A high-precision wing deflection angle tester

Abstract

The present invention provides a high-precision wing deflection angle tester, which belongs to the technical field of engineering test and testing, and aims to solve the problem that an existing measurement method using an angular displacement sensor is not suitable for wing surfaces of various models and different installation methods. The high-precision wing deflection angle tester comprises a support base, a multi-core socket arranged on the outside of the top end face of the support base; four sliding auxiliary mechanisms are evenly arranged on the outside of the top end face of the support base; four sensor pillars are respectively arranged on the outside of the top end faces of the four sliding auxiliary mechanisms; four test auxiliary mechanisms are respectively arranged on the top end faces of the four sensor pillars; the support auxiliary mechanism is arranged at the center position of the top end face of the support base; and the rudder cabin is arranged on the outside of the top end face of the support auxiliary mechanism. Laser ranging sensors of different accuracy levels can be selected according to different test accuracy requirements of the wing deflection angle, and the device can be flexibly combined and applied, with strong adaptability, meeting the use requirements in different situations.

Description

Technical Field

[0001] The present invention belongs to the technical field of engineering test and measurement, and more particularly relates to a high-precision wing deflection angle tester. Background Art

[0002] The flight control system is an important component of missile system control. It includes control devices (including high-aspect-ratio ailerons) and stabilization devices (including tail fins). It controls the flight attitude of the missile system through its structural shape and control method. Its reliability is of vital importance. Therefore, during the production and testing of the missile system, the measurement of the wing deflection angle is an essential key content.

[0003] For example, the existing application number CN201711024358.8 discloses a method for testing the strength of a titanium alloy rotorcraft frame, including static load testing: suspending the titanium alloy rotorcraft frame, measuring the value of the initial distance H from each key part to the measurement reference horizontal plane, applying a static load to the key part, and then using a tester to measure the value of the distance H' from each key part to the measurement reference horizontal plane, and comparing the H' value with the H value and the allowable limit value Δ of the frame strength deformation to determine whether the static load test is qualified; dynamic load testing: suspending the titanium alloy rotorcraft frame, measuring the value of the initial distance H from each key part to the measurement reference horizontal plane, applying a load to the key part and simulating the free fall motion of the frame, and then re-suspending the titanium alloy rotorcraft frame back to the suspension point, measuring the value of the distance H' from each key part to the measurement reference horizontal plane; comparing the H' value with the H value and the allowable limit value Δ of the frame strength deformation to determine whether the dynamic load test is qualified.

[0004] Based on the above, the current traditional measurement method is to use an angular displacement sensor, configure a dedicated signal conditioner and test equipment, and design a dedicated connection fixture. The system composition is relatively complex and the cost is high. It is not applicable to wing surfaces of various models and different installation methods. Summary of the Invention

[0005] In order to solve the above technical problems, the present invention provides a high-precision wing deflection angle tester to solve the problem that the existing measurement method uses an angular displacement sensor, configures a special signal conditioner and test equipment, and designs a special connection fixture. The system composition is relatively complex, the cost is high, and it is not applicable to multiple models of wing surfaces with different installation methods.

[0006] The purpose and effect of the high-precision wing deflection angle tester of the present invention are achieved by the following specific technical means:

[0007] A high-precision wing deflection angle tester comprises a support base, a multi-core socket, a sliding auxiliary mechanism, a sensor pillar, a test auxiliary mechanism, a support auxiliary mechanism, and a rudder compartment; the multi-core socket is arranged on the outside of the top end surface of the support base; there are four sliding auxiliary mechanisms, which are evenly arranged on the outside of the top end surface of the support base; there are four sensor pillars, which are respectively arranged on the outside of the top end surfaces of the four sliding auxiliary mechanisms; there are four test auxiliary mechanisms, which are respectively arranged on the top end surfaces of the four sensor pillars; the support auxiliary mechanism is arranged at the center position of the top end surface of the support base; and the rudder compartment is arranged on the outside of the top end surface of the support auxiliary mechanism.

[0008] Furthermore, the sliding auxiliary mechanism includes: a sliding rail guide frame, there are four sliding rail guide frames, the four sliding rail guide frames are evenly arranged and slidably connected to the outside of the top end face of the support base, and limiting guide frames are provided at both ends of the sliding rail guide frame, and the sensor support is fixedly connected to the center position of the top end face of the sliding rail guide frame.

[0009] Furthermore, the support auxiliary mechanism includes: a base bracket, and the base bracket is fixedly connected to the center position of the top end surface of the support base.

[0010] Furthermore, the support auxiliary mechanism also includes: a transfer tooling, which is arranged on the outer side of the top end surface of the base bracket, and the transfer tooling of different heights is matched according to the different models of the wing deflection angle.

[0011] Furthermore, the test auxiliary mechanism includes: a laser ranging sensor and a laser beam, wherein the laser ranging sensor is arranged on the top end surface of the sensor support; the laser beam is arranged on the inner side of the laser ranging sensor, and different levels of laser ranging sensors are selected according to usage requirements;

[0012] The rudder cabin comprises: wing surfaces, and there are four wing surfaces, which are evenly arranged on the outside of the rudder cabin.

[0013] Furthermore, the four airfoils are parallel to the corresponding laser ranging sensors.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] The present invention replaces the traditional method of using angular displacement sensors to test wing deflection angles. It uses a laser distance sensor combined with a specially designed tester structure to achieve wing deflection angle testing, greatly reducing testing costs.

[0016] The present invention has a high compatibility tester through structural optimization design and layout, and can realize the deflection angle test of various types of wings. Testing different types of wings only requires processing a fixed wing surface adapter, which improves the function of the test equipment and reduces the cost of the test equipment.

[0017] The present invention can select laser ranging sensors of different accuracy levels according to different test accuracy requirements of wing deflection angles, flexibly combine and apply them, have strong adaptability, meet the use requirements in different situations, and improve flexibility and convenience in actual use;

[0018] The invention has a compact and simple structure, reliable operation, a simple wing surface installation and fixing method, and is easy to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the overall top view of the structure of the present invention.

[0020] Figure 2 It is an overall isometric structural schematic diagram of the present invention.

[0021] Figure 3 This is an analysis diagram of the airfoil deflection angle test principle of the present invention.

[0022] In the figure, the corresponding relationship between the component names and the drawing numbers is as follows:

[0023] 1. Support base; 2. Laser beam; 3. Wing surface; 4. Rudder cabin; 5. Slide guide frame; 6. Laser ranging sensor; 7. Multi-core socket; 8. Adapter tooling; 9. Sensor support; 10. Base bracket. DETAILED DESCRIPTION

[0024] The embodiments of the present invention are described in further detail below with reference to the accompanying drawings and examples.

[0025] Example:

[0026] As attached Figure 1 To the attached Figure 3 As shown:

[0027] The present invention provides a high-precision wing deflection angle tester, comprising a support base 1, a multi-core socket 7, a sliding auxiliary mechanism, a sensor support column 9, a test auxiliary mechanism, a support auxiliary mechanism, and a rudder compartment 4; the multi-core socket 7 is arranged on the outside of the top end surface of the support base 1; there are four sliding auxiliary mechanisms, which are evenly arranged on the outside of the top end surface of the support base 1; there are four sensor columns 9, which are respectively arranged on the outside of the top end surfaces of the four sliding auxiliary mechanisms; there are four test auxiliary mechanisms, which are respectively arranged on the top end surfaces of the four sensor columns 9; the support auxiliary mechanism is arranged at the center position of the top end surface of the support base 1; and the rudder compartment 4 is arranged on the outside of the top end surface of the support auxiliary mechanism.

[0028] Among them, the sliding auxiliary mechanism includes: a slide rail guide frame 5, there are four slide rail guide frames 5, the four slide rail guide frames 5 are evenly arranged and slidably connected to the outside of the top end face of the support base 1, and a limiting guide frame is provided at both ends of the slide rail guide frame 5, and the sensor pillar 9 is fixedly connected to the center position of the top end face of the slide rail guide frame 5; in use, the limiting guidance of the slide rail guide frame 5 is achieved through the cooperation of the limiting guide frame, and when the slide rail guide frame 5 is pushed to slide, the sensor pillar 9 is driven to slide at the same time, and the position adjustment of the test auxiliary mechanism is achieved through the sliding of the sensor pillar 9. By adjusting the position of the test auxiliary mechanism, the wing deflection angle of multiple models can be tested, which improves the flexibility and convenience of this tester in actual use.

[0029] Among them, the support auxiliary mechanism includes: a base bracket 10, which is fixedly connected to the center position of the top end surface of the support base 1; during use, the support assistance for the rudder cabin 4 is achieved through the cooperation of the base bracket 10.

[0030] Among them, the support auxiliary mechanism also includes: a transfer tooling 8, which is arranged on the outer side of the top end face of the base bracket 10, and the transfer tooling 8 of different heights is matched according to the different models of wing deflection angles; in use, the positioning support of the rudder cabin 4 at the top of the base bracket 10 is achieved through the cooperation of the transfer tooling 8, and at the same time, the cooperation of the transfer tooling 8 meets the use requirements when testing different types of wing deflection angles, further improving the flexibility and convenience of the use of this tester.

[0031] The test auxiliary mechanism includes: a laser distance sensor 6 and a laser beam 2. The laser distance sensor 6 is arranged on the top end surface of the sensor support 9; the laser beam 2 is arranged on the inner side of the laser distance sensor 6. Different levels of laser distance sensors 6 are selected according to the use requirements.

[0032] The rudder cabin 4 includes: wing surfaces 3, there are four wing surfaces 3, and the four wing surfaces 3 are evenly arranged on the outside of the rudder cabin 4; in use, the test process of the wing deflection angle is realized through the cooperation of the laser ranging sensor 6 and the laser beam 2. At the same time, by selecting laser ranging sensors 6 with different accuracy levels, different wing deflection angle test accuracy requirements are met. The higher the accuracy of the laser ranging sensor 6, the higher the accuracy of the wing deflection angle test result, which further improves the flexibility of the use of this tester in actual application and meets the use requirements of this tester in different situations.

[0033] Among them, the four airfoils 3 are parallel to the corresponding laser ranging sensors 6 respectively; during use, the parallel adjustment of the airfoils 3 and the laser ranging sensors 6 improves the smoothness and accuracy of the test of the wing deflection angle.

[0034] The specific usage and function of this embodiment are as follows:

[0035] The testing principle of the present invention is as follows Figure 3 As shown, it is assumed that the movable wing surface 3 of the missile is Figure 3 In the figure, the airfoil 3 is perpendicular to the supporting base 1. When the airfoil 3 is deflected by an angle α, it is OR1. M is the laser emission point of the laser ranging sensor 6, and point O is the rotation center of the airfoil 3. When the airfoil 3 is at the 0° position, the laser spot emitted by the laser beam 2 is located at point A shown in the figure, and the distance measured at this time is L1. When the airfoil 3 is deflected by an angle α to the OR1 position, the laser spot is located at point B shown in the figure, and the distance measured at this time is L2. During the actual test, the airfoil 3 is fixed on the tester, and the laser ranging sensor 6 is also fixed on the tester. The relative positions of the laser ranging sensor 6 and the tested airfoil 3 are fixed. That is, during the actual test, the distance a of OA in the figure is a fixed value, and the distance AB is ΔL=L1-L2. Therefore, the deflection angle α is calculated from the distance L1 measured at the zero position and the distance L2 measured after the airfoil 3 is deflected:

[0036]

[0037] This tester can meet different wing deflection angle test accuracy requirements by selecting laser ranging sensors 6 with different accuracy levels. The higher the accuracy of the laser ranging sensor 6, the higher the accuracy of the wing deflection angle test result. When testing the wing deflection angles of other models, it is only necessary to install a fixed interface according to the different models of wing surfaces 3 and process the required matching adapters 8 of different heights. The adapter fixture 8 has a simple structure. The interface at one end remains matched with the support base 1, and the interface at the other end is matched with the wing surface 3. After the installation is completed, the slider on the slide guide frame 5 is used to allow the laser beam 2 of the laser ranging sensor 6 to be irradiated on the wing surface 3.

Claims

1. A high-precision wing deflection angle tester, characterized by: The invention comprises a support base (1), a multi-core socket (7), a sliding auxiliary mechanism, a sensor support (9), a test auxiliary mechanism, a support auxiliary mechanism, and a rudder cabin (4); the multi-core socket (7) is arranged on the outside of the top end surface of the support base (1); there are four sliding auxiliary mechanisms, and the four sliding auxiliary mechanisms are evenly arranged and arranged on the outside of the top end surface of the support base (1); there are four sensor supports (9), and the four sensor supports (9) are respectively arranged on the outside of the top end surfaces of the four sliding auxiliary mechanisms; there are four test auxiliary mechanisms, and the four test auxiliary mechanisms are respectively arranged on the top end surfaces of the four sensor supports (9); the support auxiliary mechanism is arranged at the center position of the top end surface of the support base (1); and the rudder cabin (4) is arranged on the outside of the top end surface of the support auxiliary mechanism; The sliding auxiliary mechanism includes: a slide rail guide frame (5), wherein there are four slide rail guide frames (5), the four slide rail guide frames (5) are evenly arranged and slidably connected to the outer side of the top end surface of the support base (1), and both ends of the slide rail guide frame (5) are provided with a limit guide frame, and the sensor support (9) is fixedly connected to the center position of the top end surface of the slide rail guide frame (5); The supporting auxiliary mechanism comprises: a base bracket (10), the base bracket (10) being fixedly connected to the center position of the top end surface of the supporting base (1); The supporting auxiliary mechanism further comprises: a transfer tool (8), the transfer tool (8) being arranged on the outer side of the top end surface of the base bracket (10), and the transfer tool (8) having different heights is matched according to different models of wing deflection angles; The test auxiliary mechanism comprises: a laser distance sensor (6) and a laser beam (2); the laser distance sensor (6) is arranged on the top end surface of the sensor support (9); the laser beam (2) is arranged on the inner side of the laser distance sensor (6); different levels of laser distance sensors (6) are selected according to usage requirements; The rudder cabin (4) comprises: wing surfaces (3), wherein there are four wing surfaces (3), and the four wing surfaces (3) are evenly arranged on the outside of the rudder cabin (4).

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