A UAV control surface measurement and calibration device

Abstract

This application discloses a UAV control surface measurement and calibration device, including a scale, a pointer, and two clamping mechanisms symmetrically arranged about the center line of the scale. Each clamping mechanism includes a support component and a telescopic component. The two opposing ends of the two support components are fixedly connected to the two ends of the scale. The two telescopic components are respectively located at the adjacent ends of the two support components, and can clamp onto the stabilizing surface of the rudder after extension. The pointer is detachably connected to the swing end of the rudder and points to the scale area of ​​the scale. This application solves the technical problem in the prior art that requires the vertical stabilizer or V-tail to be removed and a horizontal measuring ruler to measure the control surface angle, resulting in a large workload due to repeated disassembly and reassembly. It enables direct measurement of the control surface angle of the vertical stabilizer or V-tail without disassembly, effectively improving the efficiency of UAV control surface calibration.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) control surface calibration technology, and in particular to a UAV control surface measurement and calibration device. Background Technology

[0002] Control surface calibration is a key part of the aircraft control system, mainly to ensure the accurate correspondence between the mechanical deflection angle of the control surfaces (such as ailerons, elevators, rudders, etc.) and the control system commands. Its background can be summarized as follows: (1) Basic requirements of flight control: Control surfaces are the core actuators for the attitude and trajectory control of aircraft, and their deflection accuracy directly affects flight stability, maneuverability and safety. (2) If there is a deviation between the actual deflection of the control surfaces and the theoretical commands (such as nonlinearity, zero position offset, stroke asymmetry, etc.), it may lead to a decrease in control performance or even loss of control. (3) Necessity of calibration: Mechanical installation error: There may be initial deviations in the installation of mechanical components such as servos, linkages, and hinges. Electrical signal deviation: The mapping relationship between control signals (such as PWM pulse width) and control surface angles needs to be calibrated. (4) Environmental factors: Temperature changes, mechanical wear, etc. may cause parameter drift, and periodic calibration is required. (5) Calibration objectives: Zero position calibration: Ensure the control signal corresponding to the neutral position of the control surface (such as 0° deflection). Stroke symmetry: Ensure that the left and right control surfaces or the up and down deflection ranges are consistent. Linearity verification: Checking the linear relationship between the control surfaces, deflection angles, and control signals. Control surface calibration is a fundamental guarantee for the safe and reliable operation of an aircraft, and it is carried out throughout the entire life cycle of design, manufacturing, and maintenance.

[0003] Currently, the method for measuring control surfaces involves removing the vertical stabilizer or V-tail, placing it on a horizontal plane, and using a horizontal measuring ruler to measure the control surface angle. This process is quite complicated and requires repeated disassembly and reassembly of the vertical stabilizer, resulting in a large workload. Utility Model Content

[0004] This application provides a UAV control surface measurement and calibration device, which solves the technical problem in the prior art that requires the vertical tail or V-tail to be removed and a horizontal measuring ruler to measure the control surface angle, resulting in a large workload due to repeated disassembly and reassembly. It realizes the ability to directly measure the control surface angle of the vertical tail or V-tail without disassembly and reassembly, effectively improving the efficiency of UAV control surface calibration.

[0005] This utility model provides a UAV control surface measurement and calibration device, including a scale, a pointer, and two clamping mechanisms symmetrically arranged about the center line of the scale. The clamping mechanism includes a support component and a telescopic component. The two opposing ends of the two support components are respectively fixedly connected to the two ends of the scale. The two telescopic components are respectively arranged at the two adjacent ends of the two support components, and can clamp the stabilizing surface of the rudder after they are extended. The pointer is detachably connected to the swing end of the rudder and points to the scale area of ​​the scale.

[0006] In conjunction with the first aspect, in one possible implementation, the support assembly includes a first link and a second link; the first link is connected to the second link, and there is an included angle α between the first link and the second link; the end of the first link facing away from the second link is fixedly connected to the dial; the telescopic assembly is disposed on the second link, and the telescopic ends of the two telescopic assemblies are arranged facing each other.

[0007] In conjunction with the first aspect, in one possible implementation, the telescopic assembly includes a screw and a clamping block; the screw passes through the second connecting rod and is threadedly connected to the second connecting rod; the clamping block is fixedly connected to the end of the screw and is capable of approaching or moving away from the rudder's stabilizing surface when the screw is turned.

[0008] In conjunction with the first aspect, in one possible implementation, the support assembly further includes a rotating locking assembly disposed between the first connecting rod and the second connecting rod; the rotating locking assembly includes a rotating shaft, a rotating sleeve, two fixing plates, and two locking members; the two fixing plates are respectively fixedly connected to the outer side of the end of the first connecting rod away from the dial; the rotating shaft passes through the two fixing plates and is fixedly connected to the two fixing plates; the rotating sleeve is sleeved on the outer side of the rotating shaft and rotatably connected to the rotating shaft, and the end of the second connecting rod near the first connecting rod is fixedly connected to the outer side of the rotating sleeve; the fixing plates have a plurality of first locking holes, and the outer side of the end of the second connecting rod near the rotating sleeve has a second locking hole, and during the rotation of the second connecting rod relative to the first connecting rod, the second locking hole can be sequentially aligned with the plurality of first locking holes; the locking member can pass through the aligned first locking holes and second locking holes.

[0009] In conjunction with the first aspect, one possible implementation also includes a flexible locking element; the flexible locking element is disposed on the outer side of one end of the pointer near the swing end of the rudder; the flexible locking element includes a U-shaped base and two elastic elements; the U-shaped base is fixedly connected to the outer side of the pointer; the two elastic elements are respectively disposed on the inner side of the U-shaped base and can be engaged with both sides of the swing end of the rudder.

[0010] In conjunction with the first aspect, in one possible implementation, the dial is an arc-shaped dial.

[0011] In conjunction with the first aspect, in one possible implementation, a clamping plate is fixedly connected to the end of the clamping block away from the screw.

[0012] In conjunction with the first aspect, in one possible implementation, the elastic element is a C-shaped spring.

[0013] In conjunction with the first aspect, in one possible implementation, the included angle α ranges from 45° to 135°.

[0014] One or more technical solutions provided in the embodiments of this utility model have at least the following technical effects or advantages: This embodiment of the invention employs a dial, a pointer, and two symmetrically arranged clamping mechanisms. Each clamping mechanism includes a support component and a telescopic component. The support component is fixedly connected to the dial; the telescopic component is located at the end of the support component and can clamp the stabilizing surface of the rudder after extension; simultaneously, the pointer is detachably connected to the swing end of the rudder and points to the scale area of ​​the dial. This allows the entire calibration device to be directly installed on the rudder to be calibrated. When the rudder swings, the pointer can determine the swing angle, thus facilitating rudder surface calibration. This effectively solves the technical problem in the prior art where the vertical stabilizer or V-tail needs to be removed and a horizontal measuring ruler used to measure the rudder surface angle, resulting in a large workload due to repeated disassembly and reassembly. It enables direct measurement of the rudder surface angle of the vertical stabilizer or V-tail without disassembly, effectively improving the efficiency of UAV rudder surface calibration. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments of this utility model or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 A front view of the UAV control surface measurement and calibration device provided in the embodiments of this application; Figure 2 Axonometric view of the UAV control surface measurement and calibration device provided in the embodiments of this application; Figure 3 A schematic diagram of the structure when a rotating locking component is added between the first and second links in an embodiment of this application; Figure 4 for Figure 3 A magnified view of a portion of region A in the middle; Figure 5 for Figure 4 A schematic diagram of the structure after the fixing plate is removed; Figure 6 A schematic diagram of the structure of the elastic card provided in the embodiment of this application mounted on the pointer.

[0017] Icons: 1-Dial; 2-Pointer; 3-Clamping mechanism; 31-Support assembly; 311-First link; 312-Second link; 3121-Second snap-fit ​​hole; 32-Telescopic assembly; 321-Screw; 322-Clamping block; 323-Clamping piece; 33-Rotating snap-fit ​​assembly; 331-Shaft; 332-Rotating sleeve; 333-Fixing plate; 3331-First snap-fit ​​hole; 334-Snap-fit ​​piece; 4-Rudder; 41-Stabilizer; 5-Elastic snap-fit ​​piece; 51-U-shaped seat; 52-Elastic element. Detailed Implementation

[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some, not all, of the embodiments of the present utility model. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present utility model.

[0019] In the description of the embodiments of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing the embodiments of this utility model and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In addition, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. For those skilled in the art, the specific meaning of the above terms in the embodiments of this utility model can be understood according to the specific circumstances.

[0020] Reference Figure 1 , Figure 2This utility model provides a UAV control surface measurement and calibration device, including a scale 1, a pointer 2, and two clamping mechanisms 3 symmetrically arranged about the center line of the scale 1. The clamping mechanism 3 includes a support component 31 and a telescopic component 32. The two opposing ends of the two support components 31 are respectively fixedly connected to the two ends of the scale 1. The two telescopic components 32 are respectively arranged at the two adjacent ends of the two support components 31, and can clamp the stabilizing surface 41 of the rudder 4 after they are extended. The pointer 2 is detachably connected to the swing end of the rudder 4 and points to the scale area of ​​the scale 1. Specifically, in this embodiment, the fixed connection between the dial 1 and the support component 31 provides support for the telescopic component 32. By controlling the extension of the two telescopic components 32, they can be clamped onto the stabilizing surface 41 of the rudder 4. After clamping, the pointer 2 is installed on the swing end of the rudder 4 and points to the scale value on the dial 1. Thus, by controlling the swing end of the rudder 4 to swing, the pointer 2 swings synchronously. The angle of swing of the rudder 4 can be measured through the dial 1 and the pointer 2, which facilitates the calibration of the rudder 4. Specifically, the two clamping mechanisms 3 generally have an inverted V-shaped opening structure, which can better fit and vertically clamp onto the stabilizing surface 41, and stably clamp onto the stabilizing surfaces 41 on both sides of the rudder 4, effectively preventing the dial 1 from loosening.

[0021] Reference Figure 1 The support component 31 includes a first connecting rod 311 and a second connecting rod 312; the first connecting rod 311 is connected to the second connecting rod 312, and there is an included angle α between the first connecting rod 311 and the second connecting rod 312; the end of the first connecting rod 311 facing away from the second connecting rod 312 is fixedly connected to the dial 1; the telescopic component 32 is disposed on the second connecting rod 312, and the telescopic ends of the two telescopic components 32 are arranged facing each other. In this embodiment, the support component 31 specifically includes a first connecting rod 311 and a second connecting rod 312. The first connecting rod 311 is fixedly connected to the end of the dial 1, which can be a welded connection, a bolt connection, or other fixed connection methods known in the art; the value of the angle α between the first connecting rod 311 and the second connecting rod can be adaptively adjusted according to the actual situation of the rudder 4 stabilizer 41; the two second connecting rods 312 generally have an inverted V-shaped opening structure.

[0022] Reference Figure 1The telescopic assembly 32 includes a screw 321 and a clamping block 322; the screw 321 passes through the second connecting rod 312 and is threadedly connected to the second connecting rod 312; the clamping block 322 is fixedly connected to the end of the screw 321 and can approach or move away from the stabilizing surface 41 of the rudder 4 when the screw 321 is screwed. In this embodiment, the telescopic component 32 specifically includes a screw 321 and a clamping block 322. The screw 321 is a wing screw, and the clamping block 322 is made of hard or soft material. The clamping block 322 can increase the contact area with the stabilizing surface 41 and improve the stability of clamping. By turning the screw 321, the clamping block 322 is driven to move closer to or away from the stabilizing surface 41 of the rudder 4, thereby achieving clamping or releasing of the stabilizing surface 41 of the rudder 4. The telescopic component 32 can also be replaced by an electric push rod or a small hydraulic cylinder, which are conventional alternatives in the art. In this case, the electric push rod or small hydraulic cylinder needs to be fixed on the second connecting rod 312, and its telescopic end can face the stabilizing surface 41 of the rudder 4.

[0023] Reference Figures 3-5The support assembly 31 further includes a rotating snap-fit ​​assembly 33 disposed between the first connecting rod 311 and the second connecting rod 312; the rotating snap-fit ​​assembly 33 includes a rotating shaft 331, a rotating sleeve 332, two fixing plates 333, and two snap-fit ​​pieces 334; the two fixing plates 333 are respectively fixedly connected to the outer side of the end of the first connecting rod 311 away from the scale 1; the rotating shaft 331 passes through the two fixing plates 333 and is fixedly connected to the two fixing plates 333; the rotating sleeve 332 is sleeved on the outer side of the rotating shaft 331 and is rotatably connected to the rotating shaft 331. The end of the second connecting rod 312 near the first connecting rod 311 is fixedly connected to the outside of the rotating sleeve 332; the fixing plate 333 has a plurality of first snap-fit ​​holes 3331, and the second connecting rod 312 near the end of the rotating sleeve 332 has a second snap-fit ​​hole 3121. During the rotation of the second connecting rod 312 relative to the first connecting rod 311, the second snap-fit ​​hole 3121 can be aligned with the plurality of first snap-fit ​​holes 3331 in sequence; the snap-fit ​​member 334 can pass through the aligned first snap-fit ​​hole 3331 and the second snap-fit ​​hole 3121. In this embodiment, considering the different shapes of the stabilizing surface 41 of the rudder 4 of different UAV models, a rotating locking assembly 33 is designed to better meet the calibration requirements of the rudder 4 of more UAV models. This assembly allows for adjustment and fixation of the angle between the first link 311 and the second link 312, facilitating the stable clamping of the entire calibration device onto the stabilizing surface 41 of the rudder 4 of the current UAV model. The specific adjustment principle is as follows: according to the calibration requirements of the rudder 4 of different UAV models, the second link 312 is swung, allowing it to rotate relative to the first link 311. After rotating to the required angle, the locking member 334 is inserted into the first locking hole 3331 and the aligned second locking hole 3121 to achieve the desired adjustment of the second link 312 at that angle. The locking mechanism facilitates subsequent calibration of the current rudder 4. Specifically, the locking component 334 uses screws or pins to easily insert into the first locking hole 3331 and the aligned second locking hole 3121. Similarly, if it is necessary to calibrate the rudder 4 of another model of UAV, first retract the telescopic component 32, remove the entire device from the current rudder 4, and then remove the locking component 334 from the first locking hole 3331 and the second locking hole 3121, thereby unlocking the second link 312. By continuing to adjust the angle between the second link 312 and the first link 311, and locking the adjusted second link 312 again through the locking component 334, the calibration of the rudder 4 of another model of UAV can continue. By setting the rotating locking component 33, the applicability of the overall calibration device is greatly improved.Specifically, the included angle α ranges from 45° to 135°, which can basically meet the calibration requirements of the rudder 4 and stabilizer 41 of all types of UAVs.

[0024] Reference Figure 6 The system also includes an elastic retainer 5; the elastic retainer 5 is disposed on the outer side of the pointer 2 near the swing end of the rudder 4; the elastic retainer 5 includes a U-shaped base 51 and two elastic elements 52; the U-shaped base 51 is fixedly connected to the outer side of the pointer 2; the two elastic elements 52 are respectively disposed on the inner side of the U-shaped base 51, and can be engaged with both sides of the swing end of the rudder 4. Specifically, in order to enable the pointer 2 to be conveniently and quickly installed on the swing end of the rudder 4, an elastic retainer 5 is designed, and the elastic elements 52 are C-shaped springs; through the U-shaped base 51 and the C-shaped springs, when installing the pointer 2, the two C-shaped springs can be squeezed by the swing end of the rudder 4, so that the pointer 2 can be fixed on the swing end of the rudder 4; the elastic elements 52 can also be other elastic structures that can replace the C-shaped springs, such as miniature springs.

[0025] Reference Figure 1 The dial 1 is an arc-shaped dial. Specifically, in this embodiment, the dial 1 adopts an arc-shaped structure.

[0026] Reference Figure 1 The clamping block 322 is fixedly connected to a clamping plate 323 at its end away from the screw 321. Specifically, in this embodiment, a clamping plate 323 is also provided. The clamping plate 323 is made of a soft material, such as a rubber pad. The clamping plate 323 can further increase the contact area with the stabilizing surface 41, while avoiding squeezing damage between the clamping plate 323 and the stabilizing surface 41.

[0027] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0028] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.

Claims

1. An unmanned aerial vehicle control surface measurement calibration device, comprising: Includes a dial (1), a pointer (2), and two clamping mechanisms (3) symmetrically arranged about the center line of the dial (1); The clamping mechanism (3) includes a support component (31) and a telescopic component (32), with the two opposing ends of the two support components (31) respectively fixedly connected to the two ends of the dial (1); The two telescopic components (32) are respectively disposed at the two ends of the two support components (31) that are close to each other, and can be clamped to the stabilizing surface (41) of the rudder (4) after they are extended. The pointer (2) is detachably connected to the swing end of the rudder (4) and points to the scale area of ​​the dial (1).

2. The UAV control surface measurement and calibration device according to claim 1, characterized in that, The support assembly (31) includes a first link (311) and a second link (312); The first link (311) is connected to the second link (312), and there is an included angle α between the first link (311) and the second link (312); The end of the first link (311) facing away from the second link (312) is fixedly connected to the dial (1); The telescopic component (32) is disposed on the second connecting rod (312), and the telescopic ends of the two telescopic components (32) are arranged facing each other.

3. The unmanned aerial vehicle control surface measurement calibration apparatus of claim 2, wherein, The telescopic assembly (32) includes a screw (321) and a clamping block (322); The screw (321) passes through the second connecting rod (312) and is threadedly connected to the second connecting rod (312); The clamping block (322) is fixedly connected to the end of the screw (321) and can approach or move away from the stabilizing surface (41) of the rudder (4) when the screw (321) is turned.

4. The unmanned aerial vehicle control surface measurement calibration apparatus of claim 2, wherein, The support assembly (31) further includes a rotating snap-fit ​​assembly (33) disposed between the first link (311) and the second link (312). The rotating snap-fit ​​assembly (33) includes a rotating shaft (331), a rotating sleeve (332), two fixing plates (333) and two snap-fit ​​pieces (334). Two fixing plates (333) are respectively fixedly connected to the outer side of the end of the first connecting rod (311) away from the scale (1); The rotating shaft (331) passes through the two fixed plates (333) and is fixedly connected to the two fixed plates (333); The rotating sleeve (332) is sleeved on the outside of the rotating shaft (331) and rotatably connected to the rotating shaft (331). The end of the second connecting rod (312) near the first connecting rod (311) is fixedly connected to the outside of the rotating sleeve (332). The fixing plate (333) is provided with a plurality of first snap-fit ​​holes (3331), and the second connecting rod (312) is provided with a second snap-fit ​​hole (3121) on the outer side of the end near the rotating sleeve (332). During the rotation of the second connecting rod (312) relative to the first connecting rod (311), the second snap-fit ​​hole (3121) can be aligned with the plurality of first snap-fit ​​holes (3331) in sequence. The snap-fit ​​element (334) can pass through the aligned first snap-fit ​​hole (3331) and second snap-fit ​​hole (3121).

5. The unmanned aerial vehicle control surface measurement calibration apparatus of claim 1, wherein, It also includes flexible clips (5); The elastic clip (5) is located on the outer side of one end of the pointer (2) near the swing end of the rudder (4); The elastic clip (5) includes a U-shaped base (51) and two elastic elements (52); The U-shaped base (51) is fixedly connected to the outside of the pointer (2); The two elastic elements (52) are respectively disposed on the inner side of the U-shaped seat (51) and can be engaged with the two sides of the swing end of the rudder (4).

6. The UAV control surface measurement calibration apparatus of claim 1, wherein, The dial (1) is an arc-shaped dial (1).

7. The unmanned aerial vehicle control surface measurement calibration apparatus of claim 3, wherein, The clamping block (322) has a clamping plate (323) fixedly connected to the end away from the screw (321).

8. The unmanned aerial vehicle control surface measurement calibration apparatus of claim 5, wherein, The elastic element (52) is a C-shaped spring sheet.

9. The unmanned aerial vehicle control surface measurement calibration apparatus of claim 2, wherein, The included angle α ranges from 45° to 135°.

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