CN212605896U - Aileron appearance detects frock - Google Patents
Aileron appearance detects frock Download PDFInfo
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- CN212605896U CN212605896U CN202020937235.4U CN202020937235U CN212605896U CN 212605896 U CN212605896 U CN 212605896U CN 202020937235 U CN202020937235 U CN 202020937235U CN 212605896 U CN212605896 U CN 212605896U
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Abstract
The utility model relates to a detect technical field, disclose an aileron appearance detects frock. The aileron appearance detection tool comprises a main framework, a clamping plate and a fixing component, wherein the main framework extends along the course direction and is provided with a clamping foot; the clamping plate is arranged at one end of the main framework, one side of the clamping plate, which is close to the ailerons, is provided with a detection surface, and the appearance of the detection surface is the same as that of the ailerons; the fixed assembly is arranged on the main framework and detachably connected with the wing box section, and when the fixed assembly is connected with the wing box section and the clamping feet are in surface contact with the upper surface of the wing box section, the intervals of all positions between the detection surface and the ailerons are the same. The utility model realizes the connection between the main framework, the clamping feet, the clamping board and the wing box sections by additionally arranging the fixing component which is detachably connected with the wing box sections, thereby increasing the connection stability during detection; the detection precision is improved through the matching of the detection surface and the clamping pins; generally, the aileron appearance detects frock simple structure, and light in weight connects stability good, detects the precision height.
Description
Technical Field
The utility model relates to a detect technical field, especially relate to an aileron appearance detects frock.
Background
The airplane aileron is used as a main tail end execution unit in an airplane flight control system, is mainly responsible for adjusting the roll attitude of an airplane and is also an important component for airplane attitude trimming. The aileron is usually arranged at the tip of the wing and is connected with the wing back beam by a hinge mechanism. No matter the airplane is manufactured and maintained, the zero adjustment of the structure is needed after the aileron is installed, and the coincidence of the appearance of the aileron and the appearance of the wing box section is checked. Taking a certain type of airplane as an example, the aileron needs to be adjusted to a structural zero position after being installed, and the requirements on the clearance, the step difference and the shape inosculation of the aileron relative to the trailing edge of the wing are respectively met at the zero position. Generally, there are two devices for performing the aileron zeroing and the contour matching inspection, one is the traditional cardboard detection method; one is the modern digital detection method by optical instruments.
The traditional solid card board method usually uses the theoretical appearance of an airplane as a blue book, usually uses an integral airplane and a detection sample board, the shape of the sample board is the equidistant appearance of the wing, the front and the back of the sample board are provided with fixed card feet, the sample board is used as a support at the front and the back beams of the wing (the area with higher precision of the appearance of the wing) during detection, and the matching performance of the aileron relative to the appearance of the wing is judged through the distance between the tail end of the card board and. The advantage of entity cardboard is that it is comparatively convenient to use, can utilize the cardboard to accomplish zeroing and the location of aileron fast, but traditional integral machine adds that detection model weight is great, leans on the card foot exhibition to support stability relatively poor simply, has certain influence to the precision that detects.
In addition to the conventional cardboard test, digital assembly tests of aircraft may employ high precision optical instruments (e.g., laser trackers) to adjust the flap null or evaluate the conformance of the flap profile to the wing box. The general method of the operation is to establish a full-aircraft coordinate system or a local wing coordinate system through a landmark point and adjust the zero position of the aileron through a horizontal detection point on the aileron; the method comprises the steps of scanning the appearances of the ailerons and the wing box when the ailerons are at the zero position of the structure, performing detection point cloud optimal fitting based on the wing box, and evaluating the inosculation of the appearances of the ailerons by taking the appearances of the wing box as a reference (focusing on the appearances of the front beam and the back beam during fitting). The digital detection has the advantages that the shapes of the ailerons and the corresponding wing boxes can be comprehensively detected, and the defects that the detection needs preheating, the preparation period is longer, the influence of wing deflection deformation is influenced during local data analysis, and the influence of deflection deformation can be reduced only by special flexible finite element analysis. In addition, the laser tracker is expensive, has high requirements on the use environment, and is poor in the convenience of maintenance and outfield use.
In other words, under the existing operating conditions of manufacturing and maintenance, the solid snap-gauge still has its necessity in the zeroing and detection of the flap, and therefore, a flap profile detection tool is needed to solve the technical problem of the solid snap-gauge in the prior art.
SUMMERY OF THE UTILITY MODEL
Based on above, an object of the utility model is to provide an aileron appearance detects frock, simple structure, light in weight, connection stability is good, detects the precision height.
In order to achieve the purpose, the utility model adopts the following technical proposal:
an aileron appearance detects frock includes:
the main framework extends along the course direction and is provided with a clamping foot;
the clamping plate is arranged at one end of the main framework, a detection surface is arranged on one side of the clamping plate close to the ailerons, and the appearance of the detection surface is the same as that of the ailerons;
the fixed component is arranged on the main framework and detachably connected with the wing box section, and when the fixed component is connected with the wing box section, the clamping feet are in contact with the upper surface of the wing box section, and the detection surface is the same as the interval of each part between the ailerons.
As an optimal scheme of the aileron appearance detection tool, the fixed component comprises a fixed seat and a sucker, and the sucker is detachably connected with the wing box section.
As a preferred scheme of the aileron appearance detection tool, the number of the suckers is two, and the two suckers extend in the spanwise direction perpendicular to the course direction.
As a preferred scheme of the aileron appearance detection tool, two fixing assemblies are arranged, and the two fixing assemblies extend along the course direction.
As a preferred scheme of aileron appearance detection frock, still include set up in fixed subassembly with the adjusting part between the main frame, the adjusting part is configured to can adjust the main frame with the distance between the wing box section, so that the card foot with the upper surface butt of wing box section.
As an optimal scheme that aileron appearance detected frock, adjusting part includes regulating plate, adjusting stud and adjusting nut, the regulating plate with the main frame is connected, adjusting stud one end with the regulating plate is connected, the other end with fixed subassembly is connected, adjusting nut in the regulating plate with between the fixed subassembly with adjusting stud threaded connection revolves soon adjusting nut is in order to adjust the main frame with distance between the wing box section.
As an optimal scheme of the aileron appearance detection tool, the clamping plate is detachably connected with the main framework.
As a preferred scheme of the aileron appearance detection tool, the clamping plate is provided with lightening holes.
As a preferred scheme of the aileron appearance detection tool, a handle hole is formed in the main framework.
As an optimal scheme of the aileron appearance detection tool, a bakelite support is arranged on the main framework and is abutted to the upper surface of the wing box section.
The utility model has the advantages that: the main framework, the clamping feet, the clamping boards and the wing box sections are connected by additionally arranging the fixing components which are detachably connected with the wing box sections, so that the connection stability during detection is effectively improved; in addition, a detection surface with the same appearance as the aileron is arranged on one side of the clamping plate close to the aileron and used for realizing the detection of the aileron, and the clamping foot abutted to the upper surface of the wing box section is matched, so that the detection precision is effectively improved; generally, the aileron appearance detects frock simple structure, and light in weight connects stability good, detects the precision height.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required to be used in the description of the embodiments of the present invention will be briefly described below, and 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 the contents of the embodiments of the present invention and the drawings without creative efforts.
Fig. 1 is a schematic view of an aileron profile inspection tool according to an embodiment of the present invention;
fig. 2 is a front view of an aileron profile inspection tool according to an embodiment of the present invention;
fig. 3 is a top view of the aileron profile inspection tool according to the embodiment of the present invention.
In the figure:
1-a main skeleton; 11-clamping feet; 12-handle hole;
2-clamping plate; 21-detection surface; 22-lightening holes;
3-a fixing component; 31-a fixed seat; 32-a suction cup;
4-a regulating component; 41-adjusting plate; 42-adjusting the nut.
Detailed Description
In order to make the technical problems, technical solutions and technical effects achieved by the present invention more clear, the embodiments of the present invention will be described in further detail with reference to the accompanying drawings, and obviously, the described embodiments are only some embodiments, not all embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by those skilled in the art without creative efforts belong to the protection scope of the present invention.
As shown in fig. 1 to 3, the present embodiment provides an aileron profile inspection tool, which includes a main frame 1, a clamping plate 2 and a fixing component 3, wherein the main frame 1 extends along a course direction, and a clamping foot 11 is arranged on the main frame; the clamping plate 2 is arranged at one end of the main framework 1, one side of the clamping plate 2 close to the aileron is provided with a detection surface 21, and the shape of the detection surface 21 is the same as that of the aileron; the fixed component 3 is arranged on the main framework 1 and detachably connected with the wing box section, when the fixed component 3 is connected with the wing box section, and the clamping feet 11 are in surface contact with the upper surface of the wing box section, the intervals of the detection surface 21 and the ailerons are the same.
The main framework 1, the clamping feet 11, the clamping boards 2 and the wing box sections are connected by additionally arranging the fixing components 3 which are detachably connected with the wing box sections, so that the connection stability during detection is effectively improved; in addition, a detection surface 21 with the same appearance as the aileron is arranged on one side of the clamping plate 2 close to the aileron and used for realizing the detection of the aileron, and the clamping foot 11 abutted against the upper surface of the wing box section is matched, so that the detection precision is effectively improved; generally, the aileron appearance detects frock simple structure, and light in weight connects stability good, detects the precision height.
Specifically, fixed subassembly 3 includes fixing base 31 and sucking disc 32, and fixing base 31 is connected with main skeleton 1, and sucking disc 32 can dismantle with the wing box section and be connected. When the aileron appearance detection tool is needed to detect the aileron, the main framework 1 and the snap gauge 2 can be connected to the upper surface of the wing box section through the suction cup 32, and the suction cup 32 is released after the detection is finished, so that the main framework 1 and the snap gauge 2 are separated from the aileron; the detachable connection of the main framework 1 and the wing box section is realized by adopting the sucking disc 32, the connection is simple and firm, meanwhile, the upper surfaces of the ailerons and the wing box section cannot be damaged, and the attractiveness of the upper surface of the ailerons is ensured. It should be noted that the suction cups 32 are available in the prior art and can be obtained by outsourcing, and those skilled in the art can select a suction cup 32 with a suitable suction force according to actual use conditions to ensure the connection firmness of the main frame 1 and the clamping plate 2.
Furthermore, two suction cups 32 are arranged, the two suction cups 32 extend along the spanwise direction, and the spanwise direction is perpendicular to the heading direction; furthermore, two fixing assemblies 3 are arranged, and the two fixing assemblies 3 extend along the course direction; that is, the number of the suckers 32 is four, so that the firmness of connection between the main framework 1 and the clamping plate 2 and the upper surface of the wing box section during detection is effectively ensured. In other embodiments, the two suction cups 32 may also extend at an angle to the course direction, which is beneficial to reduce the size of the aileron profile inspection tool in the span-wise direction.
In this embodiment, aileron appearance detects frock still including setting up adjusting part 4 between fixed subassembly 3 and skeleton 1, adjusting part 4 sets up between fixing base 31 and skeleton 1, and adjusting part 4 can be used for adjusting the distance between skeleton 1 and the wing box section, through adjusting part 4 in the testing process, makes the upper surface butt of card foot 11 and wing box section, the detection of cardboard 2 of being convenient for. It should be noted that two clamping feet 11 are provided, and are respectively used for clamping with the wing front beam axial plane and the wing back beam axial plane.
Further, the adjusting assembly 4 comprises an adjusting plate 41 and an adjusting stud, the adjusting plate 41 is arranged in a U shape, and the main framework 1 is arranged in the U-shaped adjusting plate 41 and connected with the adjusting plate 41; one end of the adjusting stud is connected with the bottom edge of the adjusting plate 41, and the other end of the adjusting stud is in threaded connection with the fixing frame; when the distance between the main framework 1 and the wing box section needs to be adjusted, the adjusting stud is screwed to achieve the function of adjusting the distance between the main framework 1 and the wing box section, and the adjusting assembly 4 is simple in structure and convenient to operate. Further specifically, the relative positions of the component 3 and the main framework 1 can be further fixed by changing the installation positions of the adjusting plate 41 and the main framework 1, so that the detection of ailerons of different models is realized, and the universality of the aileron appearance detection tool is improved.
Preferably, cardboard 2 can be dismantled with main skeleton 1 and be connected, and different model ailerons correspond the main skeleton 1 of different detection faces 21, and cardboard 2 can be dismantled with main skeleton 1 and be connected and can improve the commonality that the aileron appearance detected the frock. In order to reduce the weight of the aileron appearance detection tool, the clamping plate 2 is further provided with lightening holes 22 under the condition that the strength of the clamping plate 2 is ensured, and the lightening holes 22 are round in the embodiment, so that the aileron appearance detection tool is convenient to process. In addition, in order to facilitate the installation and transfer of the flap profile detection tool, the main frame 1 is provided with a handle hole 12, and further preferably, the handle hole 12 is provided as an oblong hole.
In this embodiment, the length of main frame 1 is longer, so be provided with the bakelite support on the main frame 1, the bakelite support is used for the upper surface butt of main frame 1 and wing box section, plays the effect of supporting and stabilizing main frame 1.
The use method of the aileron shape detection tool comprises the following steps: firstly, after an aileron is connected with an aileron actuator, two clamping feet 11 are aligned left and right along a certain rib axis of the airfoil along the wingspan direction by referring to a fastening piece head on the upper surface of a wing box section, and the position of an aileron shape detection tool in the spanwise direction is determined; secondly, moving the aileron appearance detection tool along the course direction to enable the two clamping feet 11 to be respectively aligned with the axial plane of the front beam of the wing and the axial plane of the rear beam of the wing; thirdly, operating the suction cup 32 to fix the main framework 1 and the clamping plate 2 on the upper surface of the wing box section through the suction cup 32; fourthly, adjusting an adjusting nut 42 of the adjusting component 4 to enable the two clamping feet 11 to be respectively contacted with the upper surface of the wing box section; and fifthly, rotating the ailerons to enable the distance between the adjusted ailerons and the clamping plate 2 to meet the requirement of equal distance of 10 mm.
It should be noted that the foregoing is only a 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 invention. Therefore, although the present invention has been described in greater detail with reference to the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Wherein the terms "first position" and "second position" are two different positions.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Claims (10)
1. The utility model provides an aileron appearance detects frock which characterized in that includes:
the main framework (1) extends along the course direction, and is provided with a clamping foot (11);
the fastening plate (2) is arranged at one end of the main framework (1), a detection surface (21) is arranged on one side, close to the ailerons, of the fastening plate (2), and the shape of the detection surface (21) is the same as that of the ailerons;
fixed subassembly (3), set up in on main frame (1), can dismantle with the wing box and be connected, work as fixed subassembly (3) with the wing box is connected, card foot (11) with during the upper surface contact of wing box, detection surface (21) with the interval homogeneous phase of each department between the aileron.
2. The aileron profile inspection tooling of claim 1, wherein the fixed assembly (3) comprises a fixed seat (31) and a suction cup (32), and the suction cup (32) is detachably connected with the wing box.
3. The aileron profile inspection tool of claim 2, wherein there are two suction cups (32), and the two suction cups (32) extend in a span-wise direction perpendicular to the course direction.
4. The aileron profile inspection tooling of claim 1, wherein there are two of the securing assemblies (3), and the two securing assemblies (3) extend in the course direction.
5. The aileron profile detection tooling of claim 1, further comprising an adjustment assembly (4) disposed between the fixing assembly (3) and the main frame (1), wherein the adjustment assembly (4) is configured to adjust a distance between the main frame (1) and the wing box so that the clip leg (11) abuts against an upper surface of the wing box.
6. The aileron shape detection tooling of claim 5, wherein the adjusting component (4) comprises an adjusting plate (41), an adjusting stud and an adjusting nut (42), the adjusting plate (41) is connected with the main frame (1), one end of the adjusting stud is connected with the adjusting plate (41), the other end of the adjusting stud is connected with the fixing component (3), the adjusting nut (42) is connected with the adjusting stud through threads between the adjusting plate (41) and the fixing component (3), and the adjusting nut (42) is screwed to adjust the distance between the main frame (1) and the wing box section.
7. The aileron shape detection tooling of claim 1, wherein the snap-gauge (2) is detachably connected with the main framework (1).
8. The aileron profile testing tool according to claim 1, wherein the snap-gauge (2) is provided with a lightening hole (22).
9. The aileron profile inspection tool according to claim 1, characterized in that the main frame (1) is provided with a handle hole (12).
10. The aileron shape detection tooling of claim 1, wherein the main framework (1) is provided with a bakelite support which is abutted against the upper surface of the wing box section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020937235.4U CN212605896U (en) | 2020-05-28 | 2020-05-28 | Aileron appearance detects frock |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020937235.4U CN212605896U (en) | 2020-05-28 | 2020-05-28 | Aileron appearance detects frock |
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| CN212605896U true CN212605896U (en) | 2021-02-26 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114212275A (en) * | 2021-12-10 | 2022-03-22 | 江西昌河航空工业有限公司 | Device and method for inspecting appearance of front skin of airplane |
-
2020
- 2020-05-28 CN CN202020937235.4U patent/CN212605896U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114212275A (en) * | 2021-12-10 | 2022-03-22 | 江西昌河航空工业有限公司 | Device and method for inspecting appearance of front skin of airplane |
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