Static rigidity and strength testing device and method for rudder airfoil

Abstract

The invention discloses a rudder airfoil static rigidity and strength testing device and method.The rudder airfoil static rigidity and strength testing device comprises a supporting frame, a plurality of loading assemblies and a rudder airfoil fixing assembly, the supporting frame is provided with a loading area and a rudder airfoil mounting area, the multiple loading assemblies are all mounted in the loading area, each loading assembly can move independently, and the rudder airfoil fixing assembly is arranged in the rudder airfoil mounting area. The rudder wing is fixedly mounted on the rudder wing mounting area to adjust the position of the rudder wing in the loading area, the rudder wing fixing assembly is arranged in the rudder wing mounting area and can move in the rudder wing mounting area to drive the rudder wing to move to the position over one or more loading assemblies, so that a loading point on the rudder wing is aligned to the loading assemblies, and the loading points on the rudder wing are aligned to the loading assemblies. And the loading assembly is used for applying pressure to the loading point of the rudder wing upwards so as to measure the rigidity and strength of the rudder wing. The device for testing the static rigidity of the rudder airfoil is high in flexibility, can conveniently and accurately measure the rigidity of any loading point on the rudder airfoil, and does not cause additional damage to the rudder airfoil except the rigidity test.

Description

Technical Field

[0001] The invention belongs to the technical field of rudder wing performance testing, and in particular relates to a rudder wing surface static rigidity strength testing device and method. Background Art

[0002] As the main control surface for the missile's flight attitude and rapid maneuverability, the rudder surface plays a vital role in the aerodynamic operability and stability of the entire missile. Its tail fin and tail rudder are usually suspended on the stabilizer surface at two or more points, and its root must be subjected to static stiffness verification analysis.

[0003] At present, the static strength test device of the missile rudder surface usually adopts special tooling, and the test methods mainly include strain measurement method, deformation measurement method and punching measurement method. Among them, the strain measurement method and deformation measurement method mostly use electrical measurement methods such as displacement meter and strain gauge for measurement. However, in the test process, scenarios where the electrical measurement method is not applicable are often encountered, such as: the displacement measurement points that the designer is concerned about are very close to each other, and it is easy to interfere with each other when arranging the displacement meter, and the displacement or strain measurement points of concern are inside or around the wrench slot, which is not conducive to the arrangement of sensors in a cramped space; large structural parts are loaded and deformed greatly, and the electrical measurement method cannot be measured due to the range limitation. When conducting destructive tests on structural parts, the displacement meter needs to be removed midway to protect the sensor. In these practical scenarios, due to the limitations of traditional electrical measurement methods, designers have to adopt alternative solutions, and often cannot obtain the deformation information of the position of real concern. Therefore, the strain measurement method and deformation measurement method have the problems of poor flexibility and limited measurement.

[0004] The punching measurement method involves punching holes on the rudder wing surface and then using a force rod for loading test. This method will cause the rudder wing surface to be damaged. Regardless of whether an extreme loading test is performed, the rudder wing surface after the test can no longer be used as a formal product. The punching measurement method has the disadvantages of high cost and waste of resources. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a static stiffness strength testing device and method for a rudder wing surface in view of the above-mentioned deficiencies in the prior art. The static stiffness strength testing device for a rudder wing surface is highly flexible and can conveniently and accurately measure the stiffness of any loading point on the rudder wing surface without causing additional damage to the rudder wing surface other than the stiffness strength test.

[0006] In order to solve the above problems, the present invention adopts the following technical solutions:

[0007] A rudder wing surface static rigidity testing device comprises a support frame, a plurality of loading components, and a rudder wing fixing component, wherein the support frame is provided with a loading area and a rudder wing installation area, a plurality of loading components are installed in the loading area, and each loading component can be moved individually to adjust its position in the loading area, the rudder wing is fixedly installed on the rudder wing fixing component, the rudder wing fixing component is arranged in the rudder wing installation area, and can be moved in the rudder wing installation area to drive the rudder wing to move to just above one or more loading components so that the loading point on the rudder wing is aligned with the loading component, and the loading component is used to apply pressure upward to the loading point of the rudder wing to measure the rigidity of the rudder wing.

[0008] Preferably, the rudder wing mounting area includes a first track and a second track, and the first track and the second track are respectively arranged on two mutually perpendicular sides of the support frame, and the rudder wing fixing components are provided with two groups, and the two groups of rudder wing fixing components are respectively slidably arranged on the first track and the second track, and the loading area is located in the middle area of ​​the support frame. The rudder wing fixing assembly fixes the rudder wing horizontally and makes the rudder wing extend from the rudder wing mounting area to the loading area, thereby ensuring that the rudder wing is completely located directly above the loading area.

[0009] Preferably, the loading area is rectangular in shape, the first track is parallel to the long side of the loading area, and the length of the first track is greater than the length of the long side of the loading area; the second track is parallel to the short side of the loading area, and the length of the second track is less than or equal to the length of the short side of the loading area.

[0010] Preferably, the rudder wing fixing assembly includes a rudder wing clamp mounting platform and a rudder wing clamp, the rudder wing clamp mounting platform is slidably mounted on the first track or the second track, the rudder wing clamp is fixedly mounted on the rudder wing clamp mounting platform, and the rudder wing clamp is used to clamp the rudder wing.

[0011] Preferably, each of the first rail and the second rail has two parallel rails, and the plane where the tops of the first rail and the second rail are located is higher than the plane where the loading area is located in the vertical direction, and grooves are formed between the two first rails and the two second rails. The rudder wing fixing assembly also includes a position adjustment handwheel and a lead screw, and the lead screw is arranged in the groove and is parallel to the first rail or the second rail. The bottom of the rudder wing clamp mounting platform is threadedly connected to the lead screw, and the position adjustment handwheel is connected to the end of the lead screw for driving the lead screw to rotate, thereby driving the rudder wing clamp mounting platform to move.

[0012] Preferably, the loading assembly includes a servo electric cylinder, a force push rod mounting seat, a force push rod, and a force push rod slot block. The loading area is provided with a plurality of mounting holes. The servo electric cylinder is mounted in the mounting hole. The top of the electric push rod of the servo electric cylinder is located above the mounting hole. The force push rod mounting seat is mounted on the top of the electric push rod. The force push rod is mounted on the force push rod mounting seat. The force push rod slot block is mounted on the top of the force push rod. The electric push rod of the servo electric cylinder moves upward to drive the force push rod slot block to apply pressure to the rudder wing.

[0013] Preferably, the rudder wing surface static stiffness testing device also includes a signal processing module, the signal processing module includes a pressure sensor, a magnetic scale, and a signal processing output unit. The magnetic scale is fixedly mounted on the electric push rod of the servo electric cylinder and is used to measure the deformation of the rudder wing. The magnetic scale is also electrically connected to the signal processing output unit and is used to send the measured rudder wing deformation data to the signal processing output unit. The pressure sensor is arranged at the top of the force push rod slot block and is used to measure the pressure data applied by the force push rod slot block to the rudder wing. The pressure sensor is also electrically connected to the signal processing output unit and is used to send the measured pressure data to the signal processing output unit. The signal processing output unit calculates and analyzes the received data signal to generate and output a curve graph of pressure and deformation changes over time.

[0014] Preferably, the rudder wing surface static stiffness testing device also includes a lifting assembly, and the lifting assembly includes a crane hook, and the crane hook is installed on the support frame and is used to lift the servo electric cylinder to adjust the position of the servo electric cylinder.

[0015] Preferably, the cross-section of the force-adding push rod slot block is rectangular.

[0016] The present invention also provides a method for testing the static rigidity of a rudder wing surface, using the above-mentioned static rigidity testing device for a rudder wing surface, the method is as follows:

[0017] According to the position of the loading point on the rudder wing, the position of the plurality of loading components in the loading area is correspondingly adjusted;

[0018] The rudder wing is fixed by the rudder wing fixing assembly, and the rudder wing is driven to move, so that multiple loading points of the rudder wing are respectively aligned with multiple loading assemblies;

[0019] The loading component is started to load multiple loading points on the rudder wing respectively.

[0020] The present invention loads the rudder wing by means of a plurality of loading assemblies which can be freely moved in a loading area. When it is necessary to load one or several specific loading points on the rudder wing surface, it is only necessary to adjust the position of the loading assemblies accordingly, so that the plurality of loading assemblies correspond in position to the plurality of loading points on the rudder wing surface, thereby being able to freely perform a stiffness strength test on any loading point on the rudder wing surface. In addition, the device can also be applicable to rudder wings of different shapes, and will not damage the rudder wing surface during the test. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic diagram of the three-dimensional structure of the rudder wing surface static rigidity strength testing device in Example 1 of the present invention;

[0022] Figure 2 is a schematic diagram of the three-dimensional structure of the support frame in Example 1 of the present invention;

[0023] Figure 3 is a top view of the rudder wing surface static rigidity strength testing device in embodiment 1 of the present invention;

[0024] Figure 4 Schematic diagram of the installation of the servo electric cylinder and the support frame in Embodiment 1 of the present invention;

[0025] Figure 5 It is a schematic structural diagram of the top of the loading component in Example 1 of the present invention.

[0026] In the figure: 100-support frame, 110-loading area, 111-mounting hole, 120-rudder wing mounting area, 130-first track, 140-second track, 200-servo electric cylinder, 210-force push rod mounting seat, 220-force push rod, 230-force push rod slot block, 240-magnetic scale, 250-lap block, 260-push rod pressure plate, 300-rudder wing fixing assembly, 301-rudder wing fixture mounting table, 302-rudder wing fixture, 303-position adjustment handwheel, 304-screw, 400-rudder wing. DETAILED DESCRIPTION

[0027] The following will be combined with the accompanying drawings in the present invention to clearly and completely describe the technical solutions in the invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of the present invention.

[0028] In the description of the present invention, it should be noted that the term "upper" and the like to indicate orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience and simplification of description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0029] In the description of the present invention, the terms “first” and “second” are used for descriptive purposes only and should not be understood as indicating or implying relative importance.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connect", "set", "install", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection, or an integral connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two elements. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0031] The present invention provides a rudder wing surface static rigidity testing device, comprising a support frame, a plurality of loading components, and a rudder wing fixing component, wherein the support frame is provided with a loading area and a rudder wing installation area, a plurality of loading components are installed in the loading area, and each loading component can be moved individually to adjust its position in the loading area, the rudder wing is fixedly installed on the rudder wing fixing component, the rudder wing fixing component is arranged in the rudder wing installation area, and can be moved in the rudder wing installation area to drive the rudder wing to move to just above one or more loading components, so that the loading point on the rudder wing is aligned with the loading component, and the loading component is used to apply pressure upward to the loading point of the rudder wing to measure the rigidity of the rudder wing.

[0032] The present invention also provides a method for testing the static rigidity of a rudder wing surface, using the above-mentioned static rigidity testing device for a rudder wing surface, the method is as follows:

[0033] According to the position of the loading point on the rudder wing, the position of the plurality of loading components in the loading area is correspondingly adjusted;

[0034] The rudder wing is fixed by the rudder wing fixing assembly, and the rudder wing is driven to move, so that multiple loading points of the rudder wing are respectively aligned with multiple loading assemblies;

[0035] The loading component is started to load multiple loading points on the rudder wing respectively.

[0036] Example 1

[0037] like Figure 1As shown, the present embodiment discloses a static rigidity test device for a rudder wing surface, comprising a support frame 100, a plurality of loading assemblies, and a rudder wing fixing assembly 300. A loading area 110 and a rudder wing mounting area 120 are provided on the support frame 100, a plurality of loading assemblies are installed in the loading area 110, and each loading assembly can be moved individually to adjust its position in the loading area 110, a rudder wing 400 is fixedly installed on the rudder wing fixing assembly 300, the rudder wing fixing assembly 300 is arranged in the rudder wing mounting area 120, and can be moved in the rudder wing mounting area 120, driving the rudder wing 400 to move to the top of one or more loading assemblies, so that the loading point on the rudder wing 400 is aligned with the loading assembly, and the loading assembly is used to apply pressure upward to the loading point of the rudder wing 400, and finally the rigidity of the rudder wing 400 is measured by the deformation and pressure of the loading point.

[0038] like Figure 1 As shown, in this embodiment, the support frame 100 includes a working platform, a vertical bracket, and a bottom bracket located at the top. The loading area 110 and the rudder wing installation area 120 are located on the working platform. There are four vertical brackets, which are arranged along the vertical direction to support the working platform. There are four bottom brackets in total, each of which is arranged along the horizontal direction and is used to connect the bottoms of two adjacent vertical brackets to increase the stability of the support frame 100. Secondly, a triangular reinforcing plate is also provided at the connection between the working platform and the vertical bracket and the vertical bracket and the horizontal bracket to increase the strength of the connection between the working platform and the vertical bracket and the vertical bracket and the horizontal bracket.

[0039] like Figure 1 , 2 As shown, the rudder wing installation area 120 includes a first track 130 and a second track 140, which are respectively arranged on two mutually perpendicular sides of the support frame 100 (edges of the working platform of the support frame 100), the overall shape of the working platform is rectangular, the rudder wing installation area 120 forms an L shape on the working platform (located at the edge of the working platform), and the first track 130 and the second track 140 are respectively arranged on two sides of the rudder wing installation area 120. The remaining rectangular area of ​​the working platform constitutes the above-mentioned loading area 110 (that is, the loading area 110 is located in the middle area of ​​the support frame 100).

[0040] Specifically, two groups of rudder wing fixing assemblies 300 are provided, and the two groups of rudder wing fixing assemblies 300 are slidably disposed on the first track 130 and the second track 140 respectively. The rudder wing fixing assemblies 300 are used to fix the rudder wing 400 horizontally and make the rudder wing 400 extend from the rudder wing mounting area 120 to the loading area 110, thereby ensuring that the rudder wing 400 is completely located directly above the loading area 110.

[0041] like Figure 2As shown, the loading area 110 is in a rectangular shape, the first track 130 is parallel to the long side of the loading area 110, and the length of the first track 130 is greater than the length of the long side of the loading area 110; the second track 140 is parallel to the short side of the loading area 110, and the length of the second track 140 is less than or equal to the length of the short side of the loading area 110. The purpose of setting two tracks with different lengths is to target rudder wings 400 of different sizes, which can be installed on different tracks. For example, the first track 130 is longer, and more loading points can be set along its length direction, and the position of the rudder wing 400 can be flexibly adjusted, which is suitable for rudder wings 400 with a larger length-to-width ratio (relatively narrow and long); the second track 140 is shorter, and when adjusting the position of the rudder wing 400, it can move a smaller distance, which is suitable for rudder wings 400 with a smaller length-to-width ratio.

[0042] like Figure 1 , 2 As shown, the rudder wing fixing assembly 300 includes a rudder wing clamp mounting platform 301 and a rudder wing clamp 302. The rudder wing clamp mounting platform 301 is slidably mounted on the first track 130 or the second track 140. The rudder wing clamp 302 is fixedly mounted on the rudder wing clamp mounting platform 301. The rudder wing clamp 302 is used to clamp the rudder wing 400.

[0043] like Figure 2 As shown, the first rail 130 and the second rail 140 each have two parallel rails, and the plane where the tops of the first rail 130 and the second rail 140 are located is higher than the plane where the loading area 110 is located in the vertical direction, and a groove is formed between the two first rails 130 and the two second rails 140. The rudder wing fixing assembly 300 also includes a position adjustment hand wheel 303 and a lead screw 304, the lead screw 304 is arranged in the groove and is parallel to the first rail 130 or the second rail 140, the two sides of the bottom of the rudder wing fixture mounting platform 301 are sliding parts, and the sliding parts on both sides are slidably arranged on the two parallel first rails 130 or the second rail 140, the middle part of the bottom of the rudder wing fixture mounting platform 301 is a connecting part, the connecting part extends downward into the groove and is threadedly connected with the lead screw 304, the position adjustment hand wheel 303 is connected to the end of the lead screw 304, and is used to drive the lead screw 304 to rotate, thereby driving the rudder wing fixture mounting platform 301 to move.

[0044] Specifically, the rudder wing clamp 302 is installed on one side of the rudder wing clamp mounting platform 301 close to the loading area 110, with its inner end extending toward the loading area 110, and an upper clamp block and a lower clamp block are provided at its end, and the upper clamp block and the lower clamp block are used to clamp the rudder wing 400.

[0045] Furthermore, the rudder surface fixture can be customized according to the installation interface form of different models of rudder wing shafts, and then fixedly installed on the rudder wing fixture mounting platform 301.

[0046] like Figure 1 , 5 As shown, the loading assembly includes a servo electric cylinder 200, a booster push rod mounting seat 210, a booster push rod 220, and a booster push rod slot block 230. The loading area 110 is provided with a plurality of mounting holes 111, the servo electric cylinder 200 is mounted in the mounting holes 111, the top of the electric push rod of the servo electric cylinder 200 is located above the mounting holes 111, the booster push rod mounting seat 210 is disc-shaped and mounted on the top of the electric push rod, the top of the booster push rod 220 mounting seat 210 is provided with a slot, the bottom of the booster push rod 220 is inserted into the slot on the booster push rod mounting seat 210, the booster push rod slot block 230 is located at the top of the booster push rod 220, and its cross section is rectangular.

[0047] The electric push rod of the servo electric cylinder 200 moves upward to drive the force-adding push rod slot block 230 to apply pressure to the rudder wing.

[0048] like Figure 2 , 3 As shown in Figures 4 and 5, in the present embodiment, the loading area 110 is provided with a total of eight mounting holes 111. The eight mounting holes 111 are arranged in two rows and four columns in the loading area 110, and each mounting hole 111 has the same shape, which is a rectangular shape. The loading assembly also includes a push rod pressure plate 260. The top of the servo electric cylinder 200 has a lap block 250. The width of the lap block 250 is greater than the width of the mounting hole 111, and the length is less than the length of the mounting hole 111. Therefore, the servo electric cylinder 200 can be installed on the support frame 100 through the lap block 250, and the position can be adjusted along the length direction of the mounting hole 111. Specifically, the lap block 250 of the servo electric cylinder 200 is overlapped on the working platform (the area between the mounting holes 111), and two push rod pressure plates 260 are provided, which are used to respectively press the two sides of the lap block 250 along the width direction of the mounting hole 111, thereby fixing the servo motor on the working platform. As shown in Figure 4, the lap block 250 of the servo electric cylinder 200 is overlapped on the working platform (the area between the mounting holes 111), and the push rod pressure plate 260 is provided with two pieces, which are used to respectively press the two sides of the lap block 250 along the width direction of the mounting hole 111, thereby fixing the servo motor on the working platform. Figure 4 As shown, one mounting hole 111 can be used to simultaneously mount two servo electric cylinders 200 .

[0049] The static stiffness test device of the rudder wing surface also includes a signal processing module, which includes a pressure sensor, a magnetic scale 240, and a signal processing output unit. The magnetic scale 240 is fixedly installed on the electric push rod of the servo electric cylinder 200, and is used to measure the deformation of the rudder wing. The magnetic scale 240 is also electrically connected to the signal processing output unit, and is used to send the measured rudder wing deformation data to the signal processing output unit. The pressure sensor is set at the top of the booster push rod slot block 230, and is used to measure the pressure data applied by the booster push rod slot block 230 to the rudder wing. The pressure sensor is also electrically connected to the signal processing output unit, and is used to send the measured pressure data to the signal processing output unit. The signal processing output unit calculates and analyzes the received data signal to generate and output a curve chart showing the pressure and deformation changes over time, and analyzes the stiffness of the rudder wing based on the curve chart.

[0050] Optionally, the rudder wing surface static stiffness strength testing device also includes a lifting assembly, which includes a crane hook installed on the support frame 100. Specifically, the crane hook is installed on the side of the working platform and is used to lift the servo electric cylinder 200 to adjust the position of the servo electric cylinder 200.

[0051] The static stiffness testing device for the rudder wing surface in this embodiment is a general-purpose rudder wing stiffness testing device with large size and multi-point flexible thrust arrangement loading.

[0052] Flexibility refers to a slow loading system based on a servo motor. The maximum loading force of a single servo motor is 10,000N. The height direction of the loading rod can be slowly adjusted at a speed of 0.02mm / s. The adjustment interval is small, which is the so-called flexibility.

[0053] Specifically, due to the large loading force during loading, in order to prevent the support frame 100 from deforming, the support frame 100 adopts a high-rigidity workbench. In order to be suitable for more rudder wings of different sizes, the size of the work platform of the support frame 100 is greater than 1000×1000mm, and the test rudder wing size is ≥1000×900mm. The deformation of the support frame 100 during the test should be ≤0.2mm. A small-sized, high-thrust servo electric cylinder 200 is used as the action output device, and the servo electric cylinder 200 integrates a pressure sensor and a magnetic scale 240 (single-point maximum thrust ≥10000N, pressure feedback accuracy ≤1%FS). The upper C# control system + bus control servo motor + serial communication adopts the control system of the lower computer PLC pressure and displacement signals to realize a universal rudder surface rigidity analysis and testing device that can be flexibly arranged.

[0054] The control system hardware part of the device mainly includes industrial control computers, touch screen displays, Siemens PLCs, servo controllers and various signal terminals.

[0055] The front of the control cabinet is the control panel area, where the hardware operation functions of the control cabinet include: power switch, power indicator, position up, displacement down, return to origin, system alarm, automatic / manual, emergency stop, etc. It is used to control the power switch of the equipment, the position movement of the electric push rod, abnormal alarm and the emergency stop of the electric push rod. The electric push rod loading mode is divided into manual and automatic. The loading mode can be switched through the automatic / manual conversion switch on the control cabinet hardware. When an abnormality occurs during the test, the system alarm light will light up. Pressing the emergency stop button can immediately interrupt the servo motor loading and interrupt the test.

[0056] Below the installation position of the touch screen display is a slot for placing the mouse and keyboard. The lower cabinet is equipped with an air switch, touch screen, servo controller, electric push rod position signal terminal, etc. At the rear end of the control cabinet, the upper display installation cabinet area is equipped with an industrial control computer and a strain tester, and the lower cabinet is equipped with a total touch switch, a pressure transmitter, a high-speed pulse terminal block, etc. A dedicated static stiffness test software system is installed in the process all-in-one machine, which can collect and record the loading stress of the rudder wing surface and the displacement of the electric push rod. In addition, after the strain gauge is pasted at the specified position of the rudder wing, the strain tester can be connected to collect and record the strain data and analyze it through the software system. The software process can record the test process in real time and automatically generate a test report.

[0057] The main display contents of the basic interface of the software system include: working time, stage time, servo enable signal, pressure data, displacement data, strain data, and data curve display interface. The function buttons include: call parameters, parameter initialization, start loading, pause loading, continue loading, stop loading, curve control, data saving, etc. The function buttons can be used to set the loading curve and the pressure-time loading control curve, and control the loading speed and the maximum stress duration.

[0058] This embodiment loads the rudder wing by means of a plurality of loading assemblies which can be freely moved in the loading area. When it is necessary to load one or several specific loading points on the rudder wing surface, it is only necessary to adjust the position of the loading assemblies accordingly so that the plurality of loading assemblies correspond in position to the plurality of loading points on the rudder wing surface. This enables the rigidity test to be freely performed on any loading point on the rudder wing surface. In addition, the device can also be applicable to rudder wings of different shapes and will not cause damage to the rudder wing surface during the test.

[0059] Example 2

[0060] This embodiment discloses a method for testing the static rigidity of a rudder wing surface, using the static rigidity testing device for a rudder wing surface in Embodiment 1, and the method is as follows:

[0061] According to the position of the loading point on the rudder wing, the position of the multiple loading components in the loading area 110 is adjusted accordingly;

[0062] The rudder wing is fixed by the rudder wing fixing assembly 300, and the rudder wing is driven to move so that multiple loading points of the rudder wing are respectively aligned with multiple loading assemblies;

[0063] The loading component is started to load multiple loading points on the rudder wing respectively.

[0064] The following is an explanation of the specific shape of the rudder wing:

[0065] like Figure 1 , 3 As shown, in this embodiment, a trapezoidal rudder wing is used, which has a relatively small length-to-width ratio and can be arranged on the second track 140, and the rudder wing is fixed to the rudder wing fixture 302 on the second track 140; the rudder wing has a total of five loading points;

[0066] A total of eight servo electric cylinders 200 are provided, and then five servo electric cylinders 200 are moved and arranged into a shape corresponding to the loading points on the rudder wing, and the remaining servo electric cylinders 200 are arranged randomly;

[0067] After the preparation is completed, the rudder wing fixture mounting platform 301 moves on the second track 140 to drive the rudder wing to move directly above the five servo electric cylinders 200, and the five loading points on the rudder wing are aligned with the five servo motors in position;

[0068] Start the servo motor to perform a loading test on five loading points on the rudder wing;

[0069] The signal processing module generates and outputs a graph showing the pressure and deformation changing with time.

[0070] The static stiffness test method of the rudder wing surface in this embodiment can freely perform stiffness tests on any loading point of the rudder wing surface, and can be applied to rudder wings of different shapes, and will not cause damage to the rudder wing surface during the test.

[0071] It is to be understood that the above embodiments are merely exemplary embodiments used to illustrate the principles of the present invention, but the present invention is not limited thereto. For those of ordinary skill in the art, various modifications and improvements can be made without departing from the spirit and essence of the present invention, and these modifications and improvements are also considered to be within the scope of protection of the present invention.

Claims

1. A rudder wing surface static stiffness test device, characterized in that: It comprises a support frame (100), a plurality of loading components, and a rudder wing fixing component (300). The support frame (100) is provided with a loading area (110) and a rudder wing installation area (120), a plurality of loading components are installed in the loading area (110), and each loading component can be moved individually to adjust its position in the loading area (110). The rudder wing (400) is fixedly mounted on the rudder wing fixing assembly (300). The rudder wing fixing assembly (300) is arranged in the rudder wing installation area (120) and can move in the rudder wing installation area (120) to drive the rudder wing (400) to move to the top of one or more loading assemblies, so that the loading point on the rudder wing (400) is aligned with the loading assembly. The loading assembly is used to apply pressure upward to a loading point of the rudder wing (400) to measure the rigidity of the rudder wing (400).

2. The rudder wing surface static rigidity testing device according to claim 1, characterized in that: The rudder wing installation area (120) comprises a first track (130) and a second track (140), wherein the first track (130) and the second track (140) are respectively arranged on two mutually perpendicular sides of the support frame (100). The rudder wing fixing assembly (300) is provided with two groups, and the two groups of rudder wing fixing assemblies (300) are slidably arranged on the first track (130) and the second track (140) respectively. The loading area (110) is located in the middle area of ​​the support frame (100). The rudder wing fixing assembly (300) fixes the rudder wing (400) horizontally and enables the rudder wing (400) to extend from the rudder wing installation area (120) to the loading area (110), thereby ensuring that the rudder wing (400) is completely located directly above the loading area (110).

3. The rudder wing surface static rigidity testing device according to claim 2, characterized in that: The loading area (110) is in a rectangular shape, the first track (130) is parallel to the long side of the loading area (110), and the length of the first track (130) is greater than the length of the long side of the loading area (110); The second track (140) is parallel to the short side of the loading area (110), and the length of the second track (140) is less than or equal to the length of the short side of the loading area (110).

4. The rudder wing surface static rigidity testing device according to claim 3, characterized in that: The rudder wing fixing assembly (300) comprises a rudder wing fixture mounting platform (301) and a rudder wing fixture (302). The rudder wing clamp mounting platform (301) is slidably mounted on the first track (130) or the second track (140), the rudder wing clamp (302) is fixedly mounted on the rudder wing clamp mounting platform (301), and the rudder wing clamp (302) is used to clamp the rudder wing (400).

5. The rudder wing surface static rigidity testing device according to claim 4, characterized in that: The first rail (130) and the second rail (140) each have two parallel rails, and the plane where the tops of the first rail (130) and the second rail (140) are located is higher than the plane where the loading area (110) is located in the vertical direction, and a groove is formed between the two first rails (130) and the two second rails (140). The rudder wing fixing assembly (300) further comprises a position adjustment hand wheel (303) and a lead screw (304), wherein the lead screw (304) is arranged in the groove and is parallel to the first track (130) or the second track (140). The bottom of the rudder wing fixture mounting platform (301) is threadedly connected to the lead screw (304). The position adjustment hand wheel (303) is connected to the end of the lead screw (304) and is used to drive the lead screw (304) to rotate, thereby driving the rudder wing clamp mounting platform (301) to move.

6. The rudder wing surface static rigidity testing device according to claim 3, characterized in that: The loading assembly comprises a servo electric cylinder (200), a force ejector rod mounting seat (210), a force ejector rod (220), and a force ejector rod slot block (230). The loading area (110) is provided with a plurality of mounting holes (111), the servo electric cylinder (200) is mounted in the mounting hole (111), the top of the electric push rod of the servo electric cylinder (200) is located above the mounting hole (111), the booster push rod mounting seat (210) is mounted on the top of the electric push rod, the booster push rod (220) is mounted on the booster push rod mounting seat (210), the booster push rod slot block (230) is mounted on the top of the booster push rod (220), and the electric push rod of the servo electric cylinder (200) moves upward to drive the booster push rod slot block (230) to apply pressure to the rudder wing (400).

7. The rudder wing surface static rigidity testing device according to claim 6, characterized in that: It also includes signal processing modules, The signal processing module comprises a pressure sensor, a magnetic scale (240), and a signal processing output unit. The magnetic scale (240) is fixedly mounted on the electric push rod of the servo electric cylinder (200) and is used to measure the deformation of the rudder wing (400). The magnetic scale (240) is also electrically connected to a signal processing output unit and is used to send measured deformation data of the rudder wing (400) to the signal processing output unit. The pressure sensor is arranged at the top of the booster rod slot block (230) and is used to measure the pressure data applied by the booster rod slot block (230) to the rudder wing (400). The pressure sensor is also electrically connected to the signal processing output unit and is used to send the measured pressure data to the signal processing output unit. The signal processing output unit calculates and analyzes the received data signal to generate and output a curve graph showing changes in pressure and deformation over time.

8. The rudder wing surface static rigidity testing device according to claim 6, characterized in that: It also comprises a lifting assembly, which comprises a crane hook, and the crane hook is installed on the support frame (100) and is used to lift the servo electric cylinder (200) to adjust the position of the servo electric cylinder (200).

9. The rudder wing surface static rigidity testing device according to claim 6, characterized in that: The cross section of the force-adding push rod slot block (230) is in a rectangular shape.

10. A method for testing the static rigidity of a rudder wing surface, characterized in that: Using the rudder wing surface static stiffness testing device according to any one of claims 1 to 9, the method is as follows: According to the position of the loading point on the rudder wing (400), the position of the plurality of loading components in the loading area (110) is correspondingly adjusted; The rudder wing (400) is fixed by a rudder wing fixing assembly (300), and the rudder wing (400) is driven to move, so that a plurality of loading points of the rudder wing (400) are respectively aligned with a plurality of loading assemblies; The loading component is started to load multiple loading points on the rudder wing (400) respectively.

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