A device and method for measuring the deflection angle of a control surface in aircraft structure testing

Abstract

The application provides a kind of measuring device and measuring method for rudder deflection angle in aircraft structure test, belong to the technical field of aircraft structure test, the measuring device includes: fixed part, connecting support and laser sensor, the fixed part is fixedly arranged on the aircraft main structure without displacement activity, the connecting support is arranged on fixed part, and the end of the connecting support is fixedly installed the laser sensor, the laser sensor is arranged towards rudder, the distance data from rudder is measured in real time by the laser sensor, and the real-time measurement and calculation of rudder deflection angle are realized according to the distance data.The measuring device of the application can effectively improve the accuracy and reliability of rudder deflection angle measurement, and provide strong data support for aircraft structure test.

Description

Technical Field

[0001] This invention belongs to the field of aircraft structural testing technology, and specifically relates to a measuring device and method for measuring the deflection angle of control surfaces in aircraft structural testing. Background Technology

[0002] In full-scale aircraft structural testing, it is often necessary to measure the deflection angles of movable control surfaces such as elevators, rudders, and ailerons. Current technology typically uses tilt sensors or cable-operated displacement sensors for this purpose. However, tilt sensors can only measure angle changes based on the horizontal plane and cannot measure rudder deflection angles. Therefore, cable-operated displacement sensors are usually used to measure rudder deflection angles, but this method is complex and has relatively low accuracy. Summary of the Invention

[0003] The purpose of this invention is to provide a measuring device and method for measuring the deflection angle of control surfaces in aircraft structural testing, so as to solve or mitigate at least one of the problems in the prior art.

[0004] In a first aspect, the technical solution of the present invention is: a measuring device for the deflection angle of control surfaces in aircraft structural tests, comprising: a fixing component, a connecting bracket, and a laser sensor. The fixing component is fixedly mounted on the main body structure of the aircraft without displacement. The connecting bracket is mounted on the fixing component, and the laser sensor is fixedly mounted at the end of the connecting bracket. The laser sensor faces the control surface. By measuring the distance data between the laser sensor and the control surface in real time, the deflection angle of the control surface is measured and calculated in real time based on the distance data.

[0005] In a preferred embodiment of the present invention, the fastener is fixed to the main structure of the aircraft by adhesive bonding.

[0006] In a preferred embodiment of the present invention, the connecting bracket includes a vertical bracket, a horizontal bracket, and an adjusting fastener. The vertical bracket is set perpendicular to the main structure of the aircraft, and the horizontal bracket is set in an initial state parallel to the control surface. The adjusting fastener connects the vertical bracket and the horizontal bracket and is used to keep the vertical bracket and the horizontal bracket relatively fixed. The laser sensor is adjusted to a specified position by adjusting the relative position of the adjusting fastener with the vertical bracket and / or the horizontal bracket.

[0007] In a preferred embodiment of the present invention, the laser sensor is a 2D laser sensor, and the measurement accuracy of the laser sensor is not less than the micrometer level.

[0008] In a preferred embodiment of the present invention, the measuring device further includes a data processing unit connected to the laser sensor, which calculates the deflection angle of the control surface in real time based on the ranging information of the laser sensor.

[0009] In a preferred embodiment of the present invention, the deflection angle of the control surface is calculated as follows:

[0010] The two-dimensional coordinates of the point cloud of the control surface contour line are obtained by a laser sensor, or the two-dimensional coordinates of a set of feature points set on the control surface are obtained. The two-dimensional coordinates are fitted with a straight line by the least squares method. The tilt angle θ=arctan(k) is obtained according to the slope k of the fitted straight line. The difference between the tilt angles of the two states before and after the control surface deflection is the deflection angle.

[0011] Secondly, the present invention provides a measurement method using any of the measuring devices described above for measuring the deflection angle of control surfaces in aircraft structural testing, the measurement method comprising:

[0012] Step S1: Before the aircraft structural test, first determine the installation position of the fasteners according to the aircraft model and control surface structure characteristics, and connect the fasteners to the aircraft body structure by adhesive or other means.

[0013] Step S2: Connect one end of the connecting bracket to the fixing piece and the other end to the laser sensor. Adjust the height and / or lateral position of the connecting bracket so that the laser sensor can be aligned with the designated measurement position of the rudder surface. The designated measurement position is the position where the measurement scanning surface of the laser sensor is perpendicular to the rotation axis of the rudder surface.

[0014] Step S3: Activate the laser sensor and collect data to obtain the initial position of the control surface. During the test, the laser sensor continuously collects control surface distance data and transmits the control surface distance data to the data processing unit. The data processing unit processes the control surface distance data in real time according to a predetermined algorithm to obtain the deflection angle of the control surface.

[0015] The measuring device and method of the present invention can effectively improve the accuracy and reliability of control surface deflection angle measurement, and provide strong data support for aircraft structural testing. Attached Figure Description

[0016] To more clearly illustrate the technical solution provided by the present invention, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention.

[0017] Figure 1 This is a schematic diagram of the measuring device of the present invention. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below with reference to the accompanying drawings.

[0019] This invention provides a measuring device and method for measuring the deflection angle of control surfaces in aircraft structural tests. It aims to solve the problems in the prior art where tilt sensors can only measure the angle change relative to the horizontal plane and the accuracy of rope-type displacement sensors is low when measuring the angle change on a non-horizontal plane, thereby improving test efficiency and data accuracy.

[0020] like Figure 1 As shown, this invention first provides a measuring device for the deflection angle of control surfaces in aircraft structural testing. This measuring device mainly includes: a fixing component 1, a connecting bracket 2, and a laser sensor 3. The fixing component 1 is fixedly mounted on the main aircraft structure 4, which is typically a relatively fixed structure, i.e., a structure that does not undergo displacement, deflection, or movement. The connecting bracket 2 is mounted on the fixing component 1, and the laser sensor 3 is fixedly installed at its end. The laser sensor 3 faces the control surface 5, and the distance between the laser sensor 3 and the control surface is measured. Based on this distance, the deflection angle of the control surface is measured and calculated.

[0021] In some embodiments of the present invention, the fastener 1 can be fixed to the main structure 4 of the aircraft by adhesive bonding. It is fixed by adhesive bonding during use and can be removed after the test is completed without damaging the main structure 4 of the aircraft.

[0022] In this invention, the connecting bracket 2 includes a vertical bracket 21, a horizontal bracket 22, and an adjusting fastener 23. The vertical bracket 21 is set perpendicular to the main structure 4 of the aircraft, and the horizontal bracket 22 is set parallel to the initial state of the control surface 5 (i.e., the attitude when the control surface 5 is parallel to the main structure 4 of the aircraft). The adjusting fastener 23 connects the vertical bracket 21 and the horizontal bracket 22 to keep the vertical bracket 21 and the horizontal bracket 22 relatively fixed. The relative position of the adjusting fastener 23 with the vertical bracket 21 and / or the horizontal bracket 22 can be adjusted, so that the vertical bracket 21 and the horizontal bracket 22 can be adjusted to a specified or suitable position.

[0023] In a preferred embodiment of the present invention, the laser sensor 3 is a 2D laser sensor. Typically, a 2D laser sensor with micron-level or higher precision is selected. The laser reflection data of the rudder surface, including distance information, is collected in real time through the 2D laser sensor.

[0024] The measuring device of the present invention also includes a data processing unit, which is a device or equipment with data computing capabilities, such as a CPU, GPU, DSP, FPGA chip device, or a device such as a computer or server. The data processing unit is connected to the laser sensor 3 and calculates the deflection angle of the control surface in real time based on the ranging information of the laser sensor 3.

[0025] The calculation process of the deflection angle is as follows: The laser sensor 3 obtains the two-dimensional coordinates of the contour point cloud of the control surface 5 (for a flat control surface) or obtains the two-dimensional coordinates of a set of feature points set on the control surface 5 (for a non-flat control surface). The two-dimensional coordinates are fitted with a straight line by the least squares method. The tilt angle θ = arctan(k) is obtained according to the slope k of the fitted straight line. The difference in tilt angle between the two states before and after the control surface deflection is the deflection angle.

[0026] Based on the above-described measuring device, the present invention also provides a method for measuring the deflection angle of control surfaces in aircraft structural tests, the method comprising the following steps:

[0027] Step S1: Before the aircraft structure test, first select a suitable installation position for the fastener 1 according to the aircraft model and control surface structure characteristics, and connect the fastener 1 to the aircraft body structure 4 by adhesive or other means to ensure its stability.

[0028] Step S2: Connect one end of the connecting bracket 2 to the fixing piece 1 and the other end to the laser sensor 3. Adjust the height and / or lateral position of the connecting bracket 2 so that the laser sensor 3 can be aligned with the designated measurement position of the rudder surface 5. The designated measurement position is the position where the measurement scanning surface of the laser sensor 3 is perpendicular to the rotation axis 6 of the rudder surface.

[0029] Step S3: Activate laser sensor 3 and collect data to obtain the initial position of the control surface. During the test, laser sensor 3 continuously collects control surface distance data and transmits the control surface distance data to the data processing unit. The data processing unit processes the control surface distance data in real time according to a predetermined algorithm to obtain the deflection angle of the control surface, and records and displays it for analysis and evaluation by the test personnel.

[0030] Through multiple experiments, the measuring device and method of the present invention can effectively improve the accuracy and reliability of control surface deflection angle measurement, providing strong data support for aircraft structural testing.

[0031] The measuring device and method for measuring the deflection angle of control surfaces in aircraft structural testing, as described in this invention, have the following advantages:

[0032] 1) Higher accuracy measurement: Based on the high-precision laser sensor ranging capability, it can accurately capture the position change information of the control surface, thereby providing more accurate deflection angle measurement results;

[0033] 2) Real-time data acquisition: Laser sensors can quickly acquire data to achieve real-time monitoring of control surface deflection angles, which is particularly important for aircraft structural testing and flight performance evaluation.

[0034] 3) Simplified installation process: The design of the fixing component 1 and the connecting bracket 2 makes the installation and adjustment process of the entire measuring device simpler and faster;

[0035] 4) Improved testing efficiency: The collected laser reflection data can be processed automatically in real time to calculate the deflection angle of the control surface, which can significantly improve the efficiency of aircraft structural testing.

[0036] 5) High adaptability: This measurement method is applicable to different aircraft models and control surface structures, and has good versatility and adaptability.

[0037] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A measuring device for the deflection angle of control surfaces in aircraft structural testing, characterized in that, include: The fixture (1), the connecting bracket (2), and the laser sensor (3) are fixedly mounted on the main body structure (4) of the aircraft, which does not move. The connecting bracket (2) is mounted on the fixture (1), and the laser sensor (3) is fixedly mounted at the end of the connecting bracket (2). The laser sensor (3) is set facing the control surface (5). The distance data between the laser sensor (3) and the control surface is measured in real time, and the control surface deflection angle is measured and calculated in real time based on the distance data.

2. The measuring device for the deflection angle of control surfaces in aircraft structural testing as described in claim 1, characterized in that, The fastener (1) is fixed to the main structure (4) of the aircraft by adhesive bonding.

3. The measuring device for the control surface deflection angle in aircraft structural testing as described in claim 1, characterized in that, The connecting bracket (2) includes a vertical bracket (21), a horizontal bracket (22) and an adjusting fastener (23). The vertical bracket (21) is set perpendicular to the main structure of the aircraft (4), and the horizontal bracket (22) is set parallel to the control surface (5) in its initial state. The adjusting fastener (23) connects the vertical bracket (21) and the horizontal bracket (22) to keep the vertical bracket (21) and the horizontal bracket (22) relatively fixed. The laser sensor (3) is adjusted to a specified position by adjusting the relative position of the adjusting fastener (23) and the vertical bracket (21) and / or the horizontal bracket (22).

4. The measuring device for the control surface deflection angle in aircraft structural testing as described in claim 1, characterized in that, The laser sensor (3) is a 2D laser sensor, and the measurement accuracy of the laser sensor is not less than the micrometer level.

5. The measuring device for measuring the deflection angle of control surfaces in aircraft structural testing as described in any one of claims 1 to 4, characterized in that, The measuring device further includes a data processing unit, which is connected to the laser sensor (3) and calculates the deflection angle of the control surface in real time based on the ranging information of the laser sensor (3).

6. The measuring device for the control surface deflection angle in aircraft structural testing as described in claim 5, characterized in that, The calculation process for the deflection angle of the control surface is as follows: The laser sensor (3) obtains the two-dimensional coordinates of the contour point cloud of the rudder surface (5) or obtains the two-dimensional coordinates of a set of feature points set on the rudder surface (5). The two-dimensional coordinates are fitted with a straight line by the least squares method. The tilt angle θ = arctan(k) is obtained according to the slope k of the fitted straight line. The difference between the tilt angles of the two states before and after the rudder surface deflection is the deflection angle.

7. A measurement method, employing the measuring device for measuring the deflection angle of control surfaces in aircraft structural testing as described in any one of claims 1 to 6, characterized in that, The measurement method includes: Step S1: Before the aircraft structure test, the installation position of the fastener (1) is determined according to the aircraft model and control surface structure characteristics. The fastener (1) is then connected to the aircraft body structure (4) by adhesive or other means. Step S2: Connect one end of the connecting bracket (2) to the fixing piece (1) and the other end to the laser sensor (3). Adjust the height and / or lateral position of the connecting bracket (2) so that the laser sensor (3) can be aligned with the designated measurement position of the rudder surface (5), wherein the designated measurement position is the position where the measurement scanning surface of the laser sensor (3) is perpendicular to the rudder surface rotation axis (6). Step S3: Start the laser sensor (3) and collect data to obtain the initial position of the control surface. During the test, the laser sensor (3) continuously collects the control surface distance data and transmits the control surface distance data to the data processing unit. The data processing unit processes the control surface distance data in real time according to the predetermined algorithm to obtain the deflection angle of the control surface.

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