Rigidity testing device for control surface rotating shaft of fixed-wing unmanned target aircraft
Through sensor technology and automated control methods, the inaccuracy and labor-consuming problems caused by manual manual testing are solved, and efficient and accurate testing of the shaft stiffness of the unmanned target rudder surface is achieved, which improves the testing accuracy and stability.
Patent Information
- Application Number
- CN202422535015.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-18
- Publication Date
- 2025-08-01
- Estimated Expiration
- 2034-10-18
AI Technical Summary
The existing rudder surface shaft stiffness test methods rely on manual operation, resulting in inaccurate test results and labor-consuming, and errors and wear are prone to long-term operation.
Using sensor technology, the motor automatically applies a predetermined tension by driving the motor, combined with the inclination sensor and the tension sensor, the automatic test of the stiffness of the rudder surface shaft is realized. The entire test process is controlled by the STM32F103C8T6 main control chip, and is equipped with a horizontal adjustment component and a monitor to display the test results.
It realizes automated testing of the shaft stiffness of the rudder surface of the unmanned target, improves the testing accuracy and efficiency, saves labor costs, and ensures the accuracy and stability of the test results.
Smart Images
Figure CN223179723U_ABST
Abstract
Description
Technical Field
[0001] The utility model specifically relates to a test device for the stiffness of the rudder surface rotating shaft of a fixed-wing unmanned target aircraft. Background Art
[0002] As an important equipment for the test of the new era's sea, land and air trinity weapon system, the target aircraft should realistically simulate the characteristics and combat modes of new threat targets. However, during the actual flight process, especially under real complex airflow loads, there are obvious deviations between the actual actions of the rudder surface system and the instructions issued by the flight control through the control servo control system. The rudder surface rotating shaft stiffness test platform is used to test the stiffness of the servo system under different loads, and its test results can provide an important basis for improving the dynamic parameters of the servo, improve the stability and accuracy of the servo system, effectively avoid the occurrence of flutter, and thus fundamentally reduce flight accidents.
[0003] The existing rudder surface rotating shaft stiffness test methods mainly rely on manual testing. The tester manually hangs weights and calculates the stiffness by adjusting the rudder angle and observing the readings of the inclinometer. Although this only requires labor costs, the long-term repetitive mechanical actions and some calculations are prone to errors. Moreover, the inaccurate results are inevitable due to the wear and rust caused by the long-term non-standard use of manual operations. Content of the Utility Model
[0004] The utility model provides a test device for the stiffness of the rudder surface rotating shaft of a fixed-wing unmanned target aircraft to solve the above-mentioned technical problems, and specifically adopts the following technical solutions:
[0005] A test device for the stiffness of the rudder surface rotating shaft of a fixed-wing unmanned target aircraft, comprising:
[0006] A base;
[0007] A bracket, arranged above the base;
[0008] A first mounting rack, arranged below the bracket;
[0009] A second mounting rack, arranged above the bracket and directly above the first mounting rack;
[0010] A lead screw, with both ends rotatably connected to the first mounting rack and the second mounting rack respectively, and the lead screw is vertically arranged;
[0011] A guide rod, with both ends rotatably connected to the first mounting rack and the second mounting rack respectively, and the guide rod is arranged in parallel and at intervals with the lead screw;
[0012] A driving motor, arranged on the first mounting rack, and the driving motor is connected to the lead screw to drive the lead screw to rotate;
[0013] A slider, sleeved on the lead screw and the guide rod;
[0014] A tensile force sensor, arranged at one end of a pull rope, and the other end of the pull rope is connected to the slider;
[0015] An inclination sensor, used for connecting to an unmanned aerial vehicle to be detected;
[0016] A contact part, used for connecting to an unmanned aerial vehicle to be detected, and the tensile force sensor is connected to the contact part.
[0017] Further, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device further comprises:
[0018] A control box, arranged at the top of the bracket, a controller is arranged inside the control box, the controller is arranged inside the control box and is electrically connected to the driving motor, the tensile force sensor and the inclination sensor.
[0019] Further, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device further comprises:
[0020] A display, used for displaying the value of the tensile force provided by the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device at present, the display is arranged on the bracket, and the display is electrically connected to the controller.
[0021] Further, the controller adopts an STM32F103C8T6 main control chip.
[0022] Further, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device further comprises:
[0023] A horizontal adjustment component, and the horizontal adjustment component is arranged on the base.
[0024] Further, the horizontal adjustment component comprises:
[0025] A plurality of hydraulic cylinders, each hydraulic cylinder is arranged below the base, the cylinder body of the hydraulic cylinder is connected to the lower part of the base, and the telescopic rod of the hydraulic cylinder is arranged downward;
[0026] A horizontal detector, arranged on the base;
[0027] A plurality of the hydraulic cylinders and the horizontal detector are electrically connected to the controller.
[0028] Further, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device further comprises:
[0029] A plurality of rollers, respectively connected to the ends of the telescopic rods of the hydraulic cylinders far away from the cylinder bodies.
[0030] Furthermore, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device further comprises:
[0031] A counterweight block, which is arranged inside the base.
[0032] Furthermore, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device comprises a plurality of replaceable counterweight blocks, and the weight of each counterweight block is different.
[0033] The beneficial effect of the present utility model lies in that the provided fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device adopts sensor technology to automatically apply a predetermined tensile force without manual operation, saving labor costs. Description of the Drawings
[0034] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.
[0035] Figure 1 is a schematic diagram of the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device of the present application;
[0036] Base 1, support 2, first mounting bracket 3, second mounting bracket 4, lead screw 5, guide rod 6, drive motor 7, slider 8, tension sensor 9, pulling rope 10, contact member 11, control box 12, display 13, hydraulic cylinder 141, cylinder body 1411, telescopic rod 1412, roller 15. Detailed Embodiment [[ID=—]]
[0037] The following details the embodiments of the present utility model. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions from beginning to end. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present utility model, and should not be construed as limiting the present utility model.
[0038] In the description of the present utility model, unless otherwise clearly defined and limited, the terms "connected", "connected to", and "fixed" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.
[0039] In the present utility model, unless otherwise clearly specified and defined, the first feature being "above" or "below" the second feature may include the direct contact between the first and second features, or may also include the situation where the first and second features are not in direct contact but in contact through additional features therebetween. Moreover, the first feature being "above", "over" and "on top of" the second feature includes that the first feature is directly above and obliquely above the second feature, or merely indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature being "below", "beneath" and "underneath" the second feature includes that the first feature is directly below and obliquely below the second feature, or merely indicates that the horizontal height of the first feature is less than that of the second feature.
[0040] As Figure 1 shown, a fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device includes: a base 1, a bracket 2, a first mounting bracket 3, a second mounting bracket 4, a lead screw 5, a guide rod 6, a driving motor 7, a slider 8, a tension sensor 9, an inclination sensor (not shown), a contact member 11 and the base 1.
[0041] Specifically, the bracket 2 is arranged above the base 1, the first mounting bracket 3 is arranged below the bracket 2, the second mounting bracket 4 is arranged above the bracket 2 and directly above the first mounting bracket 3. Both ends of the lead screw 5 are respectively rotatably connected to the first mounting bracket 3 and the second mounting bracket 4, and the lead screw 5 is vertically arranged. The guide rod 6 has both ends respectively rotatably connected to the first mounting bracket 3 and the second mounting bracket 4, and the guide rod 6 is arranged in parallel and at intervals with the lead screw 5.
[0042] The driving motor 7 is arranged on the first mounting bracket 3, and the driving motor 7 is connected to the lead screw 5 to drive the lead screw 5 to rotate. In this application, the driving motor 7 is vertically arranged, and the motor shaft of the driving motor 7 is connected to one end of the lead screw 5. The slider 8 is sleeved on the lead screw 5 and the guide rod 6. When the driving motor 7 drives the lead screw 5 to rotate, the slider 8 moves up and down under the drive of the lead screw 5. The tension sensor 9 is arranged at one end of a pull rope 10, and the other end of the pull rope 10 is connected to the slider 8. The tension sensor 9 is used to detect the tension on the pull rope 10. The inclination sensor is used to be connected to the unmanned aircraft to be detected to detect the inclination angle of the inclination sensor. The contact member 11 is used to be connected to the unmanned aircraft to be detected, and the tension sensor 9 is connected to the contact member 11. Further, the contact member 11 can be clamped on the unmanned aircraft through a fixture.
[0043] In an embodiment of this application, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device further includes: a control box 12.
[0044] The control box 12 is arranged on the top of the bracket 2. A controller is arranged inside the control box 12. The controller is arranged inside the control box 12 and is electrically connected to the driving motor 7, the tension sensor 9 and the inclination sensor. The controller can control the driving motor 7 to apply a predetermined force to the tension, and at the same time can record the inclination data.
[0045] In an embodiment of the present application, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device further includes: a display 13.
[0046] The display 13 is used to display the value of the tensile force provided by the current fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device. The display 13 is arranged on the bracket 2 and is electrically connected to the controller. In the present application, the controller uses an STM32F103C8T6 main control chip.
[0047] In an embodiment of the present application, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device further includes: a horizontal adjustment assembly. The horizontal adjustment assembly is arranged on the base 1 and is used to adjust the levelness of the base 1. Specifically, the horizontal adjustment assembly includes a plurality of hydraulic cylinders 141 and a level detector. Each hydraulic cylinder 141 is arranged below the base 1. The cylinder body 1411 of the hydraulic cylinder 141 is connected to the lower part of the base 1, and the telescopic rod 1412 of the hydraulic cylinder 141 is arranged downward. The level detector is arranged on the base 1. The plurality of hydraulic cylinders 141 and the level detector are electrically connected to the controller. The controller can automatically adjust the telescopic lengths of the plurality of hydraulic cylinders 141 according to the detection data of the level detector, so as to adjust the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device to a horizontal state.
[0048] In an embodiment of the present application, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device further includes: a plurality of rollers 15. The plurality of rollers 15 are respectively connected to one end of the telescopic rod 1412 of the hydraulic cylinder 141 far away from the cylinder body 1411, so as to facilitate movement. It can be understood that the rollers 15 are provided with a lock mechanism that can be quickly adjusted. When it is necessary to move the position of the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device, the lock structure is unlocked to switch the rollers 15 to a rollable state. After the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device is moved to a predetermined position, the lock structure is locked to switch the rollers 15 to a non-rollable state.
[0049] As an optional embodiment, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device further includes: a counterweight. The counterweight is arranged in the base 1. It can be understood that the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device needs to stably apply a tensile force to the unmanned aircraft. If its own weight is too small, it cannot maintain its own stability, and thus cannot stably apply a tensile force to the unmanned aircraft. Therefore, a counterweight can be arranged in the base 1 to increase the weight of the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device and improve the test stability. Preferably, the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness test device includes a plurality of replaceable counterweights, and the weight of each counterweight is different. In this way, the counterweight with the corresponding weight can be replaced according to needs.
[0050] The basic principle, main features and advantages of the present utility model have been shown and described above. Those skilled in the art should understand that the above embodiments do not limit the present utility model in any form. Any technical solutions obtained by means of equivalent replacement or equivalent transformation shall fall within the protection scope of the present utility model.
Claims
1. A stiffness test device for the rudder surface rotating shaft of a fixed-wing unmanned target aircraft, characterized in that, Comprising: A base; A bracket, disposed above the base; A first mounting bracket, disposed below the bracket; A second mounting bracket, disposed above the bracket and directly above the first mounting bracket; A lead screw, rotatably connected at both ends to the first mounting bracket and the second mounting bracket respectively, and the lead screw is vertically arranged; A guide rod, rotatably connected at both ends to the first mounting bracket and the second mounting bracket respectively, and the guide rod is arranged in parallel and spaced apart from the lead screw; A driving motor, disposed on the first mounting bracket, and the driving motor is connected to the lead screw to drive the lead screw to rotate; A slider, sleeved on the lead screw and the guide rod; A tension sensor, disposed at one end of a pull rope, and the other end of the pull rope is connected to the slider; An inclination sensor, used for connecting to an unmanned aerial vehicle to be detected; A contact member, used for connecting to an unmanned aerial vehicle to be detected, and the tension sensor is connected to the contact member.
2. The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device according to claim 1, wherein The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device further comprises: A control box, disposed on the top of the bracket, and a controller is provided in the control box, the controller is disposed in the control box and is electrically connected to the driving motor, the tension sensor and the inclination sensor.
3. The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device according to claim 2, wherein The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device further comprises: A display, used for displaying the value of the tension provided by the fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device currently, the display is disposed on the bracket, and the display is electrically connected to the controller.
4. The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device according to claim 2, wherein The controller adopts an STM32F103C8T6 main control chip.
5. The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device according to claim 2, wherein The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device further comprises: A horizontal adjustment assembly, and the horizontal adjustment assembly is disposed on the base.
6. The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device according to claim 5, wherein The horizontal adjustment assembly comprises: A plurality of hydraulic cylinders, each hydraulic cylinder is disposed below the base, the cylinder body of the hydraulic cylinder is connected to the lower part of the base, and the telescopic rod of the hydraulic cylinder is arranged downward; A horizontal detector, disposed on the base; The plurality of hydraulic cylinders and the horizontal detector are electrically connected to the controller.
7. The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device according to claim 6, wherein The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device further comprises: A plurality of rollers, respectively connected to the end of the telescopic rod of the hydraulic cylinder far from the cylinder body.
8. The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device according to claim 1, wherein The fixed-wing unmanned target aircraft rudder surface shaft stiffness testing device further comprises: A counterweight block, disposed inside the base.
9. The fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device according to claim 8, characterized in that the fixed-wing unmanned target aircraft rudder surface rotating shaft stiffness testing device includes a plurality of replaceable counterweight blocks, and the weight of each counterweight block is different.