CN215725630U

CN215725630U - Inspection device

Info

Publication number: CN215725630U
Application number: CN202121844604.6U
Authority: CN
Inventors: 关耀辉; 章印; 甘清照; 姜胜东; 朱傲然; 李世迪
Original assignee: Commercial Aircraft Corp of China Ltd; Shanghai Aircraft Manufacturing Co Ltd
Current assignee: Commercial Aircraft Corp of China Ltd; Shanghai Aircraft Manufacturing Co Ltd
Priority date: 2021-08-09
Filing date: 2021-08-09
Publication date: 2022-02-01
Anticipated expiration: 2031-08-09

Abstract

The utility model belongs to the technical field of aircraft inspection equipment, and discloses an inspection device which comprises a first support assembly, wherein the first support assembly comprises an adjusting piece, and the adjusting piece is movably arranged along a first direction; the second support assembly comprises a cross beam piece, a joint piece and a positioning piece, the cross beam piece rotates around the second direction and is connected to one end of the adjusting piece, the first direction is perpendicular to the second direction, the joint piece and the positioning piece are fixedly arranged on the cross beam piece, the joint piece is used for rotatably connecting the auxiliary wing cabin, and the positioning piece is used for abutting against the auxiliary wing cabin to limit the cross beam piece to rotate around the second direction; and the inspection assembly is arranged on the cross beam piece and is used for inspecting the appearance of the auxiliary wing cabin. The inspection assembly can inspect the appearance of the positioned aileron cabin, and ensures inspection speed and accuracy.

Description

Inspection device

Technical Field

The utility model relates to the technical field of aircraft inspection equipment, in particular to an inspection device.

Background

The aileron of the airplane is one part of a movable surface exchange piece, the aileron cabin is usually arranged at the tip of the wing of the airplane and is connected with the aileron by a hinge mechanism, the aileron needs to be replaced in the production of an assembly line and the conventional maintenance of the airplane, and the interchangeability of the aileron has great significance corresponding to the production field and the operation and maintenance of an air route. The interchangeability of the ailerons is mainly determined by two parts, namely whether the appearance of the ailerons is qualified or not, whether the installation position of an aileron cabin for accommodating the ailerons is qualified or not, and the aileron cabin is used as an important reference area for installing the ailerons, and the accuracy of the appearance of the aileron cabin directly influences multiple engineering technical requirements such as gaps, step differences and the like between the ailerons and the ailerons after the ailerons are installed, so the control on the accuracy of the appearance of the aileron cabin is particularly important.

In the existing technology for detecting the shape of the auxiliary wing cabin, a high-precision measuring instrument is used for scanning the shape of the auxiliary wing cabin, such as a laser tracker, a full-aircraft coordinate system or a local wing coordinate system is established through landmark points, and a point cloud scanning import technology is used for judging whether the shape of the auxiliary wing cabin is accurate and qualified. The aileron cabin is preheated when being detected by using the high-precision measuring instrument, the preparation period is long, the high-precision measuring instrument is expensive, the requirement on the use environment is high, and the convenience in use in an external field is poor.

SUMMERY OF THE UTILITY MODEL

One object of the present invention is: provided is a verification device which can improve the verification speed of the appearance of an aileron cabin by verifying the appearance of the aileron cabin through a verification component.

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

an inspection device comprising:

the first support assembly comprises an adjusting piece, and the adjusting piece is movably arranged along a first direction;

the second support assembly comprises a cross beam piece, a joint piece and a positioning piece, the cross beam piece is rotatably connected to one end of the adjusting piece around a second direction, the first direction is perpendicular to the second direction, the joint piece and the positioning piece are fixedly mounted on the cross beam piece, the joint piece is used for rotatably connecting an auxiliary wing cabin, the positioning piece extends to one side of the auxiliary wing cabin, and the positioning piece can limit the cross beam piece to rotate around the second direction when abutting against the auxiliary wing cabin;

a verification assembly mounted on the transom member for verifying the profile of the aileron nacelle.

As an optional technical scheme, the inspection assemblies are arranged in at least three groups at intervals, at least one group of inspection assemblies is used for inspecting the shape of the triangular area, at least one group of inspection assemblies is used for inspecting the shape of the upper wall plate, and at least one group of inspection assemblies is used for inspecting the shape of the partition plate.

As an alternative solution, at least two sets of inspection assemblies are provided for inspecting the upper panel.

As an alternative solution, the adjusting members are provided in two, wherein one of the adjusting members is connected to one end of the cross beam member, and the other adjusting member is connected to the other end of the cross beam member.

As an optional technical solution, the joint pieces are at least three at intervals along the extending direction of the cross beam piece, the joint pieces at two ends are respectively connected with the suspension arms of the aileron cabin through bolts, the joint piece in the middle is connected with the other suspension arm of the aileron cabin through a check pin rod, and the check pin rod is used for checking the coaxiality of the intersection points of the joint pieces and the suspension arms of the aileron cabin.

As an optional technical solution, the first support assembly further includes a chassis and a moving wheel, the moving wheel is mounted at the bottom of the chassis, and the adjusting member is mounted on the chassis.

As an optional technical solution, the first supporting component further comprises a supporting leg, the supporting leg is installed on the chassis, and the supporting leg is used for fixing the first supporting component on the ground.

As an optional technical scheme, a support is arranged on the chassis, a threaded hole is formed in the support, the adjusting piece is a screw rod, and the screw rod is in threaded connection with the threaded hole.

As an optional technical scheme, a handle piece is installed on the periphery of the adjusting piece.

As an optional technical solution, the first support assembly further comprises a fastener, the fastener is installed between the adjusting member and the cross beam member, and the fastener is used for limiting the rotation of the cross beam member around the second direction.

The utility model has the beneficial effects that:

the utility model provides a checking device, wherein when the checking device is moved to one side of an aileron cabin, a joint piece is rotatably connected with the aileron cabin to realize pre-positioning, and the joint piece is fixedly arranged on a cross beam piece and is rotatably connected with an adjusting piece, so that when the adjusting piece is pushed to a first direction, the cross beam piece drives the joint piece and a positioning piece to rotate around a second direction, the positioning piece rotates a preset angle and then abuts against the aileron cabin, the cross beam piece and a checking assembly arranged on the cross beam piece do not rotate any more, and at the moment, the checking assembly can be used for checking the appearance of the aileron cabin.

Drawings

The utility model is explained in further detail below with reference to the figures and examples;

FIG. 1 is a schematic view of a portion of a aileron nacelle according to an embodiment;

FIG. 2 is a schematic view of a first view of the inspection device according to the exemplary embodiment when inspecting an aileron nacelle;

FIG. 3 is an enlarged view of a portion of FIG. 2 at position A;

FIG. 4 is an enlarged view of a portion of FIG. 2 at position B;

FIG. 5 is an enlarged view of a portion of FIG. 2 at position C;

FIG. 6 is a schematic structural view of a second viewing angle at which the inspection device according to the embodiment inspects the aileron nacelle;

FIG. 7 is a schematic structural view of a third viewing angle at which the inspection device according to the embodiment inspects the aileron nacelle;

in fig. 1 to 7:

100. a secondary wing tank; 101. a triangular area; 102. an upper wall plate; 103. a partition plate; 104. hanging a support arm;

1. a first support assembly; 11. an adjustment member; 12. a chassis; 13. a moving wheel; 14. supporting legs; 15. a support; 16. a handle member; 17. a fastener;

2. a second support assembly; 21. a cross member; 22. a joint member; 23. a positioning member;

3. inspecting a clamping plate;

4. and (6) checking the pin rod.

Detailed Description

In order to make the technical problems solved, technical solutions adopted and technical effects achieved by the present invention clearer, the technical solutions of the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

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 herein, it is to be understood that the terms "upper," "lower," "left," "right," and the like are based on the orientation or positional relationship shown in the drawings for convenience in description and simplicity of operation, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the present invention. Furthermore, the terms "first" and "second" are used merely for descriptive purposes and are not intended to have any special meaning.

In the description herein, references to the description of "an embodiment," "an example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the utility model. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example.

The technical scheme of the utility model is further explained by the specific implementation mode in combination with the attached drawings.

When the laser tracker is adopted to inspect the appearance of the aileron cabin of the airplane, the use cost is high, the inspection period is prolonged due to the preheating of the laser tracker, the efficiency is low, and particularly when the aileron cabin is inspected in an outfield, the measurement accuracy is not high, and the convenience is poor.

Fig. 1 is a schematic view of a partial structure of an aileron nacelle 100.

As shown in fig. 2 to 7, to solve the above problem, the present embodiment provides an inspection device, which includes a first support assembly 1, a second support assembly 2, and an inspection assembly, wherein the first support assembly 1 includes an adjusting member 11, and the adjusting member 11 is movably disposed along a first direction; the second support assembly 2 comprises a cross beam piece 21, a joint piece 22 and a positioning piece 23, the cross beam piece 21 is rotatably connected to one end of the adjusting piece 11 around a second direction, the first direction is perpendicular to the second direction, the joint piece 22 and the positioning piece 23 are both mounted on the cross beam piece 21, the joint piece 22 is used for rotatably connecting the auxiliary wing cabin 100, the positioning piece 23 extends to one side of the auxiliary wing cabin 100, and the positioning piece 23 can limit the cross beam piece 21 to rotate around the second direction when abutting against the auxiliary wing cabin 100; the inspection assembly is mounted on the transom member 21 for inspecting the profile of the paravane pod 100.

Optionally, the first direction is a Z-axis direction, and the second direction is an X-axis direction.

Specifically, when the inspection device of the present embodiment is used, the ground bracket support structure is used to simulate an aileron, the ground bracket support structure supports the aileron cabin 100, the aileron cabin 100 is fixed, the inspection device is moved to one side of the aileron cabin 100, the joint member 22 is rotatably connected to the aileron cabin 100 to achieve pre-positioning, because the joint member 22 is fixedly mounted on the cross member 21 and the cross member 21 is rotatably connected to the adjustment member 11, when the adjustment member 11 is pushed in a first direction, the cross member 21 drives the joint member 22 and the positioning member 23 to rotate around a second direction, the positioning member 23 rotates by a preset angle and abuts against the aileron cabin 100, the cross member 21 and the inspection component mounted on the cross member 21 do not rotate any more, at this time, the inspection component can be used to quickly and accurately inspect the shape of the aileron cabin 100, because the adjustment member 11 is adjustable in the Z-axis direction, and therefore, the inspection device can be used in various situations, for example, different aircraft models, have different aileron pods at different heights from the ground, the inspection assembly can be adapted to the height position of the aileron pod 100 by moving the adjustment member 11 in the Z-axis direction.

The laser measurement is not suitable for the measurement of the profile of the aileron pod coordinated using an analog quantity (standard or coordination template), and therefore, in the present embodiment, the inspection component is the inspection pallet 3, the inspection pallet 3 can inspect the profile of the aileron pod 100, such as spanwise gap tolerance, surface gap tolerance, and the like, and further, the inspection pallet 3 and the aileron pod 100 are located at a preset gap to be inspected, and the preset gap can be measured by other measuring instruments, such as a caliper or a camera.

The ailerons of an aircraft have a plurality of regions of large span, so that the overall inspection accuracy cannot be guaranteed by inspecting the shape of only one position of the aileron pod.

Therefore, optionally, at least three groups of inspection assemblies are arranged at intervals, at least one group of inspection assemblies is used for inspecting the shape of the triangular area 101, such as the shape of the triangular area 101 in the X-axis direction and the Z-axis direction, at least one group of inspection assemblies is used for inspecting the shape of the upper wall plate 102, such as the shape and the heading dimension of the upper wall plate 102, and at least one group of inspection assemblies is used for inspecting the shape of the partition plate 103, such as the shape of the partition plate 103 in the X-axis direction and the Z-axis direction. The triangular area 101, the upper wall plate 102, the partition plate 103 and the suspension arm 104 are four parts of the aileron cabin 100 respectively.

Optionally, the inspection assemblies for inspecting the upper wall plate 102 are provided in at least two groups, in this embodiment, the inspection assemblies for inspecting the upper wall plate 102 are provided in four groups, and in other embodiments, the inspection assemblies can be provided in two groups, or three groups, or five groups. The inspection assemblies for inspecting the triangular region 101 are provided as a set, and the inspection assemblies for inspecting the partition 103 are provided as a set.

In the present embodiment, in order to ensure the balance when the cross member 21 rotates, the adjusting members 11 are provided in two, wherein one of the adjusting members 11 is connected to one end of the cross member 21, and the other adjusting member 11 is connected to the other end of the cross member 21.

Optionally, at least three joint pieces 22 are arranged at intervals along the extending direction of the cross beam piece 21, the joint pieces 22 at two ends are respectively connected with the suspension arm 104 of the aileron cabin 100 through bolts, the joint piece 22 in the middle is connected with the other suspension arm 104 of the aileron cabin 100 through a check pin rod 4, and the check pin rod 4 is used for checking the coaxiality of the intersection point of the joint piece 22 and the suspension arm 104 of the aileron cabin 100.

In this embodiment, the first support assembly 1 further comprises a chassis 12 and a moving wheel 13, the moving wheel 13 is mounted on the bottom of the chassis 12, and the adjusting member 11 is mounted on the chassis 12. After the joint piece 22 is connected with the suspension arm 104, the moving wheel 13 moves in the X-axis direction, so that the joint piece 22 is attached to the surface of the suspension arm 104, and the positioning is realized in the X-axis direction.

Optionally, the first support assembly 1 further includes a support leg 14, the support leg 14 is installed on the chassis 12, and the support leg 14 is used for fixing the first support assembly 1 on the ground.

Optionally, a support 15 is arranged on the chassis 12, a threaded hole is formed in the support 15, the adjusting piece 11 is a screw rod, the screw rod is connected to the threaded hole in a threaded manner, and the screw rod rotates in the threaded hole to achieve adjustment in the Z-axis direction.

Optionally, a handle member 16 is mounted to the outer periphery of the adjustment member 11 to facilitate an operator's grip on the handle member 16 to rotate the adjustment member 11. The handle member 16 may be selected from a flange, a handle, a dial, etc.

Optionally, the first support assembly 1 further includes a fastener 17, the fastener 17 is installed between the adjusting member 11 and the cross beam member 21, the fastener 17 is used for limiting the rotation of the cross beam member 21 around the second direction, and after the positioning member 23 abuts against the auxiliary wing cabin 100, the cross beam member 21 is fastened and locked with the adjusting member 11 through the fastener 17, so as to complete the positioning of the inspection device. The fastener 17 may be selected as a fastening bolt.

In addition, the foregoing is only the preferred embodiment of the present invention and the technical principles applied. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the utility model. Therefore, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. An inspection apparatus, comprising:

the second support assembly comprises a cross beam piece, a joint piece and a positioning piece, the cross beam piece is rotatably connected to one end of the adjusting piece around a second direction, the first direction is perpendicular to the second direction, the joint piece and the positioning piece are fixedly mounted on the cross beam piece, the joint piece is used for rotatably connecting an auxiliary wing cabin, the positioning piece extends to one side of the auxiliary wing cabin, and the positioning piece can limit the cross beam piece to continuously rotate around the second direction when abutting against the auxiliary wing cabin;

2. The inspection device of claim 1, wherein said inspection assemblies are spaced apart in at least three groups, at least one group of said inspection assemblies for inspecting the shape of the triangular space, at least one group of said inspection assemblies for inspecting the shape of the upper panel, and at least one group of said inspection assemblies for inspecting the shape of the partition.

3. The inspection device of claim 2, wherein said inspection assemblies for inspecting said upper panel are provided in at least two sets.

4. The testing device of claim 1, wherein said adjustment members are provided in two, one of said adjustment members being attached to one end of said cross-beam member and the other of said adjustment members being attached to the other end of said cross-beam member.

5. An inspection device as claimed in claim 4, wherein the joint members are spaced apart at least three times in the direction of extension of the cross member, the joint members at the two ends being connected to the arms of the aileron nacelle by bolts, respectively, and the joint member in the middle being connected to the other arm of the aileron nacelle by an inspection pin for inspecting the coaxiality of the intersection of the joint members with the arms of the aileron nacelle.

6. The testing device of claim 1, wherein the first support assembly further comprises a chassis and a moving wheel mounted to a bottom of the chassis, the adjustment member being mounted to the chassis.

7. The testing device of claim 6, wherein said first support assembly further comprises a support foot mounted on said chassis, said support foot being configured to secure said first support assembly to the ground.

8. The inspection device of claim 6, wherein the chassis is provided with a bracket, the bracket is provided with a threaded hole, the adjusting member is a screw rod, and the screw rod is in threaded connection with the threaded hole.

9. The testing device of claim 8, wherein a handle member is mounted to the outer periphery of the adjustment member.

10. The testing device of claim 1, wherein said first support assembly further comprises a fastener mounted between said adjuster and said cross-member, said fastener for limiting rotation of said cross-member about said second direction.