An unmanned aerial vehicle flight data acquisition device

Abstract

The utility model discloses a kind of unmanned aerial vehicle flight data acquisition devices, it is related to unmanned aerial vehicle data acquisition technical field.The utility model includes gyroscopic assembly, range finder, lateral wind speed component, acceleration detection component and mounting seat, mounting groove is set in the lower end of mounting seat, gyroscopic assembly is set in mounting groove, range finder is set in gyroscopic assembly, acceleration detection component is set in the upper end surface of range finder, lateral wind speed component is set in the upper end surface of mounting seat.The utility model is by mounting seat setting in unmanned aerial vehicle bottom, when unmanned aerial vehicle climbs or dives, body is along with the inclination of flight angle, range finder is always kept perpendicular to ground under the action of gyroscopic assembly, ensure the detection height of ground accurate;The lateral wind speed of both sides of unmanned aerial vehicle is detected and collected by lateral wind speed component, the angle of unmanned aerial vehicle roll is recorded and collected by gyroscopic assembly and sensor, to provide data accumulation for the influence of lateral wind to the flight attitude of unmanned aerial vehicle.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) data acquisition technology, and in particular relates to a UAV flight data acquisition device. Background Technology

[0002] During flight, drones need to collect and record data such as altitude and speed, and save this data for flight data accumulation. This facilitates flight status evaluation and performance parameter adjustments. Drone altitude includes elevation and ground clearance. Ground clearance is a crucial data point for detecting terrain. However, when a rangefinder is mounted on the bottom of the drone, it may not be perpendicular to the ground during climbs or dives, leading to errors in the detected ground clearance. Furthermore, crosswinds affect the drone's flight attitude, so crosswind speed is also a critical parameter that needs to be recorded during flight.

[0003] To address these issues, we provide a drone flight data acquisition device. Utility Model Content

[0004] The purpose of this invention is to provide a drone flight data acquisition device. A gyroscope assembly is installed in a mounting slot at the bottom of the mounting base, and a rangefinder is placed within the gyroscope assembly. The mounting base is then placed at the bottom of the drone. When the drone climbs or dives, its body tilts with the flight angle. Under the action of the gyroscope assembly, the rangefinder remains vertically aligned with the ground, ensuring accurate height detection. Furthermore, a lateral wind speed assembly is installed on the mounting base to detect and collect the crosswind speeds on both sides of the drone. When the drone encounters a crosswind, the tilt angle caused by the crosswind is recorded by the gyroscope assembly and sensors, thus providing data accumulation on the impact of crosswinds on the drone's flight attitude.

[0005] To solve the above-mentioned technical problems, this utility model is achieved through the following technical solution:

[0006] This utility model is a drone flight data acquisition device, including a gyroscope assembly, a rangefinder, a lateral wind speed assembly, an acceleration detection assembly, and a mounting base. The lower end of the mounting base has a mounting groove, the gyroscope assembly is disposed in the mounting groove, the rangefinder is disposed in the gyroscope assembly, the acceleration detection assembly is disposed on the upper surface of the rangefinder, and the lateral wind speed assembly is disposed on the upper surface of the mounting base.

[0007] A further feature of this invention is that the gyroscope assembly includes a horizontal axis ring and a vertical axis ring. The horizontal axis ring is horizontally rotatably mounted in the mounting groove, and the vertical axis ring is horizontally mounted in the horizontal axis ring. The rangefinder is horizontally rotatably mounted in the vertical axis ring.

[0008] A further feature of this invention is that a hemispherical transparent windproof cover is fixedly installed at the lower end of the mounting groove, and the windproof cover covers the lower outer side of the gyroscope assembly.

[0009] A further feature of this invention is that the accelerated detection component includes a conductive slider and a slider tube. The slider tube is horizontally positioned on the upper surface of the rangefinder. The conductive slider is slidably fitted inside the slider tube. A conductive rod is fixedly mounted on each of the two ends of the conductive slider. The two conductive rods slide through the two end faces of the slider tube. A conductive sleeve is fixedly mounted on each of the two outer end faces of the slider tube. The two conductive rods slidely fitted inside the two conductive sleeves. The conductive sleeves are connected to the rangefinder signal via wires. The slider tube is also connected to the rangefinder signal via wires.

[0010] A further feature of this invention is that a return spring is fixedly connected to each end of the conductive slide, and the end of the return spring away from the conductive slide is fixedly connected to the inner top surface of the slide tube.

[0011] A further feature of this invention is that insulating ceramic rings are fixedly fitted into the openings at both ends of the sliding tube, and conductive sliding rods at both ends are slidably fitted into the insulating ceramic rings at both ends.

[0012] A further feature of this invention is that the lateral wind speed assembly includes two air inlet pipes and two anemometers, with the two anemometers respectively installed inside the two air inlet pipes, and the ends of the two air inlet pipes with the anemometers installed being far apart from each other.

[0013] This utility model has the following beneficial effects:

[0014] 1. This utility model sets a gyroscope assembly in the mounting groove at the bottom of the mounting base, places the rangefinder in the gyroscope assembly, and places the mounting base at the bottom of the drone. When the drone climbs or dives, the drone body tilts with the flight angle. Under the action of the gyroscope assembly, the rangefinder always remains vertically facing the ground, thereby ensuring accurate detection of the ground height.

[0015] 2. This utility model sets up a lateral wind speed component on the mounting base, which detects and collects the lateral wind speed on both sides of the drone. When the drone encounters a lateral wind, the tilt of the drone's flight attitude is recorded by the gyroscope component and sensors, thereby providing data accumulation on the influence of lateral wind on the drone's flight attitude. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 A schematic diagram of a drone flight data acquisition device;

[0018] Figure 2 This is a schematic diagram of the structure of the gyroscope assembly and the rangefinder.

[0019] Figure 3 A schematic diagram showing the disassembly of the detection components to accelerate the detection process;

[0020] Figure 4 A side sectional view to accelerate the detection of components;

[0021] Figure 5 This is a structural diagram of the lateral wind speed assembly and its mounting base;

[0022] The attached diagram lists the components represented by each number as follows:

[0023] 1-Gyroscope assembly, 101-Horizontal axis ring, 102-Vertical axis ring, 2-Radarmeter, 3-Lateral wind speed assembly, 301-Air inlet pipe, 302-Anemometer, 4-Acceleration detection assembly, 401-Conductive slider, 401a-Conductive slider rod, 401a-1-Conductive sleeve, 401b-Reset spring, 402-Slider tube, 402a-Insulating ceramic ring, 5-Mounting base, 501-Mounting groove, 501a-Windproof cover. Detailed Implementation

[0024] 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 embodiments of the present utility model, and not all embodiments. 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 protection scope of the present utility model. Example 1

[0025] Please see Figure 1 and Figure 2This utility model is a drone flight data acquisition device, including a gyroscope assembly 1, a rangefinder 2, a crosswind assembly 3, an acceleration detection assembly 4, and a mounting base 5. The gyroscope assembly 1 is placed in the mounting groove 501 at the bottom of the mounting base 5, the rangefinder 2 is placed inside the gyroscope assembly 1, and the mounting base 5 is placed at the bottom of the drone. When the drone climbs or dives, the drone's body tilts with the flight angle. Under the action of the gyroscope assembly 1, the rangefinder 2 remains vertically facing the ground, thus ensuring accurate detection of the ground altitude. The crosswind assembly 3 is installed on the mounting base 5 to detect and collect the crosswind speeds on both sides of the drone. When the drone encounters crosswinds, the tilt angle of the drone's flight attitude is recorded by the gyroscope assembly 1 and sensors, thus providing data accumulation on the influence of crosswinds on the drone's flight attitude.

[0026] Specifically, the lower end of the mounting base 5 has a mounting groove 501, the gyroscope assembly 1 is set in the mounting groove 501, the rangefinder 2 is set in the gyroscope assembly 1, the acceleration detection assembly 4 is set on the upper surface of the rangefinder 2, and the lateral wind speed assembly 3 is set on the upper surface of the mounting base 5.

[0027] Furthermore, the gyroscope assembly 1 includes a horizontal axis ring 101 and a vertical axis ring 102. The horizontal axis ring 101 is horizontally rotatably mounted in the mounting groove 501, and the vertical axis ring 102 is horizontally mounted in the horizontal axis ring 101. The rangefinder 2 is horizontally rotatably mounted in the vertical axis ring 102. When the UAV climbs or dives, the horizontal axis ring 101, which is horizontally rotatably mounted in the mounting groove 501, remains horizontal, so that the rangefinder 2 in the vertical axis ring 102 remains perpendicular to the ground.

[0028] Furthermore, a hemispherical transparent wind shield 501a is fixedly installed at the lower end of the mounting slot 501. The wind shield 501a covers the outer side of the lower end of the gyroscope assembly 1 to prevent airflow from affecting the flight angle of the rangefinder during the flight of the UAV, thereby causing errors in the rangefinder.

[0029] The operation process in this embodiment is as follows:

[0030] When the drone climbs or dives, the drone's body tilts with the flight angle, and the horizontally rotating horizontal ring 101 installed in the mounting slot 501 remains horizontal, so that the rangefinder 2 in the vertical ring 102 remains perpendicular to the ground, thereby ensuring accurate detection of the ground height. Example 2

[0031] Please see Figures 1 to 5Based on Example 1, the acceleration detection component 4 includes a conductive slider 401 and a slider tube 402, and the lateral wind speed component 3 includes two air inlet pipes 301 and two anemometers 302. By pointing the two air inlet pipes 301 toward the two sides of the UAV respectively, and placing the two anemometers 302 in the two air inlet pipes 301 respectively, when the UAV encounters a lateral wind, the anemometer 302 in the corresponding direction records the wind speed of the lateral wind, and combined with the gyroscope component 1 to collect the tilt angle of the UAV, thereby collecting the tilt angle that occurs when the UAV encounters lateral winds of various wind speeds.

[0032] Specifically, the sliding tube 402 is horizontally positioned on the upper end face of the rangefinder 2. The conductive sliding plug 401 is slidably sleeved in the sliding tube 402. A conductive sliding rod 401a is fixedly installed on each end face of the conductive sliding plug 401. The two conductive sliding rods 401a slide through the two end faces of the sliding tube 402. A conductive sleeve 401a-1 is fixedly installed on the outer end face of each end of the sliding tube 402. The two conductive sliding rods 401a slide in the two conductive sleeves 401a-1. The conductive sleeves 401a-1 are connected to the rangefinder 2 via wires, and the sliding tube 402 is connected to the rangefinder 2 via wires.

[0033] Furthermore, a return spring 401b is fixedly connected to each end of the conductive slider 401, and the end of the return spring 401b away from the conductive slider 401 is fixedly connected to the inner top surface of the slider tube 402.

[0034] Furthermore, insulating ceramic rings 402a are fixedly sleeved in the openings at both ends of the sliding tube 402, and conductive sliding rods 401a at both ends are slidably sleeved in the insulating ceramic rings 402a. When the UAV accelerates, the conductive sliding plug 401 moves against the force of the return spring 401b, causing the contact position of the conductive sliding rod 401a in the conductive sleeve 401a-1 to change, forming a variable resistor voltage divider circuit. The voltage signal corresponds to the acceleration value, and combined with the tilt angle data of the UAV collected by the gyroscope component 1, the influence of acceleration on the flight attitude of the UAV is recorded.

[0035] Furthermore, two anemometers 302 are respectively installed inside two air inlet pipes 301, with the ends of the two air inlet pipes 301 where the anemometers 302 are installed being far apart from each other.

[0036] The operation process in this embodiment is as follows:

[0037] When the drone encounters a crosswind, the anemometer 302 in the corresponding direction records the crosswind speed and, together with the gyroscope component 1, collects the drone's tilt angle, thereby collecting the tilt angle that occurs when the drone encounters crosswinds of various speeds.

[0038] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

Claims

1. A UAV flight data acquisition device, comprising a gyroscope assembly (1), a rangefinder (2), a lateral wind speed assembly (3), an acceleration detection assembly (4), and a mounting base (5), characterized in that: The mounting base (5) has a mounting groove (501) at its lower end. The gyroscope assembly (1) is located in the mounting groove (501). The rangefinder (2) is located in the gyroscope assembly (1). The acceleration detection assembly (4) is located on the upper surface of the rangefinder (2). The lateral wind speed assembly (3) is located on the upper surface of the mounting base (5).

2. The UAV flight data acquisition device according to claim 1, characterized in that: The gyroscope assembly (1) includes a horizontal ring (101) and a vertical ring (102). The horizontal ring (101) is horizontally rotatably mounted in the mounting groove (501), and the vertical ring (102) is vertically rotatably mounted in the horizontal ring (101). The rangefinder (2) is horizontally rotatably mounted in the vertical ring (102).

3. The UAV flight data acquisition device according to claim 2, characterized in that: A hemispherical transparent windproof cover (501a) is fixedly installed at the lower end of the mounting slot (501), and the windproof cover (501a) covers the lower outer side of the gyroscope assembly (1).

4. The UAV flight data acquisition device according to claim 1, characterized in that: The acceleration detection component (4) includes a conductive slider (401) and a slider tube (402). The slider tube (402) is horizontally arranged on the upper end face of the rangefinder (2). The conductive slider (401) is slidably sleeved in the slider tube (402). A conductive slider (401a) is fixedly provided on each end face of the conductive slider (401). The conductive sliders (401a) at both ends slide through the end faces of the slider tube (402). A conductive sleeve (401a-1) is fixedly provided on the outer end face of each end of the slider tube (402). The conductive sliders (401a) at both ends slidely sleeved in the two conductive sleeves (401a-1). The conductive sleeves (401a-1) are connected to the rangefinder (2) via wires. The slider tube (402) is connected to the rangefinder (2) via wires.

5. The UAV flight data acquisition device according to claim 4, characterized in that: A return spring (401b) is fixedly connected to each end of the conductive slide (401), and the end of the return spring (401b) away from the conductive slide (401) is fixedly connected to the inner top surface of the slide tube (402).

6. The UAV flight data acquisition device according to claim 5, characterized in that: Insulating ceramic rings (402a) are fixedly sleeved in the openings at both ends of the sliding tube (402), and the conductive sliding rods (401a) at both ends are slidably sleeved in the insulating ceramic rings (402a) at both ends.

7. The UAV flight data acquisition device according to claim 6, characterized in that: The lateral wind speed component (3) includes two air inlet pipes (301) and two anemometers (302). The two anemometers (302) are respectively installed inside the two air inlet pipes (301), and the ends of the two air inlet pipes (301) where the anemometers (302) are installed are far apart from each other.

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