction and the radial direction, the sliding sleeve 1 and the guide tube 2 need to be tightly attached to the corresponding limiting members 411. I.e. the size of the stop 411, needs to be adapted according to the size of the slip sleeve 1 and the catheter 2.

Further optionally, an opening is disposed on the limiting member 411, and the opening divides the limiting member 411 into a first end and a second end. The above arrangement makes the limiting member 411 become an arc-shaped member with an adjustable shape, thereby improving the adaptability of the limiting member 411. The limiting member 411 further comprises a locking member 4111, wherein the locking member 4111 is used for locking the first end and the second end of the limiting member 411, so that the shape of the limiting member 411 is fixed and is adapted to the sliding sleeve pipe 1 and the conduit 2, thereby ensuring the limiting function of the limiting member 411. In this embodiment, the specific structure of the locking member 4111 is not limited too much, as long as the first end and the second end of the limiting member 411 can be locked.

Optionally, a sliding mechanism 5 is disposed between the connecting mechanism 4 and the base 3, and the sliding mechanism 5 is disposed in one-to-one correspondence with the first connecting piece 41 and the second connecting piece 42, and is used for realizing sliding of the first connecting piece 41 and the second connecting piece 42 on the base 3. Specifically, the sliding mechanism 5 includes a slide rail 51 and a slider 52, and the slider 52 is slidably disposed on the slide rail 51 along the extending direction of the slide rail 51 to realize the sliding of the slider 52 on the slide rail 51. The slide rail 51 is provided on the base 3 in the axial direction of the slide sleeve 1 so that the sliding direction of the slide mechanism 5 is the axial direction of the guide tube 2. The first connecting member 41 and the second connecting member 42 each include a bracket body 412, and the sliding block 52 is connected to the bottom end of the bracket body 412, so that the first connecting member 41 and the second connecting member 42 can be slidably disposed on the base 3 through the sliding mechanism 5.

Further optionally, the bracket body 412 is a telescopic member to realize height adjustment of the first connecting member 41 and the second connecting member 42. Specifically, the bracket body 412 includes a first supporting rod and a second supporting rod, the first supporting rod is connected to the limiting member 411, the second supporting rod is connected to the slider 52, and the second supporting rod is slidably disposed in the first supporting rod, so as to achieve the telescopic effect of the bracket body 412. In other embodiments, the bracket body 412 may have other telescopic structures.

In civil aircraft bleed air systems, the conduit 2 is used primarily to connect the air supply to the downstream air consuming systems, i.e. the length and installation path of the conduit 2 is determined by the relative position of the connecting air supply to the downstream air consuming systems. Therefore, optionally, the stopper 411 is rotatably connected to the holder body 412 so as to change the installation path of the catheter 2. Further optionally, the limiting member 411 is detachably connected to the bracket body 412, so that the limiting member 411 can be replaced and detached, on one hand, the service life of the auxiliary installation device of the aircraft duct 2 is prolonged, and on the other hand, the number of the limiting members 411 can be adaptively changed according to the field assembly requirement. Further optionally, a plurality of stent bodies 412 are disposed on the second connecting member 42, and the plurality of stent bodies 412 are distributed at intervals along the axial direction of the catheter 2, so as to support the catheter 2 that is too long.

Further optionally, the sliding mechanism 5 further includes a first fastener 521, the sliding block 52 is provided with a first through hole, and the first fastener 521 can be inserted into the first through hole to fix the position of the sliding block 52 on the sliding rail 51, so as to realize the adjustment of the position of the bracket body 412 on the base 3.

Further optionally, the position of the bracket body 412 on the sliding block 52 is adjustable to change the clamping position of the limiting member 411 on the conduit 2 or the sliding sleeve 1, so as to ensure that the limiting member 411 can be clamped at a proper position on the surface of the conduit 2 or the sliding sleeve 1, and avoid damaging the heat insulation layer on the surface of the conduit body due to the friction between the limiting member 411 and the conduit 2 or the sliding sleeve 1. Specifically, the bracket body 412 further includes a second fastening member 4121, a second through hole is formed at the bottom end of the bracket body 412, and the second fastening member 4121 can be inserted into the second through hole to fix the position of the bracket body 412 on the slider 52.

Optionally, the auxiliary installation device for the aircraft conduit further comprises a driving mechanism 6, the first connecting member 41 is arranged at an output end of the driving mechanism 6, and the driving mechanism 6 is used for driving the first connecting member 41 to slide on the sliding rail 51. Or the second connecting member 42 is disposed at the output end of the driving mechanism 6, and the driving mechanism 6 is used for driving the second connecting member 42 to slide on the slide rail 51. The above arrangement shows two situations when the catheter 2 is assembled with the sliding sleeve 1: the first is that the second connecting piece 42 is fixed on the base 3 by the first fastener 521, the position of the connecting body of the first connecting piece 41 on the slide block 52 is adjusted by taking the position of the second connecting piece 42 as a reference, so that the slide sleeve 1 is as close to the conduit 2 as possible, and the position of the connecting body on the slide block 52 is fixed by the second fastener 4121; then, the height of the bracket body 412 of the first connecting piece 41 is adjusted, so that the sliding sleeve 1 and the guide pipe 2 are coaxially arranged; finally, the bracket body 412 of the first connecting piece 41 is connected with the output end of the driving mechanism 6, and the driving mechanism 6 is utilized to drive the first connecting piece 41 to slide on the base 3 along the direction close to the second connecting piece 42, so that the sliding sleeve 1 and the guide pipe 2 are efficiently and accurately assembled. The second is that the first connecting piece 41 is fixed on the base 3 by the first fastener 521, and the position of the connecting body of the second connecting piece 42 closest to the first connecting piece 41 on the slide block 52 is adjusted by taking the first connecting piece 41 as a reference, so that the conduit 2 is as close to the slide sleeve 1 as possible, and the position of the connecting body on the slide block 52 is fixed by the second fastener 4121; then adjusting the height of all the stent bodies 412 in the second connecting piece 42 to make the catheter 2 and the sliding sleeve 1 coaxially arranged; finally, the bracket body 412 of the second connecting piece 42 farthest from the first connecting piece 41 is connected to the output end of the driving mechanism 6, and the driving mechanism 6 is used to drive the second connecting piece 42 to slide on the base 3 along the direction close to the first connecting piece 41, so that the sliding sleeve 1 and the catheter 2 can be efficiently and accurately assembled.

Specifically, the driving mechanism 6 includes a rotating member 61 and a lead screw 62, which are rotatably disposed, and one end of the lead screw 62 is connected to the bracket body 412, and the other end thereof is screwed to the rotating member 61. The above arrangement can convert the rotation of the rotation member 61 into the linear motion of the lead screw 62. Further optionally, the driving mechanism 6 further includes a supporting member 63, the supporting member 63 is disposed on the base 3 along the vertical direction, the rotating member 61 is rotatably disposed on the supporting member 63, and the rotation axis of the rotating member 61 is parallel to the extending direction of the sliding rail 51, so that the driving direction of the driving mechanism 6 is the extending direction of the sliding rail 51.

Further optionally, two ends of the screw rod 62 are respectively provided with a sliding bearing, and the sliding bearings are used for reducing the friction force generated between the screw rod 62 and the support 63 and the bracket body 412 due to rotation, so that the rotation fluency of the screw rod 62 is improved.

It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Numerous obvious variations, adaptations and substitutions will occur to those skilled in the art without departing from the scope of the utility model. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. An auxiliary installation device for an aircraft conduit, for connecting a slip sleeve (1) and a conduit (2), characterized in that it comprises:

a base (3);

the connecting mechanism (4) comprises a first connecting piece (41) and a second connecting piece (42), the first connecting piece (41) is connected with the sliding sleeve (1), and the second connecting piece (42) is connected with the guide pipe (2); the first connecting piece (41) and the second connecting piece (42) are arranged on the base (3) in a sliding manner; the heights of the first connecting piece (41) and the second connecting piece (42) are adjustable.

2. The aircraft conduit auxiliary mounting device according to claim 1, wherein the first connecting member (41) and the second connecting member (42) each comprise a limiting member (411), the limiting member (411) is an annular sleeve, and the sliding sleeve (1) or the conduit (2) is sleeved in the annular sleeve so as to limit the movement of the sliding sleeve (1) or the conduit (2) in the axial direction and the radial direction.

3. The aircraft conduit secondary mounting device of claim 2, wherein the retainer (411) is provided with an opening that divides the retainer (411) into a first end and a second end; the locating part (411) further comprises a locking part (4111), and the locking part (4111) is used for locking the first end and the second end of the locating part (411).

4. The auxiliary installation device of an aircraft conduit according to claim 1, characterized in that a sliding mechanism (5) is arranged between the connecting mechanism (4) and the base (3), and the sliding mechanism (5) is arranged in one-to-one correspondence with the first connecting piece (41) and the second connecting piece (42) for realizing the sliding of the first connecting piece (41) and the second connecting piece (42) on the base (3).

5. Auxiliary installation device of an aircraft conduit according to claim 4, characterized in that the sliding mechanism (5) comprises a sliding rail (51) and a sliding block (52), and the sliding block (52) is arranged on the sliding rail (51) in a sliding manner along the extending direction of the sliding rail (51); the sliding rail (51) is arranged on the base (3) along the axial direction of the sliding sleeve (1), the first connecting piece (41) and the second connecting piece (42) both comprise a support body (412), and the sliding block (52) is connected with the bottom end of the support body (412).

6. Auxiliary installation device for aircraft ducts according to claim 5, characterized in that said sliding mechanism (5) further comprises a first fastening element (521), said sliding block (52) being provided with a first through hole, said first fastening element (521) being able to be inserted in said first through hole.

7. Auxiliary mounting device for aircraft ducts according to claim 5, characterized in that the position of the bracket body (412) on the slide (52) is adjustable.

8. The aircraft conduit secondary mounting device of claim 7, wherein the bracket body (412) further comprises a second fastener (4121), a bottom end of the bracket body (412) being provided with a second through hole, the second fastener (4121) being insertable into the second through hole.

9. Auxiliary installation device for aircraft ducts according to claim 5, characterized in that a plurality of said bracket bodies (412) are provided on said second connector (42), said bracket bodies (412) being distributed at intervals in the axial direction of said duct (2).

10. The auxiliary installation device of an aircraft conduit according to claim 1, further comprising a driving mechanism (6), wherein the first connecting piece (41) is arranged at the output end of the driving mechanism (6), and the driving mechanism (6) is used for driving the first connecting piece (41) to slide on the sliding rail (51); and/or

The second connecting piece (42) is arranged at the output end of the driving mechanism (6), and the driving mechanism (6) is used for driving the second connecting piece (42) to slide on the sliding rail (51).