CN115839643A - Airplane skin step difference measuring tool and measuring method - Google Patents
Airplane skin step difference measuring tool and measuring method Download PDFInfo
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- CN115839643A CN115839643A CN202211572393.4A CN202211572393A CN115839643A CN 115839643 A CN115839643 A CN 115839643A CN 202211572393 A CN202211572393 A CN 202211572393A CN 115839643 A CN115839643 A CN 115839643A
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Abstract
The invention discloses an aircraft skin step difference measuring tool and a measuring method. The invention also discloses a measuring method, which comprises the following steps: s1, prejudging the height of a step difference between a skin A and a skin B; s2, placing a measuring sheet for measurement, and observing and judging a step difference value from the side; s3, placing the skin B in the measuring groove, enabling the skin A to be attached to the bottom of the measuring sheet, and selecting the measuring sheet with the smallest measuring groove in the measuring sheets when the skin B is not attached to the measuring sheet, wherein the groove depth H of the measuring groove in the measuring sheet is the upper limit value of the step difference; s4, if the skin B cannot be placed in the measuring groove, selecting the measuring sheet of the largest measuring groove in the measuring sheets, wherein the groove depth H of the measuring groove is the lower limit value of the step difference; s5, determining a specific skin order difference value or range; the technical problem of large measurement error in the prior art is solved.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a tool and a method for measuring the jump of an aircraft skin.
Background
The aircraft skin is a dimensional component which is wrapped outside an aircraft framework structure and is fixed on the framework by using an adhesive or rivets to form the aerodynamic shape of the aircraft. The skin structure formed by the aircraft skin and the framework has large bearing capacity and rigidity, and light dead weight, and plays a role in bearing and transmitting aerodynamic load. The skin bears the aerodynamic action and then transmits the acting force to the connected fuselage wing framework, the stress is complex, and in addition, the skin is directly contacted with the outside, so that the skin material is required to have high strength, good plasticity, smooth surface and higher corrosion resistance.
The requirements on the surface quality of the aircraft, whether military aircraft or civil aircraft, are higher and higher, and particularly the requirements on the step difference of skin butt joint are higher and higher. The surface smoothness of the airplane directly influences the stealth performance, the reliability of structural strength, the fuel economy and the like of the airplane. In general, the requirement of a designer on the butt joint step difference of the skin is mostly lower than 0.3mm, and the width is widened to 0.8mm under special conditions.
The applicant has found that the prior art still has at least the following technical problems: in the process of airplane assembly, when inspectors measure the skin butt seam order difference value of an airplane, no standardized and efficient tool exists. The inspector mostly judges the step difference through visual inspection, hand touch and other forms, and in special cases, the clearance gauge is compared by means of hand touch. The feeler gauge is a large plane, curved surface and gradual change butt joint measurement are inaccurate, the pre-judgment results of different personnel are different during measurement, and a great amount of time is consumed in the measurement process.
Disclosure of Invention
The invention aims to provide an aircraft skin step difference measuring tool to solve the technical problem of large measuring error in the prior art.
In order to achieve the purpose, the invention provides an aircraft skin step difference measuring tool which comprises a fixing assembly and a plurality of measuring pieces, wherein the measuring pieces are movably connected through the fixing assembly, the measuring pieces are rectangular, and each measuring piece is provided with a measuring groove.
Furthermore, the plurality of measuring pieces are respectively provided with measuring grooves with different depths.
Further, a plurality of the measuring sheets are stacked from top to bottom, and the stacked measuring sheets are strung by the fixing assembly.
Further, the depth difference of the measuring grooves on the two adjacent measuring sheets is
mm。
Further, the groove depth H of the measurement groove with the minimum depth is 0.1mmm, and the groove depth H of the measurement groove with the maximum depth is 1.0mmm.
Further, the length of the measuring groove is half of the length of the measuring sheet.
Furthermore, four corners of the measuring sheet are rounded corners.
Furthermore, the fixing assembly comprises a connecting shaft and a fixing ring, a connecting hole is formed in one side, far away from the measuring groove, of the measuring piece, and the two ends of the connecting shaft are fixed through the fixing ring after penetrating through the connecting hole.
Further, the hardness of the measuring piece after heat treatment is 50-55HRC.
The application also discloses a measuring method based on the aircraft skin step difference measuring tool, which comprises the following steps:
s1, prejudging the height of a step difference between a skin A and a skin B;
s2, selecting one or more measuring pieces with groove depths H close to a pre-judgment value from the plurality of measuring pieces, placing the measuring pieces for measurement, and observing a judgment order difference value L from the side;
s3, placing the skin B in the measuring groove, enabling the skin A to be attached to the bottom of the measuring sheet, and selecting the measuring sheet with the smallest measuring groove in the measuring sheet when the skin B is not attached to the measuring sheet, wherein the groove depth H of the measuring groove in the measuring sheet is the upper limit value of the step difference;
s4, if the skin B cannot be placed in the measuring groove, selecting the measuring sheet of the largest measuring groove in the measuring sheets, wherein the groove depth H of the measuring groove is the lower limit value of the step difference;
and S5, determining a specific skin order difference value L or range.
Based on the technical scheme, the invention has the following advantages: according to the measuring tool and the measuring method for the aircraft skin step difference, the measured value is the step difference value L which is more accurate, the accurate value range of the measuring sheet detection groove is within 0.1mm, and the technical problem of large measuring error in the prior art is solved.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a schematic flow chart of an embodiment of the present invention;
in the figure: 1-measuring the sheet; 2-measuring the groove; 3-connecting hole.
Detailed Description
In order to better understand the purpose, structure and function of the present invention, an aircraft skin step difference measuring tool of the present invention is described in further detail below with reference to the accompanying drawings.
In the description of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element 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 "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
It should be noted that the tool and the method for measuring the step difference of the aircraft skin disclosed by the application are specially used for detecting the seam step difference value L of the aircraft skin.
In order to achieve the purpose, the invention provides an aircraft skin step difference measuring tool which comprises a fixing assembly and a plurality of measuring pieces 1, wherein the measuring pieces 1 are movably connected through the fixing assembly, the measuring pieces 1 are rectangular, and each measuring piece 1 is provided with a measuring groove 2.
The thickness of each measuring piece 1 is preferably 0.8mm.
Based on the technical requirements of various airplane models on skin step difference in China at present, the skin butt-joint step difference value L can be measured quickly and accurately by combining the design form of the measuring sheet 1.
Furthermore, the plurality of measuring pieces 1 are respectively provided with measuring grooves 2 with different depths.
Further, a plurality of the measuring sheets 1 are stacked in sequence from top to bottom, and the stacked plurality of measuring sheets 1 are strung by the fixing assembly.
Further, the depth difference of the measuring grooves 2 on the two adjacent layers of the measuring sheets 1 is
mm. The measuring sheet 1 is a combined measuring tool, and the measuring range is increased from 0.1mm to 1.0 mm.
Further, the groove depth H of the measurement groove 2 with the smallest depth is 0.1mmm, and the groove depth H of the measurement groove 2 with the largest depth is 1.0mmm.
It should be noted that, in the measurement and judgment in the prior art, the inspector cannot measure a specific step difference value L, only one pre-judged value can be provided under the condition of the feeler gauge and the hand feeling, and the step difference values L judged by different persons during pre-judgment are different. This also creates a centralized problem for operators to compete with the inspection personnel. The measured value of the invention can be given to be more accurate step difference value L, and the accurate value range of the detection groove of the measuring sheet 1 is in the range of 0.1 mm. Meanwhile, the groove depth H of the detection groove of the measuring sheet 1 can be further reduced or the number of the measuring sheets 1 can be increased according to different application scenes and requirements, so that the measured value is more accurate, and the measuring range is larger. On the other hand, in the prior art, an inspector gives a skin-to-seam step value L time of at least 3 minutes through visual inspection, hand touch and the like. The invention can lock the range of the step value L by quickly replacing the measuring sheets 1, and finally, the upper limit value and the lower limit value of the actual skin step are given by using the two measuring sheets 1. One skin-to-seam step value L was measured for less than 1 minute. In addition, if the reworking and reworking of the product are more accurate, if the step tolerance of the skin on the aircraft product is out of tolerance, the inspector can not provide an accurate out-of-tolerance part on the aircraft product, such as: and the specific starting point and the actual length of the over-tolerance of the butt seam skin are extended. The method can quickly measure and mark the specific position of the aircraft skin butt joint over-tolerance on the product. The worker is more targeted when performing rework repair operations.
The roughness group of each surface of the measurement piece 1 was 0.4. The chamfer of the measuring chip 1 is R1.
Further, the length of the measuring groove 2 is half of the length of the measuring piece 1.
Furthermore, four corners of the measuring piece 1 are rounded.
Furthermore, the fixing assembly comprises a connecting shaft and a fixing ring, a connecting hole 3 is formed in one side, far away from the measuring groove 2, of the measuring piece 1, and the connecting shaft penetrates through the connecting hole 3 and then is fixed at two ends through the fixing ring.
Further, the hardness of the measuring piece 1 after heat treatment is 50-55HRC.
The application also discloses a measuring method based on the aircraft skin step difference measuring tool, which comprises the following steps:
s1, prejudging the height of a step difference between a skin A and a skin B;
s2, selecting one or more measuring pieces 1 with groove depths H close to a pre-judgment value from the plurality of measuring pieces 1, placing the measuring pieces 1 for measurement, and observing a judgment order difference value L from the side;
s3, placing the skin B in the measuring groove 2, enabling the skin A to be attached to the bottom of the measuring sheet 1, when the skin B is not attached to the measuring sheet 1, selecting the measuring sheet 1 with the smallest measuring groove 2 in the measuring sheet 1, and enabling the groove depth H of the measuring groove 2 in the measuring sheet 1 to be the upper limit value of the step difference;
s4, if the skin B cannot be placed in the measuring groove 2, selecting the measuring sheet 1 of the largest measuring groove 2 in the measuring sheets 1, wherein the groove depth H of the measuring groove 2 is the lower limit value of the step difference;
and S5, determining a specific skin order difference value L or range.
It should be noted that, as shown in fig. 2, in S3-S4, through side view, the light may be emitted by means of a flashlight, and the step difference value L is determined, that is, on the premise that the skin a is attached to the measuring sheet 1, when the skin B is not attached to the measuring sheet 1, the depth value of the measuring groove 2 of the selected minimum measuring sheet 1 is the upper limit value of the step difference, and when the measuring sheet 1 cannot be snapped into the skin B, the depth value of the measuring groove 2 of the selected maximum measuring sheet 1 is the lower limit value of the step difference.
It is to be understood that the present invention has been described with reference to certain embodiments, and that various changes or equivalents may be made by those skilled in the art without departing from the spirit and scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.
Claims (10)
1. The utility model provides an aircraft skin jump measuring tool, characterized in that, is including fixed subassembly and a plurality of measuring piece (1), and is a plurality of measuring piece (1) passes through fixed subassembly swing joint, measuring piece (1) is the rectangle, every measuring tank (2) have all been seted up on measuring piece (1).
2. The tool for measuring the jump of the aircraft skin as claimed in claim 1, wherein a plurality of the measuring sheets (1) are respectively provided with measuring grooves (2) having different depths.
3. The aircraft skin step measurement tool according to claim 1, characterized in that a plurality of measurement sheets (1) are stacked in sequence from top to bottom, and the stacked measurement sheets (1) are strung up by the fixing assembly.
4. The aircraft skin step difference measuring tool according to claim 2, characterized in that the depth difference of the measuring grooves (2) on two adjacent layers of the measuring sheets (1) is
mm。
5. The aircraft skin step measurement tool according to claim 4, characterized in that the measurement groove (2) with the smallest depth has a groove depth H of 0.1mmm, and the measurement groove (2) with the largest depth has a groove depth H of 1.0mmm.
6. The aircraft skin step measurement tool according to claim 1, characterized in that the length of the measuring groove (2) is half the length of the measuring blade (1).
7. The aircraft skin step measurement tool according to claim 1, characterized in that four corners of the measurement piece (1) are rounded.
8. The aircraft skin step difference measuring tool according to claim 1, wherein the fixing assembly comprises a connecting shaft and a fixing ring, a connecting hole (3) is formed in one side of the measuring piece (1) far away from the measuring groove (2), and both ends of the connecting shaft are fixed through the fixing ring after the connecting shaft passes through the connecting hole (3).
9. The aircraft skin step measurement tool according to claim 1, characterized in that the hardness of the measurement piece (1) after heat treatment is 50-55HRC.
10. A method for measuring the aircraft skin step difference measuring tool based on the claim 9, which is characterized by comprising the following steps:
s1, prejudging the height of a step difference between a skin A and a skin B;
s2, selecting one or more measuring sheets (1) with groove depths H close to a pre-judgment value from the plurality of measuring sheets (1), placing the measuring sheets (1) for measurement, and observing a judgment order difference value L from the side;
s3, placing the skin B in the measuring groove (2), attaching the skin A to the bottom of the measuring sheet (1), and selecting the measuring sheet (1) with the smallest measuring groove (2) in the measuring sheet (1) when the skin B is not attached to the measuring sheet (1), wherein the groove depth H of the measuring groove (2) in the measuring sheet (1) is the upper limit value of the step difference;
s4, if the skin B cannot be placed in the measuring groove (2), selecting the measuring sheet (1) of the largest measuring groove (2) in the measuring sheets (1), wherein the groove depth H of the measuring groove (2) is the lower limit value of the step difference;
and S5, determining a specific skin order difference value L or range.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211572393.4A CN115839643A (en) | 2022-12-08 | 2022-12-08 | Airplane skin step difference measuring tool and measuring method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211572393.4A CN115839643A (en) | 2022-12-08 | 2022-12-08 | Airplane skin step difference measuring tool and measuring method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115839643A true CN115839643A (en) | 2023-03-24 |
Family
ID=85578299
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211572393.4A Pending CN115839643A (en) | 2022-12-08 | 2022-12-08 | Airplane skin step difference measuring tool and measuring method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115839643A (en) |
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2022
- 2022-12-08 CN CN202211572393.4A patent/CN115839643A/en active Pending
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