Rigidity testing system for control surface rotating shaft of fixed-wing unmanned target aircraft

Abstract

The invention discloses a fixed-wing unmanned target aircraft control surface rotating shaft rigidity test system. The system comprises a base; the bracket is arranged above the base; the tensile force applying assembly is connected to the bracket and is used for providing different pre-stress tensile forces; the tension sensor is arranged at one end of the pull rope, and the other end of the pull rope is connected to the tension applying assembly; the tilt angle sensor is used for being connected to a to-be-detected unmanned aerial vehicle; the contact piece is used for being connected to the unmanned aerial vehicle to be detected, and the tension sensor is connected to the contact piece. The controller is electrically connected to the tension applying assembly, the tension sensor and the tilt angle sensor, and the controller controls the tension applying assembly to apply preset tension based on a detection value of the tension sensor and records a tilt angle value of the tilt angle sensor under the corresponding tension. According to the fixed-wing unmanned target aircraft control surface rotating shaft rigidity testing system, the preset tension can be automatically applied to the target aircraft to carry out control surface rotating shaft rigidity testing, and the labor cost is greatly reduced.

Description

Technical Field

[0001] The invention specifically relates to a fixed-wing unmanned target drone rudder surface shaft stiffness testing system. Background Art

[0002] The target drone mainly simulates the characteristics and combat mode of new threat targets realistically. However, in the actual flight process, there is a significant deviation between the actual action of the control surface system and the instructions issued by the flight control through the control of the steering gear control system. The control surface shaft stiffness test can provide an important basis for improving the dynamic parameters of the steering gear, improve the stability and accuracy of the steering gear system, effectively avoid the occurrence of flutter, and thus fundamentally reduce flight accidents.

[0003] The existing rudder shaft stiffness test device mainly relies on the tester to manually mount weights, adjust the rudder angle and observe the inclinometer reading to calculate its stiffness. This requires a lot of manpower costs. In addition, the long-term repeated mechanical actions and some calculations involved are prone to errors. Summary of the invention

[0004] The present invention provides a fixed-wing unmanned target drone rudder shaft stiffness test system to solve the above-mentioned technical problems, and specifically adopts the following technical solutions:

[0005] A fixed-wing unmanned target aircraft rudder shaft stiffness test control system, comprising:

[0006] Base;

[0007] A bracket, arranged above the base;

[0008] A tension applying assembly, connected to the bracket, for providing different prestressed tensions;

[0009] A tension sensor is arranged at one end of the pull rope, and the other end of the pull rope is connected to the tension applying assembly;

[0010] A tilt sensor for connecting to the drone to be detected;

[0011] A contact piece is used for connecting to the UAV to be detected, and the tension sensor is connected to the contact piece.

[0012] A controller is electrically connected to the tension applying assembly, the tension sensor and the inclination sensor. The controller controls the tension applying assembly to apply a predetermined tension based on the detection value of the tension sensor, and records the inclination value of the inclination sensor under the corresponding tension.

[0013] Furthermore, the tension applying component comprises:

[0014] A first mounting frame is disposed below the bracket;

[0015] A second mounting frame is disposed above the bracket and is located directly above the first mounting frame;

[0016] A lead screw, both ends of which are rotatably connected to the first mounting frame and the second mounting frame respectively, and the lead screw is vertically arranged;

[0017] A guide rod, both ends of which are rotatably connected to the first mounting frame and the second mounting frame respectively, and the guide rod is arranged parallel to the lead screw and spaced apart;

[0018] A driving motor, disposed on the first mounting frame, the driving motor is connected to the lead screw to drive the lead screw to rotate, and the driving motor is electrically connected to the controller;

[0019] A slider is sleeved on the lead screw and the guide rod, and the other end of the pull rope is connected to the slider.

[0020] Furthermore, the tension applying assembly further comprises:

[0021] The tension verticality detection mechanism is used to detect the verticality of the pull rope, and the tension verticality detection mechanism is electrically connected to the controller.

[0022] Furthermore, the tension verticality detection mechanism comprises:

[0023] A fixed outer ring is horizontally arranged and connected to the bracket;

[0024] A movable inner ring is arranged in the middle of the fixed outer ring, and a drawstring is passed through the movable inner ring;

[0025] The center sensing structure is used to be arranged between the fixed outer ring and the movable inner ring to detect whether the movable inner ring is located at the center position of the fixed outer ring.

[0026] Furthermore, the centrality sensing structure comprises:

[0027] A plurality of tension sensors are disposed in the fixed outer ring, and the tension sensors are electrically connected to the controller;

[0028] A plurality of springs have one end connected to the tension sensor in the fixed outer ring and the other end connected to the outer side of the movable inner ring.

[0029] Furthermore, the fixed-wing unmanned target drone rudder shaft stiffness test control system also includes:

[0030] A position adjustment mechanism is arranged between the base and the bracket, and is used to adjust the bracket along a first horizontal direction and a second horizontal direction to adjust the inner ring to the center position of the fixed inner ring. The first direction and the second direction are perpendicular to each other, and the position adjustment mechanism is electrically connected to the controller.

[0031] Furthermore, the fixed-wing unmanned target drone rudder shaft stiffness test control system also includes:

[0032] A level adjustment component is arranged on the base.

[0033] Furthermore, the level adjustment component comprises:

[0034] A plurality of hydraulic cylinders, each of which is arranged below the base, a cylinder body of the hydraulic cylinder is connected to the bottom of the base, and a telescopic rod of the hydraulic cylinder is arranged downward;

[0035] A level detector is arranged on the base;

[0036] The plurality of hydraulic cylinders and the level detector are electrically connected to the controller.

[0037] Furthermore, the fixed-wing unmanned target drone rudder shaft stiffness test control system also includes:

[0038] A display is used to display relevant test data of the current fixed-wing unmanned target aircraft rudder shaft stiffness test control system, the display is arranged on the bracket, and the display is electrically connected to the controller.

[0039] Furthermore, the display is a touch screen, and the touch screen is also used to receive test parameters input by a tester.

[0040] The invention is beneficial in that the provided fixed-wing unmanned target aircraft rudder surface shaft stiffness testing system adopts sensor technology to automatically apply a predetermined pulling force without manual operation, thus saving labor costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0042] Figure 1 It is a schematic diagram of the fixed-wing unmanned target aircraft rudder shaft stiffness test system of the present application;

[0043] Figure 2 is a schematic diagram of a tension verticality detection mechanism of the present application;

[0044] Base 1, bracket 2, tension applying assembly 3, first mounting frame 31, second mounting frame 32, screw 33, guide rod 34, drive motor 35, slider 36, tension sensor 4, contact piece 5, tension verticality detection mechanism 6, fixed outer ring 61, movable inner ring 62, round hole 621, spring 63, hydraulic cylinder 71, cylinder body 711, telescopic rod 712, display 8, pull rope 9. DETAILED DESCRIPTION

[0045] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0046] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0047] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0048] like Figure 1 The figure shows a fixed-wing unmanned target drone rudder shaft stiffness test control system of the present application, comprising: a base 1, a bracket 2, a tension application component 3, a tension sensor 4, a tilt sensor, a contact member 5 and a controller.

[0049] Specifically, the bracket 2 is arranged above the base 1. The tension applying assembly 3 is connected to the bracket 2 to provide different prestressed tensions. The tension sensor 4 is arranged at one end of the pull rope 9, and the other end of the pull rope 9 is connected to the tension applying assembly 3. The inclination sensor is used to be connected to the drone to be detected, and is used to detect the rotation inclination of the drone under the action of tension. The contact member 5 is used to be connected to the drone to be detected, and the tension sensor 4 is connected to the contact member 5. The contact member 5 can be clamped on the drone by a clamp. The controller is electrically connected to the tension applying assembly 3, the tension sensor 4 and the inclination sensor. The controller controls the tension applying assembly to apply a predetermined tension based on the detection value of the tension sensor 4, and records the inclination value of the inclination sensor under the corresponding tension. In this way, after setting the predetermined tension, the fixed-wing unmanned target drone rudder shaft stiffness test control system can automatically apply tension to the unmanned target drone and record relevant test data.

[0050] In the embodiment of the present application, the tension applying assembly 3 includes: a first mounting frame 31 , a second mounting frame 32 , a lead screw 33 , a guide rod 34 and a drive motor 35 .

[0051] The first mounting frame 31 is arranged below the bracket 2. The second mounting frame 32 is arranged above the bracket 2 and is located directly above the first mounting frame 31. The two ends of the lead screw 33 are rotatably connected to the first mounting frame 31 and the second mounting frame 32 respectively, and the lead screw 33 is arranged vertically. The two ends of the guide rod 34 are rotatably connected to the first mounting frame 31 and the second mounting frame 32 respectively, and the guide rod 34 is arranged parallel to the lead screw 33 and spaced apart. The driving motor 35 is arranged on the first mounting frame 31, and the driving motor 35 is connected to the lead screw 33 to drive the lead screw 33 to rotate. The driving motor 35 is electrically connected to the controller. The slider 36 is sleeved on the lead screw 33 and the guide rod 34, and the other end of the pull rope 9 is connected to the slider 36. When the driving motor 35 drives the lead screw 33 to rotate, the slider 36 moves up and down under the drive of the lead screw 33, thereby providing prestress of different sizes.

[0052] As a preferred embodiment, the tension applying assembly 3 further comprises: a tension verticality detection mechanism 6. The tension verticality detection mechanism 6 is used to detect the verticality of the pull rope 9, and the tension verticality detection mechanism 6 is electrically connected to the controller. It can be understood that when the tension applying assembly 3 applies tension, the pull rope 9 needs to be kept in a vertical state as much as possible. If the pull rope 9 is in an inclined state, it will affect the test accuracy.

[0053] like Figure 2As shown, in the embodiment of the present application, the tension verticality detection mechanism 6 includes: a fixed outer ring 61, a movable inner ring 62 and a center sensing structure. The fixed outer ring 61 is horizontally arranged and connected to the bracket 2. The movable inner ring 62 is arranged in the middle of the fixed outer ring 61, and the pull rope 9 is passed through the circular hole 621 in the middle of the movable inner ring 62. The inner diameter of the circular hole 621 in the middle of the movable inner ring 62 is similar to the diameter of the pull rope 9. The center sensing structure is arranged between the fixed outer ring 61 and the movable inner ring 62 to detect whether the movable inner ring 62 is located at the center position of the fixed outer ring 61. Specifically, the center sensing structure includes: a plurality of tension sensors and a plurality of springs 63. The plurality of tension sensors are arranged in the fixed outer ring 61, and the tension sensors are electrically connected to the controller. One end of the plurality of springs 63 is connected to the tension sensor in the fixed outer ring 61, and the other end is connected to the outer side of the movable inner ring 62. In the present application, the number of tension sensors and springs 63 is 4. In the natural state, the movable inner ring 62 is located at the center of the fixed outer ring 61, and the tension values ​​sensed by the four tension sensors are equal. When the pull rope 9 is tilted, the pull rope 9 will press the movable inner ring 62 to deviate from the center of the fixed outer ring 61, and at this time, the vertical sensed by the tension sensor changes.

[0054] In an embodiment of the present application, the fixed-wing unmanned target drone rudder shaft stiffness test control system further includes: a position adjustment mechanism.

[0055] The position adjustment mechanism is disposed between the base 1 and the bracket 2, and is used to adjust the bracket 2 along a first horizontal direction and a second horizontal direction to adjust the inner ring to the center position of the fixed inner ring, the first direction and the second direction are perpendicular to each other, and the position adjustment mechanism is electrically connected to the controller. Specifically, the controller can determine the degree of eccentricity between the movable inner ring 62 and the inductive outer ring according to the sensing values ​​of the four tension sensors, and then control the position adjustment mechanism to move along two directions until the sensing values ​​of the four tension sensors are the same.

[0056] In an embodiment of the present application, the control system for testing the rigidity of the rudder shaft of the fixed-wing unmanned target aircraft further includes: a horizontal adjustment component, which is arranged on the base 1 and is used to adjust the horizontality of the base 1. Specifically, the horizontal adjustment component includes: a plurality of hydraulic cylinders 71 and a level detector. Each hydraulic cylinder 71 is arranged below the base 1, the cylinder body 711 of the hydraulic cylinder 71 is connected to the bottom of the base 1, and the telescopic rod 712 of the hydraulic cylinder 71 is arranged downward. The level detector is arranged on the base 1. The plurality of hydraulic cylinders 71 and the level detector are electrically connected to the controller. The controller can automatically adjust the extension and retraction of the plurality of hydraulic cylinders 71 according to the detection data of the level detector, thereby adjusting the fixed-wing unmanned target aircraft rudder shaft rigidity test system to a horizontal state.

[0057] In the embodiment of the present application, the fixed-wing unmanned target aircraft rudder shaft stiffness test control system further comprises: a display 8. The display 8 is used to display the relevant test data of the current fixed-wing unmanned target aircraft rudder shaft stiffness test control system, and the display 8 is arranged on the bracket 2, and the display 8 is electrically connected to the controller. As a preferred embodiment, the display 8 is a touch screen, and the touch screen is also used to receive the test parameters input by the tester.

[0058] As an optional embodiment, the fixed-wing unmanned target drone rudder shaft stiffness test system also includes: a counterweight. The counterweight is arranged in the base 1. It is understandable that the fixed-wing unmanned target drone rudder shaft stiffness test system needs to stably apply tension to the drone. If its own weight is too small, it cannot maintain its own stability and thus cannot stably apply tension to the drone. Therefore, a counterweight can be set in the base 1 to increase the weight of the fixed-wing unmanned target drone rudder shaft stiffness test system and increase the test stability. Preferably, the fixed-wing unmanned target drone rudder shaft stiffness test system includes a plurality of replaceable counterweights, each of which has a different weight. In this way, the counterweight of the corresponding weight can be replaced as needed.

[0059] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the above embodiments do not limit the present invention in any form, and any technical solution obtained by equivalent replacement or equivalent transformation falls within the protection scope of the present invention.

Claims

1. A fixed-wing unmanned target aircraft rudder shaft stiffness test control system, characterized in that: Include: Base; A bracket, arranged above the base; A tension applying assembly, connected to the bracket, for providing different prestressed tensions; A tension sensor is arranged at one end of the pull rope, and the other end of the pull rope is connected to the tension applying assembly; A tilt sensor for connecting to the drone to be detected; A contact piece is used for connecting to the UAV to be detected, and the tension sensor is connected to the contact piece. A controller is electrically connected to the tension applying assembly, the tension sensor and the inclination sensor. The controller controls the tension applying assembly to apply a predetermined tension based on the detection value of the tension sensor, and records the inclination value of the inclination sensor under the corresponding tension.

2. The fixed-wing unmanned target drone rudder shaft stiffness test control system according to claim 1, characterized in that: The tension applying component comprises: A first mounting frame is disposed below the bracket; A second mounting frame is disposed above the bracket and is located directly above the first mounting frame; A lead screw, both ends of which are rotatably connected to the first mounting frame and the second mounting frame respectively, and the lead screw is vertically arranged; A guide rod, both ends of which are rotatably connected to the first mounting frame and the second mounting frame respectively, and the guide rod is arranged parallel to the lead screw and spaced apart; A driving motor, disposed on the first mounting frame, the driving motor is connected to the lead screw to drive the lead screw to rotate, and the driving motor is electrically connected to the controller; A slider is sleeved on the lead screw and the guide rod, and the other end of the pull rope is connected to the slider.

3. The fixed-wing unmanned target drone rudder shaft stiffness test control system according to claim 2, characterized in that: The tension applying assembly further comprises: The tension verticality detection mechanism is used to detect the verticality of the pull rope, and the tension verticality detection mechanism is electrically connected to the controller.

4. The fixed-wing unmanned target aircraft rudder shaft stiffness test control system according to claim 3, characterized in that: The tension verticality detection mechanism comprises: A fixed outer ring is horizontally arranged and connected to the bracket; A movable inner ring is arranged in the middle of the fixed outer ring, and a drawstring is passed through the movable inner ring; The center sensing structure is used to be arranged between the fixed outer ring and the movable inner ring to detect whether the movable inner ring is located at the center position of the fixed outer ring.

5. The fixed-wing unmanned target drone rudder shaft stiffness test control system according to claim 4, characterized in that: The centrality sensing structure comprises: A plurality of tension sensors are disposed in the fixed outer ring, and the tension sensors are electrically connected to the controller; A plurality of springs have one end connected to the tension sensor in the fixed outer ring and the other end connected to the outer side of the movable inner ring.

6. The fixed-wing unmanned target drone rudder shaft stiffness test control system according to claim 5, characterized in that: The fixed-wing unmanned target drone rudder shaft stiffness test control system also includes: A position adjustment mechanism is arranged between the base and the bracket, and is used to adjust the bracket along a first horizontal direction and a second horizontal direction to adjust the inner ring to the center position of the fixed inner ring. The first direction and the second direction are perpendicular to each other, and the position adjustment mechanism is electrically connected to the controller.

7. The fixed-wing unmanned target drone rudder shaft stiffness test control system according to claim 2, characterized in that: The fixed-wing unmanned target drone rudder shaft stiffness test control system also includes: A level adjustment component is arranged on the base.

8. The fixed-wing unmanned target drone rudder shaft stiffness test control system according to claim 7, characterized in that: The level adjustment component comprises: A plurality of hydraulic cylinders, each of which is disposed below the base, a cylinder body of the hydraulic cylinder is connected to the bottom of the base, and a telescopic rod of the hydraulic cylinder is disposed downward; A level detector is arranged on the base; The plurality of hydraulic cylinders and the level detector are electrically connected to the controller.

9. The fixed-wing unmanned target aircraft rudder shaft stiffness test control system according to claim 1, characterized in that: The fixed-wing unmanned target drone rudder shaft stiffness test control system also includes: A display is used to display relevant test data of the current fixed-wing unmanned target aircraft rudder shaft stiffness test control system, the display is arranged on the bracket, and the display is electrically connected to the controller.

10. The fixed-wing unmanned target aircraft control surface shaft stiffness test control system according to claim 1, characterized in that: The display is a touch screen, and the touch screen is also used to receive test parameters input by a tester.

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