Fixing tool for calibration test of unmanned aerial vehicle

Abstract

The utility model discloses a fixing tool for an unmanned aerial vehicle calibration test in the technical field of unmanned aerial vehicle testing, which comprises an unmanned aerial vehicle body, a fixing mechanism and a testing mechanism are arranged on the outer side of the unmanned aerial vehicle body, a limiting sleeve is fixedly mounted at the lower end of the unmanned aerial vehicle body, and a first supporting table is arranged on the right side of the limiting sleeve. A second supporting table is arranged on the left side of the limiting sleeve, a limiting inserting rod is inserted into the limiting sleeve, a workbench is fixedly installed at the lower ends of the first supporting table and the second supporting table, an air outlet pipe is fixedly installed at the right end of the centrifugal fan, a first motion recorder is fixedly installed at the front end in the air outlet pipe, and a limiting sliding rail is arranged at the lower end of the limiting inserting rod; according to the fixing tool for the unmanned aerial vehicle calibration test, the stability and safety of the unmanned aerial vehicle in the test process can be ensured, the real flight environment can be simulated, and the flight performance of the unmanned aerial vehicle can be accurately and comprehensively detected and evaluated.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle testing, in particular to a fixed tooling for unmanned aerial vehicle calibration testing. Background Art

[0002] A drone is an aircraft that does not require a human pilot and is controlled by a radio remote control device or a self-contained program control device. It is usually composed of a fuselage, a power system, a propeller, a camera, a remote control device, a transmission system, and a sensing component. It can perform various tasks in the air, such as reconnaissance and surveillance, cargo transportation, environmental monitoring, aerial photography, etc. The advantages of drones are low cost, zero risk of casualties, strong survivability, good maneuverability and ease of use, which makes them widely used in both military and civilian fields. With the development of science and technology, drones are becoming an indispensable part of modern society; drone calibration testing is a performance test and accuracy verification process for ground or sea measurement and control systems, radars, communication equipment, etc. by carrying specific measurement and calibration equipment on drones. In this process, drones, as dynamic calibration sources, can simulate actual target objects and test and evaluate key indicators such as tracking capability, measurement accuracy, and system response of measurement and control equipment by accurately controlling their flight trajectory and position.

[0003] In the current practice of UAV calibration and testing, as an important test platform, the endurance and flight performance of UAVs are key indicators for evaluating their practical application value. When performing calibration and testing tasks, these performance indicators are directly related to the accuracy and reliability of the test results. However, after observing the existing UAV calibration and testing fixed tooling configurations, we found that these devices generally can only provide basic support functions, but lack more comprehensive practical and functional support;

[0004] Based on this, the utility model designs a fixed tooling for UAV calibration test to solve the above problems. Utility Model Content

[0005] The purpose of the utility model is to provide a fixed tooling for calibration testing of unmanned aerial vehicles to solve the problems raised in the above-mentioned background technology.

[0006] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0007] A fixed tooling for calibration and testing of unmanned aerial vehicles comprises an unmanned aerial vehicle body, wherein a fixing mechanism and a testing mechanism are arranged on the outer side of the unmanned aerial vehicle body, the fixing mechanism is located below the unmanned aerial vehicle body, and the testing mechanism is arranged on the left side of the unmanned aerial vehicle body, the fixing mechanism comprises a workbench, a first supporting platform, a second supporting platform, a limiting sleeve and a limiting plug rod, the limiting sleeve is fixedly installed on the lower end of the unmanned aerial vehicle body, the first supporting platform is arranged on the right side of the limiting sleeve, the second supporting platform is arranged on the left side of the limiting sleeve, the limiting plug rod is inserted inside the limiting sleeve, the lower ends of the first supporting platform and the second supporting platform are fixedly installed with the workbench, the testing mechanism comprises a centrifugal fan, an air outlet pipe and a first motion recorder, the right end of the centrifugal fan is fixedly installed with the air outlet pipe, the first motion recorder and the second motion recorder are installed on the pipe wall of the air outlet pipe, and the first motion recorder is fixedly arranged on the pipe wall of the front end of the air outlet pipe.

[0008] Optionally, the fixing mechanism also includes a limiting slide rail, a telescopic rod and a fixed plate. The limiting slide rail is arranged at the lower end of the limiting rod. The limiting rod and the limiting slide rail are in a limiting relationship. The front end of the limiting rod is fixedly installed with the telescopic rod. The end of the telescopic rod away from the limiting rod is fixedly connected with the fixed plate. The limiting slide rail and the fixed plate are both fixedly installed on the workbench.

[0009] Optionally, a first bearing ring is provided at the left end of the drone body, a first traction rope is fixedly connected to the outer wall of the first bearing ring, a first winding drum is provided at the end of the first traction rope away from the first bearing ring, the first traction rope is wound on the first winding drum, a first driving motor is provided on the left side of the first winding drum, and a transmission end of the first driving motor is fixedly connected to the first winding drum.

[0010] Optionally, a second bearing ring is provided at the right end of the drone body, a second traction rope is fixedly connected to the outer wall of the second bearing ring, a second winding drum is provided at the end of the second traction rope away from the second bearing ring, the second traction rope is wound on the second winding drum, a second drive motor is provided on the right side of the second winding drum, and the transmission end of the second drive motor is fixedly connected to the second winding drum.

[0011] Optionally, the testing mechanism further includes a fixing rod and a driving motor. The driving motor is arranged behind the centrifugal fan. The transmission end of the driving motor is connected to the centrifugal fan. A fixing rod is fixedly installed at the lower end of the driving motor, and the fixing rod is fixedly installed on the workbench.

[0012] Optionally, a connecting rod is fixedly mounted on the upper end of the centrifugal fan, and a monitoring camera is mounted on the upper end of the connecting rod.

[0013] Optionally, the second motion recorder is fixedly arranged on the pipe wall at the rear end of the air outlet pipe, and a body bracket is fixedly installed at the lower end of the centrifugal fan, and the body bracket is fixedly installed on a workbench.

[0014] Optionally, mounting seats are provided on both the front and rear sides of the workbench, and a wind shielding compartment is provided above the mounting seats.

[0015] Compared with the prior art, the beneficial effects of the utility model are:

[0016] 1. In the utility model, a fixing mechanism is provided, and the snap-on fixing structure and the four-end traction structure are adopted, which can not only effectively support and install the unmanned aerial vehicle body, ensure its stability and facilitate detection, but also simulate the load state of the unmanned aerial vehicle body to perform more realistic detection and test operations. In addition, the four-end traction structure can also prevent the unmanned aerial vehicle body from accidentally flying around during the test, thereby ensuring the safety of the test.

[0017] 2. In the utility model, a testing mechanism is provided, which adopts a blowing structure and a recording structure, and can produce a wind environment of specified wind force to test the endurance and flight performance of the unmanned aerial vehicle. At the same time, multiple recorders can record the flight trajectory and status of the unmanned aerial vehicle in detail, which is convenient for later analysis and calibration, thereby improving the accuracy and reliability of the test results. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of the structure of the utility model in a three-dimensional front view in a disassembled state;

[0019] Figure 2 This is a schematic diagram of the structure of the utility model in a plane front view of a disassembled state;

[0020] Figure 3 It is a schematic diagram of the structure of the utility model in a three-dimensional top view in a disassembled state;

[0021] Figure 4 It is a schematic diagram of the structure of the utility model in a plane top view in a disassembled state;

[0022] Figure 5 It is a schematic diagram of the structure of the utility model in a three-dimensional cutaway view in a disassembled state;

[0023] Figure 6 This is a schematic diagram of the structure of the utility model in a three-dimensional right-side view in a disassembled state;

[0024] Figure 7 This is the split state of the utility model Figure 5 A schematic diagram of the structure at the center showing a three-dimensional magnification;

[0025] Figure 8 This is the split state of the utility model Figure 6 A schematic diagram of the structure at B in the middle is a three-dimensional enlargement;

[0026] Fig. 9 It is a schematic diagram of the structure of the utility model in a combined state plane front view;

[0027] Fig.10 It is a structural schematic diagram of the utility model in a combined state plane right view.

[0028] In the figure: 1. drone body; 2. fixing mechanism; 201. workbench; 202. first support platform; 203. second support platform; 204. limit sleeve; 205. limit plug rod; 206. limit slide rail; 207. telescopic rod; 208. fixing plate; 209. first bearing ring; 210. first traction rope; 211. first winding drum; 212. first driving motor; 213. second bearing ring; 214. second traction rope; 215. second winding drum; 216. second driving motor; 3. testing mechanism; 301. fixing rod; 302. driving motor; 303. centrifugal fan; 304. air outlet pipe; 305. connecting rod; 306. monitoring camera; 307. first motion recorder; 308. second motion recorder; 309. body bracket; 310. mounting seat; 311. wind shield. DETAILED DESCRIPTION

[0029] In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present utility model, unless otherwise specified, "multiple" means two or more.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" 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 it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0031] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0032] See also Figures 1 to 10 In an embodiment of the utility model, a fixed tooling for calibration and testing of a drone comprises a drone body 1, a fixing mechanism 2 and a testing mechanism 3 are arranged on the outside of the drone body 1, the fixing mechanism 2 is located below the drone body 1, and the testing mechanism 3 is arranged on the left side of the drone body 1, the fixing mechanism 2 comprises a workbench 201, a first supporting platform 202, a second supporting platform 203, a limiting sleeve 204 and a limiting plug rod 205, the limiting sleeve 204 is fixedly installed at the lower end of the drone body 1, and a first limiting sleeve 204 is arranged on the right side of the limiting sleeve 204. The support platform 202 is provided with a second support platform 203 on the left side of the limiting sleeve 204, and the limiting sleeve 204 is internally inserted with a limiting rod 205. The lower ends of the first support platform 202 and the second support platform 203 are fixedly installed with a workbench 201. The fixing mechanism 2 also includes a limiting slide rail 206, a telescopic rod 207 and a fixing plate 208. The lower end of the limiting rod 205 is provided with a limiting slide rail 206, and the limiting rod 205 and the limiting slide rail 206 are in a limiting relationship. The front end of the limiting rod 205 is fixedly installed with a telescopic rod 207, and the telescopic rod 208 is fixedly installed with the telescopic rod 207. 07 One end away from the limiting plug rod 205 is fixedly connected with a fixing plate 208, the limiting slide rail 206 and the fixing plate 208 are both fixedly installed on the workbench 201, a first bearing ring 209 is arranged at the left end of the drone body 1, a first traction rope 210 is fixedly connected to the outer wall of the first bearing ring 209, a first winding drum 211 is arranged at the end of the first traction rope 210 away from the first bearing ring 209, the first traction rope 210 is wound on the first winding drum 211, and a first driving motor 212 is arranged on the left side of the first winding drum 211, The transmission end of the first driving motor 212 is fixedly connected to the first winding drum 211, a second bearing ring 213 is provided at the right end of the drone body 1, a second traction rope 214 is fixedly connected to the outer wall of the second bearing ring 213, a second winding drum 215 is provided at one end of the second traction rope 214 away from the second bearing ring 213, the second traction rope 214 is wound on the second winding drum 215, a second driving motor 216 is provided on the right side of the second winding drum 215, and the transmission end of the second driving motor 216 is fixedly connected to the second winding drum 215;

[0033] See also Figure 1 , Figure 4 , Figure 5 , Figure 6 , Figure 7and Figure 8 Initially, before activation, the first drive motor 212 and the second drive motor 216 need to be powered and connected to the control terminal in advance. When activated, the snap-on fixing structure in the fixing mechanism 2 is activated. First, the unmanned aerial vehicle body 1 is placed on the first support platform 202 and the second support platform 203. The user then pushes the limit rod 205 so that the limit rod 205 is inserted into the limit sleeve 204 at the lower end of the unmanned aerial vehicle body 1, thereby fixing the unmanned aerial vehicle body 1 on the first support platform 202 and the second support platform 203 to achieve the fixed installation effect of the unmanned aerial vehicle body 1. After fixing the unmanned aerial vehicle body 1, the unmanned aerial vehicle body 1 can be statically detected. During the dynamic detection process, the limit rod 205 is removed, and the unmanned aerial vehicle body 1 is started by the remote control to make the unmanned aerial vehicle body 1 fly, and the unmanned aerial vehicle body 1 can be dynamically detected. , the rope-supporting limiting structure in the fixing mechanism 2 is activated, and a group of bearing rings, traction ropes, winding drums and driving motors are also provided at the front and rear ends of the unmanned aerial vehicle 1. The rope-supporting limiting structures at the left and right ends of the unmanned aerial vehicle 1 are combined to form a four-end traction structure. The four-end traction structure not only protects and limits the unmanned aerial vehicle 1, but also can simulate the load of the unmanned aerial vehicle 1. The first driving motor 212 and the second driving motor 216 control the downward pulling force of the first traction rope 210 and the second traction rope 214. Similarly, the driving motors at the front and rear ends of the unmanned aerial vehicle 1 control the downward pulling force of the corresponding traction ropes, thereby simulating the load of the unmanned aerial vehicle 1, and then performing detection and test operations on the unmanned aerial vehicle 1 in the loaded state. In addition, the four-end traction structure can also ensure the stability and reliability of the unmanned aerial vehicle 1 during the test work;

[0034] The fixing mechanism 2 adopts a snap-on fixing structure and a four-end traction structure. In the process of fixing and installing the unmanned aerial vehicle body 1, the snap-on fixing structure can effectively support and install the unmanned aerial vehicle body 1, ensure the installation stability of the unmanned aerial vehicle body 1, and also facilitate the detection and removal of the unmanned aerial vehicle body 1. The four-end traction structure is used to assist the testing mechanism 3 in performing the testing operation, which can not only prevent the unmanned aerial vehicle body 1 from accidentally flying around, but also facilitate the height positioning of the unmanned aerial vehicle body 1.

[0035] The test mechanism 3 includes a centrifugal fan 303, an air outlet pipe 304 and a first motion recorder 307. The air outlet pipe 304 is fixedly installed at the right end of the centrifugal fan 303. The first motion recorder 307 and the second motion recorder 308 are installed on the pipe wall of the air outlet pipe 304. The first motion recorder 307 is fixedly set on the pipe wall of the front end of the air outlet pipe 304. The test mechanism 3 also includes a fixing rod 301 and a drive motor 302. The drive motor 302 is set at the rear of the centrifugal fan 303. The transmission end of the drive motor 302 is connected to the centrifugal fan 303. The drive motor 302 is connected to the centrifugal fan 303. A fixing rod 301 is fixedly installed at the lower end of 02, and the fixing rod 301 is fixedly installed on the workbench 201. A connecting rod 305 is fixedly installed at the upper end of the centrifugal fan 303, and a monitoring camera 306 is installed at the upper end of the connecting rod 305. A second motion recorder 308 is fixedly installed on the pipe wall at the rear end of the air outlet pipe 304. A body bracket 309 is fixedly installed at the lower end of the centrifugal fan 303, and the body bracket 309 is fixedly installed on the workbench 201. Mounting seats 310 are provided on both the front and rear sides of the workbench 201, and a wind shielding bin 311 is provided above the mounting seat 310.

[0036] See also Figure 1 , Figure 3 , Figure 6 and Fig.10 ,observe Figure 3 and Figure 6 It can be seen that the first motion recorder 307 and the second motion recorder 308 are respectively embedded in the wall surface of the front end and the rear end of the air outlet duct 304. Fig.10 (It is a plane right view) It can be known that the first motion recorder 307 and the second motion recorder 308 are respectively fixed at the center point of the relative wall surface of the front end and the rear end of the tube body. Before activation, it is necessary to pre-connect the driving motor 302, the monitoring camera 306, the first motion recorder 307 and the second motion recorder 308 to the power supply and the control terminal, start the test mechanism 3 to simulate the wind test environment, keep the monitoring camera 306, the first motion recorder 307 and the second motion recorder 308 to be synchronously activated, directly observe and record the flight of the unmanned vehicle body 1, start the driving motor 302 to drive the centrifugal fan 303 to work, and the centrifugal fan 303 discharges air from the air outlet pipe 304 to form a blowing effect from left to right. The size of the wind force can be controlled to measure the flight conditions of the unmanned vehicle body 1 under different wind forces. Later, by comparing the detailed flight data of the unmanned vehicle body 1, a more detailed flight condition of the unmanned vehicle body 1 can be obtained;

[0037] The test mechanism 3 adopts a blowing structure and a recording structure. The blowing structure is used to produce a specified wind strength for testing the endurance and flight performance of the unmanned aerial vehicle 1. The recording structure adopts multiple recorders to observe the trajectory and record the flight status of the unmanned aerial vehicle 1 during the test, so as to facilitate the later analysis and calibration of the unmanned aerial vehicle 1.

[0038] The working principle of the utility model is as follows: first, the unmanned aerial vehicle body 1 is placed on the first support platform 202 and the second support platform 203, and then the limit rod 205 is pushed to insert the limit sleeve 204 at the lower end of the unmanned aerial vehicle body 1, and the unmanned aerial vehicle body 1 is fixedly installed on the first support platform 202 and the second support platform 203 through a snap-on fixing structure. During the static detection process, the unmanned aerial vehicle body 1 can be directly tested. During the dynamic detection process, the limit rod 205 is removed, and the unmanned aerial vehicle body 1 is started by the remote control to make it fly. At this time, the rope-supporting limit structure in the fixing mechanism 2 is activated, and a group of bearing rings, traction ropes, winding drums and driving motors are also provided at the front and rear ends of the unmanned aerial vehicle body 1. Combined with the rope-supporting limit structures at the left and right ends of the unmanned aerial vehicle body 1, a four-end traction structure is formed. The traction structure not only protects and limits the unmanned aerial vehicle 1, but also can simulate the load of the unmanned aerial vehicle 1. The downward pulling force of the first traction rope 210 and the second traction rope 214 is controlled by the first drive motor 212 and the second drive motor 216. Similarly, the downward pulling force of the corresponding traction rope is controlled by the front and rear end drive motors of the unmanned aerial vehicle 1 to simulate the load of the unmanned aerial vehicle 1, and then the unmanned aerial vehicle 1 in the loaded state is detected and tested. At the same time, the drive motor 302 of the test mechanism 3 drives the centrifugal fan 303 to work, and a blowing effect of a specified wind force is generated from the air outlet 304 to simulate the wind test environment. The monitoring camera 306, the first motion recorder 307 and the second motion recorder 308 observe and record the flight trajectory and state of the unmanned aerial vehicle 1 in real time.

[0039] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A fixed fixture for calibration and testing of unmanned aerial vehicles, comprising an unmanned aerial vehicle body (1), characterized in that: A fixing mechanism (2) and a testing mechanism (3) are arranged on the outside of the unmanned aerial vehicle (1); the fixing mechanism (2) is located below the unmanned aerial vehicle (1); the testing mechanism (3) is arranged on the left side of the unmanned aerial vehicle (1); the fixing mechanism (2) comprises a workbench (201), a first supporting platform (202), a second supporting platform (203), a limiting sleeve (204) and a limiting insertion rod (205); the limiting sleeve (204) is fixedly mounted on the lower end of the unmanned aerial vehicle (1); the first supporting platform (202) is arranged on the right side of the limiting sleeve (204); and the second supporting platform (203) is arranged on the left side of the limiting sleeve (204). 3), a limiting rod (205) is inserted into the interior of the limiting sleeve (204), a workbench (201) is fixedly mounted at the lower ends of the first support platform (202) and the second support platform (203), the testing mechanism (3) comprises a centrifugal fan (303), an air outlet pipe (304) and a first motion recorder (307), the air outlet pipe (304) is fixedly mounted at the right end of the centrifugal fan (303), a first motion recorder (307) and a second motion recorder (308) are mounted on the pipe wall of the air outlet pipe (304), and the first motion recorder (307) is fixedly arranged on the pipe wall of the front end of the air outlet pipe (304).

2. A fixed fixture for calibration and testing of unmanned aerial vehicles according to claim 1, characterized in that: The fixing mechanism (2) further comprises a limiting slide rail (206), a telescopic rod (207) and a fixing plate (208); the limiting slide rail (206) is arranged at the lower end of the limiting plug rod (205); the limiting plug rod (205) and the limiting slide rail (206) are in a limiting relationship; the front end of the limiting plug rod (205) is fixedly mounted with the telescopic rod (207); one end of the telescopic rod (207) away from the limiting plug rod (205) is fixedly connected with the fixing plate (208); the limiting slide rail (206) and the fixing plate (208) are both fixedly mounted on the workbench (201).

3. A fixed fixture for calibration and testing of unmanned aerial vehicles according to claim 2, characterized in that: A first bearing ring (209) is arranged at the left end of the unmanned aerial vehicle body (1); a first traction rope (210) is fixedly connected to the outer wall of the first bearing ring (209); a first wire reel (211) is arranged at one end of the first traction rope (210) away from the first bearing ring (209); the first traction rope (210) is wound on the first wire reel (211); a first drive motor (212) is arranged on the left side of the first wire reel (211); and a transmission end of the first drive motor (212) is fixedly connected to the first wire reel (211).

4. A fixed fixture for calibration and testing of unmanned aerial vehicles according to claim 3, characterized in that: A second bearing ring (213) is provided at the right end of the unmanned aerial vehicle body (1); a second traction rope (214) is fixedly connected to the outer wall of the second bearing ring (213); a second cable drum (215) is provided at one end of the second traction rope (214) away from the second bearing ring (213); the second traction rope (214) is wound on the second cable drum (215); a second drive motor (216) is provided on the right side of the second cable drum (215); and a transmission end of the second drive motor (216) is fixedly connected to the second cable drum (215).

5. The fixing device for calibration test of unmanned aerial vehicle according to claim 1, characterized in that: The testing mechanism (3) further comprises a fixing rod (301) and a driving motor (302); the driving motor (302) is arranged behind the centrifugal fan (303); a transmission end of the driving motor (302) is connected to the centrifugal fan (303); a fixing rod (301) is fixedly mounted at the lower end of the driving motor (302); and the fixing rod (301) is fixedly mounted on the workbench (201).

6. The fixing device for calibration test of unmanned aerial vehicle according to claim 5, characterized in that: A connecting rod (305) is fixedly mounted on the upper end of the centrifugal fan (303), and a monitoring camera (306) is mounted on the upper end of the connecting rod (305).

7. The fixing device for calibration and testing of unmanned aerial vehicles according to claim 1, characterized in that: The second motion recorder (308) is fixedly mounted on the pipe wall at the rear end of the air outlet pipe (304); a body support (309) is fixedly mounted on the lower end of the centrifugal fan (303); and the body support (309) is fixedly mounted on the workbench (201).

8. The fixing device for calibration and testing of unmanned aerial vehicles according to claim 1, characterized in that: Mounting seats (310) are provided on both the front and rear sides of the workbench (201), and a wind shielding bin (311) is provided above the mounting seats (310).

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