阅读说明：本技术 一种快速检测飞机零件大半径的方法及装置 (Method and device for rapidly detecting large radius of airplane part ) 是由 樊娜娜 丁苏煜 李亮 于 2021-08-25 设计创作，主要内容包括：本发明公开了一种快速检测飞机零件大半径的方法及装置,方法包括S1、在飞机零件表面的待测区域选择三点；S2、确保三点所在平面垂直于待测区域,同时三点构成等腰三角形；S3、测量第一距离、第二距离和第三距离中的至少两个；S4、构建直角三角形,使用三角函数和/或勾股定理建立等式关系,得到待测区域的半径；装置包括标尺,以及连接在标尺上的：主尺、第一测量杆和第二测量杆,主尺位于第一测量杆和第二测量杆之间,第一测量杆的测量端和第二测量杆的测量端相对于标尺的距离相同；该检测方法简便有效,降低了检测难度,方便操作,提高了检测效率,节省检测成本,适用性强,检测装置体积较小,方便携带,具有较强的实用性和可操作性。(The invention discloses a method and a device for rapidly detecting the large radius of an airplane part, wherein the method comprises the steps of S1, selecting three points in a region to be detected on the surface of the airplane part; s2, ensuring that the plane where the three points are located is perpendicular to the area to be measured, and meanwhile, forming an isosceles triangle by the three points; s3, measuring at least two of the first distance, the second distance and the third distance; s4, constructing a right triangle, and establishing an equality relation by using a trigonometric function and/or a pythagorean theorem to obtain the radius of the area to be measured; the device comprises a scale and is connected to the scale: the main ruler is positioned between the first measuring rod and the second measuring rod, and the distances between the measuring end of the first measuring rod and the measuring end of the second measuring rod relative to the ruler are the same; the detection method is simple, convenient and effective, reduces the detection difficulty, is convenient to operate, improves the detection efficiency, saves the detection cost, has strong applicability, has smaller volume of the detection device, is convenient to carry, and has stronger practicability and operability.)

1. A method for rapidly detecting the large radius of an airplane part is characterized by comprising the following steps:

s1, selecting three points in the area to be measured on the surface of the airplane part, wherein the selected point in the middle position is a reference point, and the selected points on the two sides of the reference point are a first measuring point and a second measuring point respectively;

s2, ensuring that the plane where the three points of the reference point, the first measuring point and the second measuring point are located is perpendicular to the area to be measured, and simultaneously ensuring that the reference point, the first measuring point and the second measuring point form an isosceles triangle, wherein the reference point is the vertex of the isosceles triangle;

s3, setting a straight line where the first measuring point and the second measuring point are located as l, setting the distance between the reference point and the straight line as a first distance, the distance between the first measuring point and the second measuring point as a second distance, setting the distance between the reference point and the first measuring point or the second measuring point as a third distance, and measuring at least two of the first distance, the second distance and the third distance;

s4, constructing a right triangle by at least two of the first distance, the second distance and the third distance and the radius of the area to be measured, and establishing an equation relation by using a trigonometric function and/or a pythagorean theorem to obtain the radius of the area to be measured.

2. The method for rapidly detecting the large radius of the airplane part according to claim 1, wherein in the step S4, when the first distance and the second distance are measured, an equation relationship is established to obtain the radius of the area to be measured as:

wherein R is the radius of the region to be measured on the surface of the aircraft part, a is the first distance, and b is half of the second distance.

3. The method for rapidly detecting the large radius of the airplane part according to claim 1, wherein in the step S4, when the second distance and the third distance are measured, an equation relationship is established to obtain the radius of the area to be detected as:

wherein R is the radius of the region to be measured on the surface of the aircraft part, b is half of the second distance, and c is the third distance.

4. The method for rapidly detecting the large radius of the airplane part according to claim 1, wherein in the step S4, when the first distance and the third distance are measured, an equation relationship is established to obtain the radius of the area to be measured as:

wherein R is the radius of the region to be measured on the surface of the aircraft part, a is a first distance, and c is a third distance.

5. The method for rapidly detecting the large radius of an aircraft part according to any one of claims 2 to 4, wherein in the step S4, when three distances of the first distance, the second distance and the third distance are measured simultaneously, the radius of the region to be detected is obtained through any two distances.

6. A method for rapid inspection of a large radius of an aircraft part according to any one of claims 1 to 4 wherein the surface of the aircraft part is convex with a large radius R or concave with a large radius R, the large radius R ranging from R to greater than 25 mm.

7. An apparatus for rapidly inspecting a large radius of an aircraft part, which can be used in the method for rapidly inspecting a large radius of an aircraft part according to any one of claims 1 to 6, wherein the apparatus comprises a scale, and connected to the scale: the main ruler is positioned between the first measuring rod and the second measuring rod, and the distance between the measuring end of the first measuring rod and the measuring end of the second measuring rod relative to the scale is the same; the distance between the measuring end of the main ruler and the scale can be adjusted, and/or the distance between the measuring end of the first measuring rod and the measuring end of the second measuring rod and the scale can be adjusted.

8. The device for rapidly detecting the large radius of an aircraft part according to claim 7, wherein the scale is provided with a slide rail, the first measuring rod and the second measuring rod are respectively connected to the slide rail, and the first measuring rod and the second measuring rod adjust the second distance or the third distance through the slide rail.

9. The device for rapidly detecting the large radius of an airplane part according to claim 7, wherein at least two of the first measuring rod, the scale and the main ruler are provided with scales, and the scales of the second measuring rod are arranged the same as those of the first measuring rod; or at least one of the first measuring rod, the second measuring rod and the main ruler is provided with a displacement sensor, the displacement sensor is electrically connected with a digital display, and the digital display is arranged on the ruler.

10. The device for rapidly detecting the large radius of the airplane part according to claim 7, wherein the measuring end of the first measuring rod, the measuring end of the second measuring rod and the measuring end of the main scale are respectively embedded with a contact ball, and the contact ball can freely rotate relative to the measuring ends.

Technical Field

The invention relates to the technical field of airplane part detection, in particular to a method and a device for rapidly detecting the large radius of an airplane part.

Background

Because the requirement of an aviation part assembly structure requires that a large radius R larger than R25 is adopted to smoothly transition part structure parts, reduce stress concentration, meet assembly function requirements and the like, the large radius R larger than R25 is widely applied to various structural parts, so that a plurality of aviation part structure parts have the parts with the large radius R larger than R25. The part with the large radius R larger than R25 has various structural styles, the size and the position of the large radius R larger than R25 are various, and the maximum R gauge value of the conventional gauge such as the R gauge used for mass field production inspection is R25, so that the large radius R larger than R25 of the part cannot be inspected by the conventional gauge such as the R gauge.

At present, the large radius R detection mode larger than R25 in mass field production only uses a three-coordinate measuring machine, the three-coordinate measuring machine is generally fixed on the ground and cannot be moved, a worker needs to move a part to the measuring machine for measurement during detection, and the detection is very inconvenient, the number of three-coordinate measuring machines used in field production is limited, the waiting time of each part for detection is long, in addition, the operation of the three-coordinate measuring machine is inconvenient, and the detection is slow, so that the three-coordinate measuring machine is used for detecting the large radius R larger than R25, the detection is inconvenient, the detection efficiency is low, the detection cost is high, and the requirements of mass and high-efficiency field production cannot be met.

Disclosure of Invention

The invention aims to overcome the defects of inconvenient operation and low detection efficiency of the detection in the prior art, and provides a method and a device for quickly detecting the large radius of an airplane part.

In order to achieve the above purpose, the invention provides the following technical scheme:

a method for rapidly detecting the large radius of an airplane part comprises the following steps:

s1, selecting three points in the area to be measured on the surface of the airplane part, wherein the selected point in the middle position is a reference point, and the selected points on the two sides of the reference point are a first measuring point and a second measuring point respectively;

s2, ensuring that the plane where the three points of the reference point, the first measuring point and the second measuring point are located is perpendicular to the area to be measured, and simultaneously ensuring that the reference point, the first measuring point and the second measuring point form an isosceles triangle, wherein the reference point is the vertex of the isosceles triangle;

s3, setting a straight line where the first measuring point and the second measuring point are located as l, setting the distance between the reference point and the straight line as a first distance, the distance between the first measuring point and the second measuring point as a second distance, setting the distance between the reference point and the first measuring point or the second measuring point as a third distance, and measuring at least two of the first distance, the second distance and the third distance;

s4, constructing a right triangle by at least two of the first distance, the second distance and the third distance and the radius of the area to be measured, and establishing an equation relation by using a trigonometric function and/or a pythagorean theorem to obtain the radius of the area to be measured.

The three points are selected on the surface of the airplane part, so that the detection process is simplified, the detection is convenient, the position relation of the three points is limited, the basis for constructing the trigonometric function is provided, the measurement is carried out again, a ruler marked with scales can be used for measuring, the measurement can also be carried out by means of tool assistance, the operability is strong, the radius of the area to be detected of the airplane part is directly calculated by utilizing the trigonometric function and/or the pythagorean theorem, the final detection result is directly obtained, and the detection efficiency is high.

In a preferred embodiment of the present invention, in step S4, when the first distance and the second distance are measured, an equation relationship is established, and the radius of the region to be measured is obtained as:

wherein R is the radius of a region to be measured on the surface of the aircraft part, a is a first distance, and b is half of a second distance; the radius of the area to be detected of the airplane part is directly obtained through a formula relation by selecting two distances of the first distance and the second distance for measurement, and the detection is rapid and efficient.

In a preferred embodiment of the present invention, in the step S4, when the second distance and the third distance are measured, an equation relationship is established, and the radius of the region to be measured is obtained as:

wherein R is the radius of the area to be measured on the surface of the aircraft part, b is half of the second distance, and c is the third distance; the radius of the area to be detected of the airplane part is directly obtained through a formula relation by selecting two distances of the second distance and the third distance for measurement, and the detection is rapid and efficient.

In a preferred embodiment of the present invention, in step S4, when the first distance and the third distance are measured, an equation relationship is established, and the radius of the region to be measured is obtained as:

wherein R is the radius of a region to be measured on the surface of the aircraft part, a is a first distance, and c is a third distance; the radius of the area to be detected of the airplane part is directly obtained through a formula relation by selecting two distances of the first distance and the third distance for measurement, and the detection is rapid and efficient.

In a preferred embodiment of the present invention, in step S4, when three distances, namely, the first distance, the second distance and the third distance, are measured simultaneously, the radius of the region to be measured is obtained according to any two distances; when three distances are measured, two distances can be selected as parameters, the radius of the area to be measured of the airplane part is directly obtained through a formula relation, the detection is rapid, and the efficiency is high.

In a preferred embodiment of the present invention, the surface of the aircraft component is a convex surface with a large radius R or a concave surface with a large radius R, wherein R is greater than 25 mm; the detection method can be used for both the convex surface and the concave surface of the airplane part, three points can be selected on the convex surface for measurement, three points can also be selected on the concave surface for measurement, the applicability is strong, and the detection method aims at the airplane part with the large radius R larger than 25mm for measurement, so that the detection requirement of the airplane part with the large radius is met.

The device for rapidly detecting the large radius of the airplane part can be used for the method for rapidly detecting the large radius of the airplane part, and comprises a scale and a sensor connected to the scale, wherein the sensor comprises: the main ruler is positioned between the first measuring rod and the second measuring rod, and the distances between the measuring end of the first measuring rod and the measuring end of the second measuring rod relative to the ruler are the same; the distance between the measuring end of the main ruler and the scale can be adjusted, and/or the distance between the measuring end of the first measuring rod and the measuring end of the second measuring rod and the scale can be adjusted; the measuring end of the main ruler is used for measuring a datum point, the measuring end of the first measuring rod is used for measuring a first measuring point, the measuring end of the second measuring rod is used for measuring a second measuring point, three points on the surface of the aircraft part can be selected and positioned through the main ruler, the first measuring rod and the second measuring rod, the detection method is convenient to use for measurement, the position relation of the three points is limited through the position arrangement of the main ruler, the first measuring rod and the second measuring rod, the three points in the detection method are directly positioned, position adjustment is carried out through at least one of the main ruler, the first measuring rod and the second measuring rod, different three point positions are convenient to select, and the application range is wide.

In a preferred embodiment of the present invention, the scale is provided with a slide rail, the first measuring rod and the second measuring rod are respectively connected to the slide rail, and the first measuring rod and the second measuring rod adjust the second distance or the third distance through the slide rail; through setting up the slide rail, first measuring stick and second measuring stick slidable adjusting position adjust second distance, third distance, conveniently fix a position first measurement station and second measurement station promptly.

In a preferred embodiment of the present invention, at least two of the first measuring rod, the scale and the main ruler are provided with scales, and the scales of the second measuring rod are the same as those of the first measuring rod; or at least one of the first measuring rod, the second measuring rod and the main ruler is provided with a displacement sensor, the displacement sensor is electrically connected with a digital display, and the digital display is arranged on the ruler; the method can adopt an original scale reading mode to measure, has strong realizability, is easy to realize and operate, can also adopt a digital display mode to measure, determines three-point positions through a displacement sensor, displays the three-point positions through a digital display, conveniently reads, improves the precision and reduces errors.

In a preferred embodiment of the present invention, the measuring end of the first measuring rod, the measuring end of the second measuring rod, and the measuring end of the main scale are respectively embedded with a contact ball, and the contact ball can rotate freely relative to the measuring ends; through the contact ball, reduce detection device and aircraft part surperficial friction, avoid taking place wearing and tearing, let the measuring end of main scale, first measuring stick and second measuring stick remove more smoothly on the surface of aircraft part.

Compared with the prior art, the invention has the beneficial effects that:

1. according to the detection method, three points are selected on the surface of the airplane part and then the measurement is carried out, so that the detection process is simplified, the detection is convenient, the operability is strong, the detection is fast, only two numerical values are read, finally, the radius of the area to be detected of the airplane part is directly calculated by utilizing a trigonometric function and/or a pythagorean theorem, the final detection result is directly obtained, and the detection efficiency is high.

2. The method can meet the requirements of airplane parts with different sizes, different positions and different types, is suitable for detecting the airplane parts with the large radius R larger than 25mm, fills the large radius R detection method for quickly and accurately detecting the airplane parts, and overcomes the technical problem of the current detection.

3. According to the detection device, three points on the surface of the airplane part can be selected and positioned through the main scale, the first measuring rod and the second measuring rod, the detection is fast, the three measuring ends of the detection device are directly attached to the surface of the airplane part, the value can be measured, the detection method is convenient to use for measurement, different three point positions and positioning of the surface of the airplane part are convenient to select, and the application range is wide.

Description of the drawings:

FIG. 1 is a method for rapidly detecting a large radius of an aircraft part according to embodiment 1 of the present invention;

FIG. 2 is a detection schematic diagram of embodiment 1 of the present invention;

FIG. 3 is a detection schematic diagram of embodiment 2 of the present invention;

FIG. 4 is a detection schematic diagram of embodiment 3 of the present invention;

FIG. 5 is a schematic view of a detecting device according to embodiment 4 of the present invention;

FIG. 6 is a partial schematic view of a detecting device according to embodiment 4 of the present invention;

FIG. 7 is a schematic view of the detecting device of embodiment 4 of the present invention;

FIG. 8 is a schematic view of a detecting device according to embodiment 5 of the present invention;

fig. 9 is a schematic view of a detection apparatus according to embodiment 6 of the present invention.

The labels in the figure are: 1-datum point; 2-a first measurement point; 3-a second measuring point; 4-aircraft parts; 5-a scale; 5.1-sliding rail; 6-main ruler; 7-a first measuring bar; 7.1-main pole; 7.2-telescopic rod; 8-a second measuring rod; 9-contact ball; 10-digital display.

Detailed Description

The present invention will be described in further detail with reference to test examples and specific embodiments. It should be understood that the scope of the above-described subject matter is not limited to the following examples, and any techniques implemented based on the disclosure of the present invention are within the scope of the present invention.

Example 1

Referring to fig. 1, the present embodiment provides a method for rapidly detecting a large radius of an aircraft part, which measures a surface of an "R-convex" large radius aircraft part 4, and includes the following steps:

s1, selecting the aircraft part 4 with a convex surface with a large radius R for measurement, wherein the range of the large radius R is R >25mm, the radius of a region to be measured on the surface of the aircraft part 4 in the embodiment is 80 +/-0.5 mm, the region to be measured is a part of the surface of the aircraft part 4 on the same circumferential surface and is also a position to be detected, points of the region to be measured on the surface of the aircraft part 4 are required to be positioned on the circumferential surface, three points are selected on the region to be measured on the surface of the aircraft part 4, the selected point at the middle position is a reference point 1, the selected points at two sides of the reference point 1 are respectively a first measuring point 2 and a second measuring point 3, the step can be divided into two steps, one point is selected as the reference point 1 in the region to be measured on the surface of the aircraft part 4 in the first step, the first measuring point 2 and the second measuring point 3 are selected in the region to be measured on the surface of the aircraft part 4 in the second step, so that the first measuring point 2 and the second measuring point 3 are respectively positioned at two sides of the reference point 1, the sequence of the two steps can be interchanged, the first step during the interchange is to select the first measuring point 2 and the second measuring point 3, and the second step is to select the reference point 1 between the first measuring point 2 and the second measuring point 3.

S2, ensuring that planes of three points of a reference point 1, a first measuring point 2 and a second measuring point 3 are vertical to a region to be measured, ensuring that the reference point 1, the first measuring point 2 and the second measuring point 3 are simultaneously positioned on the same circumference of the region to be measured, ensuring that the planes of the three points pass through the circle center of the circumference of the region to be measured, ensuring that the reference point 1, the first measuring point 2 and the second measuring point 3 form an isosceles triangle, ensuring that the reference point 1, the first measuring point 2 and the second measuring point 3 form a plane determined by the three points, wherein the plane is required to be vertical to the region to be measured, if the plane is not vertical, the position of the first measuring point 2 and the position of the second measuring point 3 are deviated, and the large radius R calculated in the subsequent step has errors, so that the vertical relation between the plane and the region to be measured on the surface of the airplane part 4 is ensured, it should be noted that, the vertical relationship means approximately vertical, and there may be a certain error, for example, the error is less than or equal to 1 °, when the error is approximately vertical, the vertical also belongs to the vertical of the present invention, and the triangle formed by the reference point 1, the first measuring point 2 and the second measuring point 3 is an isosceles triangle, so that the distance from the reference point 1 to the first measuring point 2 and the second measuring point 3 is the same, the isosceles triangle is also an approximate isosceles triangle, a certain error is allowed, and there may be a certain error when two third distances are measured, but because of the approximate isosceles triangle, there is an error.

S3, simplifying the calculation process by establishing coordinates and constructing a model, measuring three points, and using a ruler with scales or a tool to assist in measurement, wherein the embodiment adopts the mode of constructing the model, the measurement is carried out by using the ruler, the straight line of the first measuring point 2 and the second measuring point 3 is l, the distance between the reference point 1 and the straight line l can be measured, namely, the perpendicular line of the straight line l is drawn through the reference point 1, the length of the perpendicular line is the distance, the distance between the reference point 1 and the straight line l is a first distance, the distance between the first measuring point 2 and the second measuring point 3 is also obtained, the distance between the first measuring point 2 and the second measuring point 3 is a second distance, the distance between the reference point 1 and the first measuring point 2 or the second measuring point 3 is also obtained, at least two of the first distance, the second distance and the third distance are measured, and the calculation can be carried out through the two distances, two third distances are provided, namely two sides of the isosceles triangle, certain errors may exist during measurement, but the errors of the two distances are small and can be ignored due to the isosceles triangle; when three distances of the first distance, the second distance and the third distance are measured simultaneously, two optional distances are used as parameters, the radius of the area to be measured of the airplane part 4 is directly obtained through a formula relation through any two distances, and the detection is rapid and efficient.

S4, constructing a right triangle by the first distance, the second distance and the radius of the area to be measured, and establishing an equation relation by using a trigonometric function and/or a pythagorean theorem to obtain the radius of the area to be measured.

Defining a first distance as a parameter a, defining a half of a second distance as a parameter b, defining a third distance as a parameter c, positioning an angle formed by a reference point 1, a first measuring point 2 and a second measuring point 3 as an angle theta, positioning a radius of a region to be measured as R, and defining a distance from another point opposite to the reference point 1 to the first measuring point 2 or the second measuring point 3 on a circle where the three points of the reference point 1, the first measuring point 2 and the second measuring point 3 are located as a parameter d, referring to FIG. 2, the first distance and the second distance are measured to construct a measured model, wherein a triangle formed by a, b and c is a right-angled triangle;

through the Pythagorean theorem relationship, it can be known that:

a²+b²＝c² (1)

and by the trigonometric function relation, it can be known that:

therefore, the first and second electrodes are formed on the substrate,angle theta isAnd because the triangle formed by c, d and 2R is also a right-angle triangle, the relation is established through a trigonometric function:

the equations (1), (2) and (3) are combined to establish an equation relation, and the radius of the region to be measured on the surface of the airplane part 4 is obtained as follows:

wherein R is the radius of the area to be measured on the surface of the aircraft part 4, a is the first distance between the datum point 1 and a straight line l, the straight line l is the straight line where the first measuring point 2 and the second measuring point 3 are located, and b is half of the second distance between the first measuring point 2 and the second measuring point 3.

And (3) comparing the actual value of the radius R calculated by the formula (4) with the theoretical value of the radius R designed by a factory, and easily judging whether the radius R is qualified.

This embodiment is through selecting three points on aircraft part 4 surface, the flow of detection has been simplified, convenient detection, position relation through injecing three points, the basis of the trigonometric function of having provided the structure, measure again, only measure through selecting two distances of first distance and second distance, can use the ruler marked with scale to measure during the measurement, also can utilize the instrument to assist and measure, maneuverability is strong, utilize trigonometric function and/or collude the thigh theorem at last, establish the formula relation, directly calculate the radius of the region to be measured of aircraft part 4, directly obtain final testing result, the detection efficiency is high.

Example 2

The present embodiment provides a method for rapidly inspecting a large radius of an aircraft part, and is substantially the same as the steps S1-S3 of embodiment 1 except that the present embodiment performs the measurement on the surface of the aircraft part 4 with a large radius of "concave R" in step S4.

S4, constructing a right triangle by the second distance, the third distance and the radius of the area to be measured, and establishing an equation relation by using a trigonometric function and/or a pythagorean theorem to obtain the radius of the area to be measured.

Referring to fig. 3, in the present embodiment, the definition of each parameter is the same as that in embodiment 1, and in the present embodiment, a second distance b and a third distance c are measured to construct a measurement model, where a triangle formed by a, b, and c is a right triangle;

through the Pythagorean theorem relationship, it can be known that:

a²+b²＝c² (5)

and by the trigonometric function relation, it can be known that:

therefore, the angle θ isAnd because the triangle formed by c, d and 2R is also a right-angle triangle, the relation is established through a trigonometric function:

the equations (5), (6) and (7) are combined to establish an equation relation, and the radius of the region to be measured on the surface of the aircraft part 4 is obtained as follows:

wherein R is the radius of a region to be measured on the surface of the aircraft part 4, b is half of a second distance between the first measuring point 2 and the second measuring point 3, and c is the distance between the datum point 1 and the first measuring point 2 or the distance between the datum point 1 and the second measuring point 3; the three points are selected on the surface of the airplane part 4, the detection process is simplified, the detection is convenient, the position relation of the three points is limited, the basis for constructing the trigonometric function is provided, the measurement is carried out again, the measurement is carried out only by selecting two distances of the second distance and the third distance, a ruler marked with scales can be used for measurement during the measurement, the measurement can also be carried out by using the aid of tools, the operability is strong, finally, the trigonometric function and/or the pythagorean theorem are used for establishing the formula relation, the radius of the area to be detected of the airplane part 4 is directly calculated, the final detection result is directly obtained, and the detection efficiency is high.

Example 3

The embodiment provides a method for rapidly detecting the large radius of an aircraft part, the embodiment is substantially the same as the steps S1-S3 of the embodiment 1, the definition of each parameter in the embodiment is also the same as the embodiment 1, the difference is that the embodiment detects the region to be detected on the surface of the aircraft part 4 with the large radius of the convex R, the embodiment simplifies the calculation process by establishing coordinates, and the difference is the step S4.

In step S3, a rectangular coordinate system of XOY is established with reference point 1 as origin O, where the diameter direction passing through origin O on the circumference where reference point 1, first measuring point 2, and second measuring point 3 are located is set as Y axis, and the direction along the side of second measuring point 3 is set as X axis, the coordinate of reference point 1 is O (0, 0), the coordinate of first measuring point 2 is a (-B, a), the coordinate of second measuring point 3 is B (B, a), the dot coordinate of the circumference where the region to be measured is located is O' (0, R), and the dot coordinate of the top end of the circumference is C (0, 2R).

In step S4, a right triangle is constructed from the first distance, the third distance, and the radius of the area to be measured, and an equality relationship is established using a trigonometric function and/or pythagorean theorem to obtain the radius of the area to be measured.

Referring to fig. 4, a triangle is formed by the reference point 1O, the first measuring point 2A and the vertical point D of the first measuring point 2 on the Y axis, and a triangle is formed by the point C at the top end of the circumference, the first measuring point 2A and the reference point 1O, and both triangles are right-angled triangles;

by the trigonometric function relationship, the equality relationship of similar triangles is established, and the following can be known:

calculating the lengths of OD, OA and OC according to the coordinates of each point, and substituting the lengths into the formula (9) to obtain

Obtaining the radius of the area to be measured as:

wherein R is the radius of the region to be measured on the surface of the aircraft part 4, a is the length of OD, and c is the length of OA.

It should be noted that the method for rapidly detecting the large radius of the aircraft part of the present invention can also be used for measuring the situation that the region to be measured on the surface of the aircraft part 4 is located on the same spherical surface, the step method is the same as that in the embodiment 1-embodiment 3, that is, a reference point 1, a first measuring point 2 and a second measuring point 3 are found on the spherical surface, the three points are located on the same plane, meanwhile, the plane where the three points are located passes through the sphere center of the spherical surface, the three points form an isosceles triangle, the reference point 1 is the vertex of the isosceles triangle, the parameters in the embodiments 1-embodiment 2 are measured, and the parameters can be obtained through the same calculation method.

Example 4

Referring to fig. 5, the present embodiment provides a device for rapidly detecting a large radius of an aircraft part, which can be used in the method for rapidly detecting a large radius of an aircraft part according to any one of embodiments 1 to 3, the device includes a scale 5, a main scale 6, a first measuring rod 7, a second measuring rod 8, a digital display 10, and a contact ball 9, the main scale 6, the first measuring rod 7, and the second measuring rod 8 are respectively connected to the scale 5, the main scale 6 is movable along an extending direction of the main scale 6 relative to the scale 5, the first measuring rod 7 and the second measuring rod 8 are slidable along an edge direction of the scale 5 relative to the scale 5, the edge of the scale 5 is an edge at which a connection point between the main scale 6 and the first measuring rod 7 and the second measuring rod 8 is located, in the present embodiment, the extending direction of the main scale 6 is perpendicular to the edge direction of the scale 5, in an actual product, the two directions may also be in a non-perpendicular relationship, namely, the main ruler 6, the first measuring rod 7 and the second measuring rod 8 can be intersected with the scale 6 to form an acute angle, the main ruler 6 is positioned between the first measuring rod 7 and the second measuring rod 8, the digital display 10 is arranged on the scale 5, the measuring ends of the main ruler 6, the first measuring rod 7 and the second measuring rod 8 are respectively provided with a contact ball 9, the measuring ends refer to one ends of the main ruler 6, the first measuring rod 7 and the second measuring rod 8, the ends are separated from the scale 5 by a distance, the measuring end of the main ruler 6 is used for measuring the reference point 1, the measuring end of the first measuring rod 7 is used for measuring the first measuring point 2, and the measuring end of the second measuring rod 8 is used for measuring the second measuring point 3; three points on the surface of the airplane part 4 can be selected and positioned through the main ruler 6, the first measuring rod 7 and the second measuring rod 8, the detection method of the embodiment 1-3 is convenient to use for measurement, the position relation of the three points is limited through the position arrangement of the main ruler 6, the first measuring rod 7 and the second measuring rod 8, the three points in the detection method are directly positioned, the position adjustment is carried out through the main ruler 6, different three point positions are convenient to select, and the application range is wide.

Referring to fig. 6, a through groove penetrating through both sides is formed in the middle of the scale 5, and the main scale 6 is disposed in the through groove, such that the main scale 6 is slidable with respect to the scale 5, and further, a distance between the measuring end of the main scale 6 and the scale 5 is adjusted, the measuring end of the main scale 6, the measuring end of the first measuring rod 7, and the measuring end of the second measuring rod 8 are all located at the same side of the scale 5, the side edge of the scale 5 is provided with a slide rail 5.1, the slide rails 5.1 are respectively located at both sides of the main scale 6, the slide rail 5.1 has a slide groove, one end of the first measuring rod 7 is provided with a slide block matching with the slide groove, one end of the second measuring rod 8 is also provided with a slide block matching with the slide groove, and both slide blocks are disposed in the slide groove, such that the first measuring rod 7 and the second measuring rod 8 are respectively vertically connected at the edge of the scale 5 through the slide block, the first measuring rod 7 and the second measuring rod 8 are slidable with respect to the scale 5, when the first measuring rod 7 and the second measuring rod 8 slide, the first measuring rod 7 and the second measuring rod 8 are kept synchronous, namely the first measuring rod 7 and the second measuring rod 8 are close to or separated from each other, in the synchronous moving process, the distance between the measuring end of the first measuring rod 7 and the measuring end of the second measuring rod 8 relative to the scale 5 is always kept the same, namely the distance between the measuring end of the first measuring rod 7 and the scale 5 is the same as the distance between the measuring end of the second measuring rod 8 and the scale 5, the first measuring rod 7 and the second measuring rod 8 adjust the second distance through the sliding rail 5.1, and meanwhile, the third distance is also adjusted, so that the first measuring point 2 and the second measuring point 3 are conveniently positioned; and the measuring end of main scale 6, the measuring end of first measuring stick 7 and the measuring end of second measuring stick 8 are equipped with similar spherical recess respectively in the concave, and the embedding sets up contact ball 9 in each recess, and contact ball 9 can rotate wantonly for the measuring end, through contact ball 9, reduces the friction on detection device and aircraft part 4 surface, avoids taking place wearing and tearing, lets the measuring end of main scale 6, first measuring stick 7 and second measuring stick 8 remove more in the smooth way on aircraft part 4's surface.

The main scale 6, the first measuring rod 7 and the second measuring rod 8 are respectively internally provided with a displacement sensor, the main scale 6 is internally provided with a grating displacement sensor, the first measuring rod 7 and the second measuring rod 8 are respectively internally provided with a capacitive grating displacement sensor, the displacement sensors are electrically connected with a digital display 10, the digital display 10 is installed on the scale 5, after the installation, the digital display 10 just seals part of the main scale 6 in a through groove of the scale 5 and is fixed by screws, the digital display 10 adopts a grating, a capacitive grating and other measuring systems for calculation and integration, can directly display the measured value, adopts a digital display mode for measurement, determines the three-point position by the displacement sensor, the digital display 10 is internally provided with a program for calculating the half b and the third distance c of the first distance a and the second distance, and the calculation formulas in the embodiments 1-3 are arranged in the program, and the numerical value measured by the displacement sensor is converted into a calculation formula of the first distance, the second distance and the third distance, so that the final result radius R can be directly displayed through the digital display 10, the reading is convenient, the precision is improved, and the error is reduced.

Referring to fig. 7, in the embodiment, the first measuring rod 7 and the second measuring rod 8 slide back and forth relative to the edge of the scale 5, and the main scale 6 slides relative to the scale 5, so that the relative positions of the measuring ends of the main scale 6, the first measuring rod 7 and the second measuring rod 8 are changed, and the numerical values of the large radii R with different sizes and different types can be measured; according to the difference of the relative positions, the detection device has three different states for measurement, namely a 'return-to-zero' state, a 'concave R' state and a 'convex R' state, the different states can detect different types of large radiuses R, the large radius R of the concave surface of the aircraft part 4 can be detected in the "concave R" state, in which the distance between the measuring end of the main scale 6 and the scale 5 > the distance between the measuring ends of the first measuring rod 7 and the second measuring rod 8 and the scale 5, and the large radius R of the convex surface of the aircraft part 4 can be detected in the "convex R" state, in which the distance between the measuring end of the main scale 6 and the scale 5 < the distance between the measuring ends of the first measuring rod 7 and the second measuring rod 8 and the scale 5, and is reset to the "return-to-zero" state when not detected, in which the distance between the measuring end of the main scale 6 and the scale 5 is equal to the distance between the measuring ends of the first measuring rod 7 and the second measuring rod 8 and the scale 5.

When the detection device is used, the detection device is adjusted according to the to-be-detected areas on the surfaces of different airplane parts 4, when the large-radius concave surface of the to-be-detected area is formed, the detection device slides to be in a concave R state, contact balls 9 at the measuring ends of a main ruler 6, a first measuring rod 7 and a second measuring rod 8 are completely attached to the concave R surface, and after complete attachment is guaranteed, the numerical value of a digital display 10 on a ruler 5 is directly read, wherein the numerical value is the radius of the to-be-detected area on the surface of the airplane part 4; when the large-radius convex surface of the area to be measured is formed, the detection device slides to be in a convex R state, contact balls 9 at the measuring ends of the main ruler 6, the first measuring rod 7 and the second measuring rod 8 are completely attached to the convex R surface of the airplane part 4, and after complete attachment is guaranteed, the numerical value of a digital display 10 on the scale 5 is directly read, wherein the numerical value is the radius of the area to be measured on the surface of the airplane part 4; because the areas to be measured on the surface of the aircraft part 4 are on the same circumference or the same spherical surface, and the large radiuses of the areas to be measured are different, the positions of the main scale 6, the first measuring rod 7 and the second measuring rod 8 need to be adjusted, so that the contact balls 9 at the measuring end of the main scale 6, the measuring end of the first measuring rod 7 and the measuring end of the second measuring rod 8 are respectively tightly attached to the areas to be measured on the surface of the aircraft part 4, and then the numerical value size on the digital display 10 is read, so that whether the areas to be measured of the aircraft part 4 meet the requirements can be judged according to the requirements of the relevant technical files of the aircraft part 4, and if the areas to be measured meet the requirements, the areas to be measured of the aircraft part 4 are judged to be qualified; if the requirement is not met, the test is judged to be unqualified.

Example 5

Referring to fig. 8, the present embodiment is substantially the same as embodiment 4, except that the positions of the first measuring stick 7 and the second measuring stick 8 of the present embodiment are fixed.

In this embodiment, the second distance is fixed when the detection device leaves the factory, the radius R of the region to be measured on the surface of the aircraft part 4 can be obtained only by measuring the first distance or the third distance, the displacement sensor is arranged in the main scale 6, and the position of the main scale 6 is sensed by the displacement sensor, so that the first distance or the third distance is obtained; the scale 5 of this embodiment does not have the slide rail 5.1, and the first measuring stick 7 and the second measuring stick 8 are all fixed at the side of the scale 5, and the measuring ends of the first measuring stick 7, the second measuring stick 8 and the main scale 6 are located on the same side of the scale 5, and the main scale 6 is also located between the first measuring stick 7 and the second measuring stick 8, and other settings and connection relations are the same as those of embodiment 4.

During measurement, the contact balls 9 of the first measuring rod 7 and the second measuring rod 8 are firstly attached to a region to be measured on the surface of the airplane part 4, and only the telescopic position of the main scale 6 relative to the scale 5 needs to be adjusted, so that the contact balls 9 of the main scale 6 are attached to the region to be measured on the surface of the airplane part 4 to form three-point attachment, and then the degree is measured through the digital display 10; and when the 'concave R' state, the 'convex R' state and the 'return-to-zero' state of the detection device are adjusted, the adjustment can be realized only by adjusting the position of the main scale 6 relative to the scale 5.

Example 6

Referring to fig. 9, the present embodiment provides a device for rapidly detecting a large radius of an aircraft part, which is simplified on the basis of embodiments 4 and 5, and the device includes a scale 5, and connected to the scale 5: the main ruler 6 is positioned between the first measuring rod 7 and the second measuring rod 8, one end of the main ruler 6 extends out of the scale 5, the main ruler 6 is perpendicular to one side edge of the scale 5, the main ruler 6 and the scale 5 are fixed through screws, the side edge of the scale 5 is provided with a sliding rail 5.1, the sliding rail 5.1 is respectively positioned at two sides of the main ruler 6, the sliding rail 5.1 is provided with a sliding groove, one end of the first measuring rod 7 is provided with a sliding block matched with the sliding groove, one end of the second measuring rod 8 is also provided with a sliding block matched with the sliding groove, the two sliding blocks are both arranged in the sliding groove, thus, the first measuring rod 7 and the second measuring rod 8 are respectively and vertically connected at the edge of the scale 5 through the sliding block, the first measuring rod 7 and the second measuring rod 8 can slide relative to the scale 5, the second distance and the third distance can be adjusted through the sliding rail 5.1, the first measuring point 2 and the second measuring point 3 can be conveniently positioned, when the first measuring rod 7 and the second measuring rod 8 slide, the first measuring rod 7 and the second measuring rod 8 keep synchronous, namely, are close to or separated from each other at the same time, the distance between the measuring end of the first measuring rod 7 and the measuring end of the second measuring rod 8 relative to the scale 5 always keeps the same, and the distance is adjusted in a telescopic mode.

The first measuring rod 7 and the second measuring rod 8 are of the same structure, and will be described below by the first measuring rod 7, the first measuring rod 7 further includes a main rod 7.1 and a telescopic rod 7.2, wherein one end of the main rod 7.1 is fixed with the slider as a whole, the end surface of the other end of the main rod 7.1 is provided with a jack inward along the main rod 7.1 direction, and the measuring end of the telescopic rod 7.2 is inserted into the jack and matched with the main rod 7.1, so that the telescopic rod 7.2 and the main rod 7.1 adjust the length of the first measuring rod 7 in a telescopic manner, when the lengths of the telescopic rod 7.2 and the main rod 7.1 are extended to a middle length position, the detection device is in a "return to zero" state, at this time, the measuring end of the telescopic rod 7.2 of the first measuring rod 7, the measuring end of the telescopic rod 7.2 of the second measuring rod 8 and the measuring end of the main rod 7.1 are located on the same straight line, and the telescopic rod 7.2 and the main rod 7.1 adjust the length to the shortest, the limit position of the detection device in a "concave R" state ", when the length of the telescopic rod 7.2 and the main rod 7.1 is adjusted to be longest, the detection device is at the limit position of a convex R state, and the length of the telescopic rod 7.2 and the length of the main rod 7.1 are adjusted, so that the detection device can adapt to concave R surfaces or convex R surfaces on the surfaces of different airplane parts 4.

The scales are arranged on the first measuring rod 7, the second measuring rod 8 and the scale 5, and the scales can be arranged on at least two of the first measuring rod 7, the scale 5 and the main scale 6, the scales of the second measuring rod 2 are arranged the same as the scales of the first measuring rod 7, in this embodiment, only one of the scales is arranged, the scale is arranged on the edge of one side of the slide rail 5.1 of the scale 5, the scales are arranged on the telescopic rods 7.2 of the first measuring rod 7 and the second measuring rod 8, the distance between the first measuring rod 7 and the second measuring rod 8 can be read through the scales of the scale 5, the projected distance between the measuring ends of the first measuring rod 7 and the second measuring rod 8 and the measuring end of the main scale 6 along the direction can be read through the scales on the telescopic rod 7.2, namely, the vertical distance can be also read, the measurement is carried out by adopting the original scale reading mode, the practicability is strong, and the operation is easy to realize, and then, calculating by the formulas in the embodiments 1 to 3 to finally obtain the radius of the region to be measured of the surface of the aircraft part 4.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.