Control surface zero position measuring device

Abstract

The utility model discloses a control surface zero position measuring device, which relates to the technical field of unmanned aerial vehicle production and comprises a plurality of measuring clamping plates used for contacting with a wing surface, the measuring clamping plates are arranged along the transverse direction of a to-be-measured wing, and the curvature of the inner surface of each measuring clamping plate is measured. The curvature of the designed wing surface is the same as the curvature of the designed wing surface of the to-be-measured wing at the corresponding to-be-measured transverse position; a first reference point, measuring points and a second reference point are arranged on the inner surface of the to-be-measured cardboard along the heading direction, the first reference point is used for aligning and abutting against the intersection line position of the front edge upper skin and the integrally cured upper skin, the second reference point is used for aligning and abutting against the rear edge of the control surface, and the measuring points comprise the second measuring point and at least one first measuring point; and after the measurement clamping plate is aligned in place, the first measurement point is positioned above the integrally cured upper skin, and the second measurement point is positioned above the rear edge of the rear edge upper skin. Therefore, the structure is simple, positioning is accurate, operation is convenient, and unmanned aerial vehicle control surface zero position measurement can be efficiently and conveniently completed.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) manufacturing technology, and more specifically, to a control surface zero-position measuring device. Background Technology

[0002] In the servo control system of a drone, the servo is connected to the control surface through a linkage mechanism. The servo is the power source and the control surface is the actuator. The control surface is used to control the pitch and roll motion of the aircraft.

[0003] The deflection of control surfaces provides trim moments for stable aircraft flight and alters the aircraft's lift-to-drag ratio, thus affecting its range. Currently, there is no efficient method for determining the mechanical zero position of UAV control surfaces during production.

[0004] In summary, how to efficiently and conveniently measure the zero position of the control surface of a UAV is a problem that urgently needs to be solved by those skilled in the art. Utility Model Content

[0005] In view of this, the purpose of this utility model is to provide a control surface zero-position measuring device, which has a simple structure, accurate positioning, and convenient operation, and can efficiently and conveniently complete the zero-position measurement of UAV control surfaces.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] A control surface zero-position measuring device includes several measuring plates for contacting the wing surface. The measuring plates are arranged along the lateral direction of the wing to be measured, and the curvature of the inner surface of the measuring plates is the same as the design wing surface curvature of the wing to be measured at the corresponding lateral position to be measured.

[0008] The inner surface of the test plate is provided with a first reference point, a measurement point and a second reference point along the heading direction of the wing under test. The first reference point is used to align and abut with the intersection of the leading edge upper skin and the integral solidified upper skin. The second reference point is used to align and abut with the trailing edge of the control surface. The measurement point includes a second measurement point and at least one first measurement point.

[0009] Once the first reference point and the second reference point are aligned, the first measuring point is located above the integrally cured upper skin and is used to measure the distance from the first measuring point to the integrally cured upper skin. The second measuring point is located above the rear edge of the rear edge upper skin and is used to measure the distance from the second measuring point to the rear edge of the rear edge upper skin.

[0010] Preferably, the first measuring points are evenly distributed on the integrally solidified skin along the flight direction.

[0011] Preferably, the first reference point, the measuring point, and the second reference point are all provided to protrude from the inner surface of the measuring plate.

[0012] Preferably, the first reference point, the measuring point, and the second reference point are provided with an anti-slip pad at one end of their inner surfaces that are relatively far from the measuring plate. The anti-slip pad is used to increase the friction between the measuring plate and the wing surface so that the wing surface is scratched.

[0013] Preferably, the first reference point, the measuring point, and the second reference point all protrude 3-5mm from the inner surface of the measuring plate, and the distance between the first reference point and the inner surface of the measuring plate is equal to the distance between the second reference point and the inner surface of the measuring plate.

[0014] Preferably, the outer surface of the measuring plate is a vertical surface, and the outer surface and the inner surface of the measuring plate are connected by two parallel horizontal planes.

[0015] Preferably, the measuring plate has at least one weight-reducing hole, and the minimum distance from the weight-reducing hole to the outer edge of the measuring plate is greater than the minimum strength allowable size.

[0016] Preferably, the side of the measuring plate is provided with a heading mark at one end relative to the outer surface. The heading mark is used to assist the measuring plate in aligning with the heading direction when measuring at the zero position of the control surface.

[0017] Preferably, it also includes an angle measuring device for measuring the orientation of the measuring plate, the angle measuring device being used to ensure that the measuring plate is aligned with the heading direction when measuring at the zero position of the control surface.

[0018] Preferably, the measuring card includes an aluminum alloy measuring card, a carbon fiber measuring card, and a composite material measuring card.

[0019] The control surface zero-position measuring device provided by this utility model involves placing each measuring plate at the lateral position to be measured on the wing under test, and setting corresponding measuring plates along the heading at the lateral position to be measured. The first reference point of the measuring plate is aligned and abutted with the intersection of the leading edge upper skin and the integrally solidified upper skin of the wing under test. Then, the control surface is rotated so that the second reference point is aligned and abutted with the trailing edge of the control surface of the wing under test. At this time, the deflection position of the control surface is the mechanical zero-position value of the control surface. At the same time, the distance from each measuring point to the wing surface of the wing under test can be used to determine whether the wing configuration of the wing under test meets the requirements.

[0020] Therefore, the control surface zero-position measuring device provided by this utility model has a simple structure, accurate positioning, and convenient operation, and can efficiently and conveniently complete the control surface zero-position measurement and wing configuration detection of UAVs. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0022] Figure 1 A schematic diagram of a specific embodiment of the rudder surface zero-position measuring device provided by this utility model;

[0023] Figure 2 This is a schematic diagram of the measuring plate structure;

[0024] Figure 3 This is a schematic diagram of the assembly of the measuring plate and the left wing during zero-position measurement.

[0025] Figure 4 This is a schematic diagram of the assembly of the measuring plate and the right wing during zero-position measurement.

[0026] Figure 5 This is a schematic diagram showing the distribution of measurement points on the left wing of the measuring plate.

[0027] Figure 6 This is a schematic diagram showing the distribution of measurement points on the right wing for measuring the measuring plate.

[0028] Figures 1-6 middle:

[0029] 10-Wing; 101-Leading edge upper skin; 102-Integral solidified upper skin; 103-Leading edge upper skin; 104-Control surface; 1-Measuring plate; 11-First reference point; 12-Measuring point; 121-First measuring point; 122-Second measuring point; 13-Second reference point; 14-Weight reduction hole; 15-Heading mark. Detailed Implementation

[0030] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0031] The core of this utility model is to provide a control surface zero-position measuring device, which has a simple structure, accurate positioning, and convenient operation, and can efficiently and conveniently complete the zero-position measurement of UAV control surfaces.

[0032] The control surface zero-position measuring device provided by this utility model includes several measuring plates 1 for contacting the wing surface. The measuring plates 1 are arranged along the lateral direction of the wing 10 to be measured. The curvature of the inner surface of the measuring plates 1 is the same as the design wing surface curvature of the wing 10 to be measured at the corresponding lateral position to be measured.

[0033] The inner surface of the measuring plate 1 is provided with a first reference point 11, a measuring point 12 and a second reference point 13 along the heading direction of the wing 10 to be tested. The first reference point 11 is used to align and abut with the intersection of the leading edge upper skin 101 and the integrally solidified upper skin 102. The second reference point 13 is used to align and abut with the trailing edge of the control surface 104. The measuring point 12 includes a second measuring point 122 and at least one second measuring point 121.

[0034] Once the first reference point 11 and the second reference point 13 are aligned, the first measuring point 121 is located above the integrally cured upper skin 102 and is used to measure the distance from the first measuring point 121 to the integrally cured upper skin 102. The second measuring point 122 is located above the rear edge of the rear edge upper skin 103 and is used to measure the distance from the second measuring point 122 to the rear edge of the rear edge upper skin 103.

[0035] It should be noted that the measuring card 1 includes both the measuring card 1 used for measuring the zero position of the control surface of the left wing 10 of the UAV, such as... Figure 3 As shown, it also includes a measuring card 1 for measuring the zero position of the control surface of the right wing 10 of the UAV, such as... Figure 4 As shown.

[0036] The number of measuring plates 1 is the same as the number of control surfaces of the wing 10 under test. Here, the number of control surfaces refers to the sum of the number of flaps, flaperons, and ailerons on the trailing edge of the wing 10. The larger the number of control surfaces of the wing 10, the more measuring plates 1 are required to measure the zero position of the control surfaces. Figure 3 and Figure 4 For example, a single-sided wing 10 is provided with 3 control surfaces 104, and 3 corresponding measuring plates 1 are provided to perform control surface zero-position measurement on the control surfaces 104.

[0037] Regardless of the number of measuring plates 1 corresponding to a single wing 10, the lateral position to be measured corresponding to each measuring plate 1 needs to be determined based on factors such as the structure of the wing 10 itself in actual production, which will not be elaborated here; however, for UAVs with symmetrical wing layouts, the lateral positions to be measured corresponding to the two wings 10 of the same UAV are usually set symmetrically about the flight axis.

[0038] For example Figure 3 The left wing 10 shown has three measuring plates 1 positioned from the inside out along the wing span at distances of 1101 mm, 3541 mm, and 6623 mm from the flight axis, respectively. Figure 4The right wing 10 shown has three measuring plates 1 positioned from the inside out at 1101mm, 3541mm, and 6623mm from the flight axis, respectively, along the wing span direction.

[0039] To facilitate the transportation and storage of the measuring caliper 1, the measuring caliper 1 is usually made of aluminum alloy, carbon fiber, or composite material. It is lightweight and easy to transport and measure. Considering cost, the measuring caliper 1 is mostly made of aluminum alloy.

[0040] The curvature of the inner surface of the measuring plate 1 is the same as the design airfoil curvature of the wing 10 under test at the corresponding transverse position. Therefore, the curvature shape and size of the inner surface of the measuring plate 1 need to be determined based on the curvature shape and size of the airfoil of the wing 10 under test at the transverse position during actual testing, so that the inner surface of the measuring plate 1 is compatible with the airfoil of the wing 10 under test.

[0041] The inner surface of the measuring plate 1 is provided with a first reference point 11, a measuring point 12, and a second reference point 13 along the heading direction of the wing 10 to be measured, such as... Figure 2 As shown, considering that the wing 10 itself usually consists of four parts: leading edge upper skin 101, integrally solidified upper skin 102, trailing edge upper skin 103, and control surface 104, in order to accurately measure the mechanical zero position value of the wing 10 and reduce the zero position detection error of the control surface of the wing 10, the measurement reference for the control surface zero position measurement should be determined first during the test.

[0042] The first reference point 11 of the measuring plate 1 is used to abut against the intersection of the leading edge upper skin 101 and the integrally solidified upper skin 102. On the one hand, it can determine the measurement reference for the second reference point 13 to perform zero-position measurement of the control surface. On the other hand, it can cooperate with the second reference point 13 to form a measurement reference surface, which facilitates the detection of the wing configuration of the wing 10 under test.

[0043] It should be noted that the first reference point 11 should be aligned with the intersection of the leading edge upper skin 101 and the integrally cured upper skin 102 and then abut against it, rather than being suspended above the gap between the two.

[0044] The second reference point 13 of the measuring plate 1 is used to align and abut with the trailing edge of the control surface 104. The position of the second reference point 13 relative to the first reference point 11 is the same as the position of the intersection of the trailing edge of the control surface 104 relative to the leading edge upper skin 101 and the integrally solidified upper skin 102 on the designed airfoil of the wing under test 10 at the lateral position under test.

[0045] Measurement point 12 is mainly used for wing configuration detection of the wing 10 under test. The first measurement point 121 is used to detect whether the processing and assembly errors of the integrally cured upper skin 102 are qualified. Although the directional dimension of the integrally cured upper skin 102 is relatively long, the surface curvature of the integrally cured upper skin 102 changes little. Usually, according to the directional dimension of the integrally cured upper skin 102, two to three second measurement points 121 are selected to measure the zero position of the control surface. It is preferred to set the first measurement point 121 to be evenly distributed on the integrally cured upper skin 102 along the directional direction.

[0046] The second measuring point 122 is used to detect whether the machining and assembly errors of the upper skin 103 at the trailing edge are qualified. Considering that the upper skin 102 at the leading edge of the upper skin 103 at the trailing edge is a fixed skin, while the control surface 104 at the trailing edge is a movable control surface, the second measuring point 122 is usually set above the trailing edge of the control surface 104 during the test.

[0047] During measurement, each measuring plate 1 is placed at the lateral position to be measured on the wing 10 to be measured, and a corresponding measuring plate 1 is set along the heading at the lateral position to be measured, so that the first reference point 11 of the measuring plate 1 is aligned and abutted with the intersection of the leading edge upper skin 101 and the integrally solidified upper skin 102 of the wing 10 to be measured. Then, the control surface is rotated so that the second reference point 13 is aligned and abutted with the trailing edge of the control surface 104 of the wing 10 to be measured. At this time, the deflection position of the control surface is the mechanical zero value of the control surface. At the same time, the distance from each measuring point 12 to the wing surface of the wing 10 to be measured can be used to determine whether the wing configuration of the wing 10 to be measured meets the requirements.

[0048] It should be noted that the wing configuration test of the wing 10 under test can be carried out by visually inspecting whether the distance between each measurement point 12 and the wing surface of the wing 10 under test is uniform, or by actually measuring the distance from each measurement point 12 to the wing surface of the wing 10 under test and determining whether the difference falls within the allowable range of the wing configuration.

[0049] Therefore, the control surface zero-position measurement device provided in this embodiment has a simple structure, accurate positioning, and convenient operation, and can efficiently and conveniently complete the control surface zero-position measurement and wing configuration detection of UAVs.

[0050] Based on the above embodiments, the structure of the measuring card 1 is defined such that the first reference point 11, the measuring point 12, and the second reference point 13 all protrude from the inner surface of the measuring card 1.

[0051] The first reference point 11, the measuring point 12, and the second reference point 13 are all set to protrude from the inner surface of the measuring plate 1 in order to reduce the contact area between the measuring plate 1 and the wing surface during testing. This can increase the contact pressure on the contact surface and prevent the measuring plate 1 from slipping, while also reducing the risk of scratches on the wing surface by reducing the contact area.

[0052] Preferably, the first reference point 11, the measuring point 12, and the second reference point 13 can all protrude 3-5mm from the inner surface of the measuring plate 1. The distance between the first reference point 11 and the inner surface of the measuring plate 1 is the same as the distance between the second reference point 13 and the inner surface of the measuring plate 1.

[0053] In this embodiment, the first reference point 11, the measuring point 12, and the second reference point 13 are all protruding from the inner surface of the measuring plate 1, which can prevent the measuring plate 1 from slipping or even scratching the wing surface.

[0054] Preferably, an anti-slip pad can be provided at one end of the first reference point 11, the measuring point 12, and the second reference point 13 that is relatively far from the inner surface of the measuring card plate 1. The anti-slip pad can be made of wool felt, rubber pad, etc. The anti-slip pad is used to increase the friction between the measuring card plate 1 and the wing surface in order to prevent the wing surface from being scratched.

[0055] Based on the above embodiments, in order to facilitate the placement of the measuring card 1, the outer surface of the measuring card 1 can be set as a vertical plane, and the outer surface of the measuring card 1 and the inner surface of the measuring card 1 are connected by two parallel horizontal planes.

[0056] like Figure 2 As shown, the measuring plate 1 forms a rectangular frame structure on one side through the vertical surface and the upper and lower horizontal surfaces. The regular shape facilitates transportation and storage and meets the ergonomic principles. The other side is an inner surface with reference points and measuring points 12. The shape of the inner surface is adapted to the wing surface of the wing 10 to be tested, so that the operator can accurately and conveniently detect the wing configuration of the wing 10 to meet the testing requirements.

[0057] Preferably, the measuring plate 1 can be provided with at least one weight reduction hole 14, and the minimum distance from the weight reduction hole 14 to the outer edge of the measuring plate 1 is greater than the minimum strength allowable size, so as to ensure the strength and rigidity of the measuring plate 1 and reduce the deformation of the measuring plate 1 during long-term use.

[0058] Based on the above embodiments, in order to ensure that the measuring plate 1 is aligned with the heading direction during measurement, a heading mark 15 can be provided on the side of the measuring plate 1 at one end relatively close to the outer surface. The heading mark 15 is used to assist the measuring plate 1 in aligning with the heading direction when the control surface is at zero position for measurement.

[0059] Please refer to Figure 2 The heading indicator 15 can be set as a heading indicator groove or heading indicator arrow parallel to the vertical surface of the measuring plate 1. It has a simple structure, is easy to process, and is relatively large in size, which makes it convenient for operators to visually judge whether the measuring plate 1 is parallel to the heading direction.

[0060] Of course, in order to further improve the measurement accuracy of the mechanical zero position value, the control surface zero position measurement device also includes an angle measurement device, such as a heading instrument, for measuring the orientation of the measuring card 1. The angle measurement device is used to ensure that the measuring card 1 is aligned with the heading direction when measuring the control surface zero position.

[0061] It should be noted that the first reference point 11 and the second reference point 13, as well as the first measurement point 121 and the second measurement point 122 mentioned in this application, are only used to distinguish the different positions and do not contain any limitation on the order.

[0062] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0063] The above provides a detailed description of the rudder surface zero-position measuring device provided by this utility model. Specific examples have been used to illustrate the principle and implementation of this utility model. The descriptions of the embodiments above are merely for the purpose of helping to understand the method and core idea of ​​this utility model. It should be noted that those skilled in the art can make various improvements and modifications to this utility model without departing from its principles, and these improvements and modifications also fall within the protection scope of the claims of this utility model.

Claims

1. A rudder surface zero-position measuring device, characterized in that, It includes several measuring plates (1) for contacting the wing surface. The measuring plates (1) are arranged along the lateral direction of the wing to be tested. The curvature of the inner surface of the measuring plates (1) is the same as the design wing surface curvature of the wing to be tested at the corresponding lateral position to be tested. The inner surface of the measuring plate (1) is provided with a first reference point (11), a measuring point (12), and a second reference point (13) along the heading direction of the wing to be tested. The first reference point (11) is used to align and abut with the intersection of the leading edge upper skin (101) and the integrally solidified upper skin (102). The second reference point (13) is used to align and abut with the trailing edge of the control surface (104). The measuring point (12) includes a second measuring point (122) and at least one first measuring point (121). Once the first reference point (11) and the second reference point (13) are aligned, the first measuring point (121) is located above the integrally cured upper skin (102) and is used to measure the distance from the first measuring point (121) to the integrally cured upper skin (102). The second measuring point (122) is located above the rear edge of the rear edge upper skin (103) and is used to measure the distance from the second measuring point (122) to the rear edge of the rear edge upper skin (103).

2. The rudder surface zero-position measuring device according to claim 1, characterized in that, The first measurement point (121) is evenly distributed on the integrally solidified upper skin (102) along the flight direction.

3. The rudder surface zero-position measuring device according to claim 1, characterized in that, The first reference point (11), the measuring point (12) and the second reference point (13) are all set to protrude from the inner surface of the measuring plate (1).

4. The rudder surface zero-position measuring device according to claim 3, characterized in that, The first reference point (11), the measuring point (12) and the second reference point (13) are provided with anti-slip pads at the ends of the measuring card plate (1) that are relatively far from the inner surface of the measuring card plate (1). The anti-slip pads are used to increase the friction between the measuring card plate (1) and the wing surface in order to prevent the wing surface from being scratched.

5. The rudder surface zero-position measuring device according to claim 3, characterized in that, The first reference point (11), the measuring point (12) and the second reference point (13) all protrude 3-5mm from the inner surface of the measuring plate (1). The distance between the first reference point (11) and the inner surface of the measuring plate (1) is the same as the distance between the second reference point (13) and the inner surface of the measuring plate (1).

6. The rudder surface zero-position measuring device according to any one of claims 1-4, characterized in that, The outer surface of the measuring plate (1) is a vertical surface, and the outer surface of the measuring plate (1) and the inner surface of the measuring plate (1) are connected by two parallel horizontal surfaces.

7. The rudder surface zero-position measuring device according to claim 6, characterized in that, The measuring plate (1) is provided with at least one weight reduction hole (14), and the minimum distance from the weight reduction hole (14) to the outer edge of the measuring plate (1) is greater than the minimum strength allowable size.

8. The rudder surface zero-position measuring device according to claim 6, characterized in that, The side of the measuring plate (1) is provided with a heading mark (15) at one end relative to the outer surface. The heading mark (15) is used to assist the measuring plate (1) in aligning the heading direction when measuring the zero position of the control surface.

9. The rudder surface zero-position measuring device according to claim 8, characterized in that, It also includes an angle measuring device for measuring the orientation of the measuring card (1), the angle measuring device being used to ensure that the measuring card (1) is aligned with the heading direction when the rudder surface is at zero position for measurement.

10. The rudder surface zero-position measuring device according to any one of claims 1-4, characterized in that, The measuring plate (1) includes an aluminum alloy measuring plate, a carbon fiber measuring plate, and a composite material measuring plate.

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