Unmanned aerial vehicle-mounted field intensity testing instrument

Abstract

The utility model discloses an unmanned aerial vehicle-mounted field intensity test instrument, and relates to the technical field of test equipment. The unmanned aerial vehicle comprises an unmanned aerial vehicle body and a field intensity tester body arranged below the unmanned aerial vehicle body. The field intensity tester body is placed on the upper surface of a horizontally arranged support plate; limiting flanges are vertically arranged on the four side edges of the supporting plate. The field intensity tester body is placed among the four limiting flanges; connecting lugs are arranged on the opposite side edges of the supporting plate side by side. First through holes are vertically formed in the upper surfaces of the two pairs of connecting lugs; bearing columns are inserted into the two pairs of first through holes in a sliding manner; the upper ends of the two pairs of bearing columns are fixed to the bottom wall of a shell of the unmanned aerial vehicle body. A positioning assembly used for locking the supporting plate to the bearing column is arranged below the unmanned aerial vehicle body. The field intensity tester is reasonable in structural design and convenient to use, and the use effect of the field intensity tester is effectively improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of testing equipment, in particular to an unmanned aerial vehicle (UAV)-borne field strength testing instrument. Background Art

[0002] When high-power shortwave and microwave transmitters on ships and aircraft platforms operate, the electromagnetic environment they generate can degrade or even malfunction other electronic equipment and affect personnel safety. To ensure the proper functioning of platform electronic equipment and the safety of personnel, platform electromagnetic field strength testing is essential.

[0003] In the existing technology, there are two methods for field strength testing: one is to manually test the field strength by walking around the test area with a tester holding a field strength tester, and the other is to use a drone to fly the field strength tester over the test area. The specific method for testing with a drone-mounted field strength tester is generally to directly bolt the field strength tester to the drone. Although this connection structure is simple, the installation and removal of the field strength tester is relatively time-consuming, thus affecting the efficiency of the field strength test. Therefore, it is urgent to develop a drone-mounted field strength tester to solve the above problems. Utility Model Content

[0004] The utility model provides an unmanned aerial vehicle (UAV)-mounted field strength test instrument, the purpose of which is to solve the technical problems raised in the above-mentioned background technology.

[0005] In order to solve the above technical problems, the present invention is achieved through the following technical solutions:

[0006] The utility model is a field strength test instrument carried by an unmanned aerial vehicle, comprising an unmanned aerial vehicle body and a field strength tester body arranged below the unmanned aerial vehicle body; the field strength tester body is placed on the upper surface of a horizontally arranged support plate; the four side edges of the support plate are vertically provided with limit flanges; the field strength tester body is placed between the four limit flanges; connecting ears are arranged side by side on opposite sides of the support plate; the upper surfaces of two pairs of the connecting ears are vertically provided with first through holes; supporting columns are slidably inserted into the two pairs of the first through holes; the upper ends of the two pairs of the supporting columns are fixed on the bottom wall of the casing of the unmanned aerial vehicle body; a positioning component for locking the support plate on the supporting column is installed below the unmanned aerial vehicle body.

[0007] As an optimal technical solution of the present invention, an elastic pad is horizontally arranged between the drone body and the field strength tester body; the elastic pad is fixed on the bottom wall of the drone body casing; and a plurality of second through holes are evenly distributed on the upper surface of the elastic pad.

[0008] As a preferred technical solution of the present invention, an elastic detour portion is provided at the connection between the limiting flange and the support plate.

[0009] As a preferred technical solution of the present invention, the positioning assembly includes a pair of protrusions fixed side by side on the lower surface of the support plate and a pair of mounting posts arranged side by side and horizontally between the two protrusions; the opposite surfaces of the two protrusions are provided with accommodating holes; the two ends of the two mounting posts are respectively fixed on the lower ends of the two pairs of supporting posts; the two mounting posts are rotatably connected with a flip block; the two flip blocks are interspersed with a positioning post perpendicular to the mounting post; when the two positioning posts are horizontally arranged above the two mounting posts, one end of the two positioning posts slides and is inserted into the two accommodating holes respectively.

[0010] As an optimal technical solution of the present invention, the two positioning columns are respectively slidably matched with the two flip blocks; the other ends of the two positioning columns are fixed with pull rings; the two positioning columns are each provided with a tensioning spring; the two ends of the tensioning spring are respectively fixed on the adjacent flip blocks and pull rings.

[0011] The utility model has the following beneficial effects:

[0012] The utility model places the field strength tester body on the upper surface of the support plate, uses four limiting flanges to limit the circumference of the field strength tester body, and then slides the support plate close to the drone body by the supporting column in the first through hole, so that the distance between the bottom wall of the casing of the drone body and the limiting flange is smaller than the thickness of the field strength tester body, and then uses the positioning component to lock the support plate on the supporting column, so that the field strength tester body is stably installed on the drone body, which not only shortens the installation or disassembly time of the field strength tester body, but also ensures the installation stability of the field strength tester body on the drone body, and effectively ensures the field strength test efficiency.

[0013] Of course, any product implementing the present invention does not necessarily need to achieve all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. 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 creative work.

[0015] Figure 1 The utility model is a structural schematic diagram of an unmanned aerial vehicle-mounted field strength test instrument.

[0016] Figure 2This is a schematic diagram of the structure of the connection between the drone body, the field strength tester body and the support plate of the utility model.

[0017] Figure 3 This is a schematic structural diagram of the connection between the field strength tester body, support plate and bearing column of the present utility model.

[0018] Figure 4 This is a structural diagram of the support plate of the present invention.

[0019] Figure 5 It is a schematic structural diagram of the connection between the support plate and the positioning assembly of the present invention.

[0020] Figure 6 It is a structural schematic diagram of the positioning component of the present utility model.

[0021] In the accompanying drawings, the components represented by the reference numerals are as follows:

[0022] 1-UAV body, 2-field strength tester body, 3-support plate, 4-bearing column, 5-positioning assembly, 6-elastic pad, 301-limiting flange, 302-connecting ear, 303-first through hole, 304-elastic detour, 501-bump, 502-mounting column, 503-accommodation hole, 504-flip block, 505-positioning column, 506-pull ring, 507-tension spring, 601-second through hole. DETAILED DESCRIPTION

[0023] The following will be combined with the accompanying drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0024] Example 1:

[0025] See also Figure 1-4As shown, the utility model is a field strength test instrument carried by an unmanned aerial vehicle, comprising a unmanned aerial vehicle body 1 and a field strength tester body 2 arranged below the unmanned aerial vehicle body 1; the unmanned aerial vehicle body 1 and the field strength tester body 2 are both conventional structures in this field; the field strength tester body 2 is placed on the upper surface of a horizontally arranged support plate 3; the four side edges of the support plate 3 are integrally formed with vertically arranged limit flanges 301; the field strength tester body 2 is placed between the four limit flanges 301; one opposite side edge of the support plate 3 is integrally formed with connecting ears 302 side by side; the upper surfaces of the two pairs of connecting ears 302 are vertically opened with first through holes 303; the two pairs of first through holes 303 are slidably inserted with supporting columns 4; the upper ends of the two pairs of supporting columns 4 are fixed on the bottom wall of the casing of the unmanned aerial vehicle body 1; a positioning component 5 for locking the support plate 3 on the supporting column 4 is installed below the unmanned aerial vehicle body 1. During use, the field strength tester body 2 is placed on the upper surface of the support plate 3, and the four limiting flanges 301 are used to limit the peripheral side of the field strength tester body 2. The supporting column 4 is then slid in the first through hole 303 to move the supporting plate 3 close to the drone body 1, so that the distance between the bottom wall of the casing of the drone body 1 and the limiting flange 301 is less than the thickness of the field strength tester body 2. The positioning component 5 is then used to lock the supporting plate 3 on the supporting column 4, so that the field strength tester body 2 is stably installed on the drone body 1, which not only shortens the installation or disassembly time of the field strength tester body 2, but also ensures the installation stability of the field strength tester body 2 on the drone body 1, effectively ensuring the field strength test efficiency.

[0026] Among them Figure 2-3 As shown, a rubber elastic pad 6 is horizontally positioned between the drone body 1 and the field strength tester body 2. The elastic pad 6 is bonded to the bottom wall of the drone body 1. Multiple second through-holes 601 are evenly distributed on the upper surface of the elastic pad 6. During use, the upper surface of the field strength tester body 2 is aligned with the lower surface of the elastic pad 6, thereby improving the positioning of the field strength tester body 2. Furthermore, the multiple second through-holes 601 evenly distributed on the upper surface of the elastic pad 6 not only ensure heat dissipation from the field strength tester body 2 but also enhance the elasticity of the elastic pad 6.

[0027] Among them Figure 4 As shown, an elastic detour portion 304 is provided at the connection between the limiting flange 301 and the support plate 3. Providing the elastic detour portion 304 at the connection between the limiting flange 301 and the support plate 3 not only improves the bendability of the limiting flange 301 but also effectively ensures the limiting effect of the limiting flange 301 on the field strength tester body 2.

[0028] Example 2:

[0029] Based on Example 1 Figure 3and Figure 5-6 As shown, the positioning assembly 5 includes a pair of protrusions 501 welded side by side on the lower surface of the support plate 3 and a pair of mounting posts 502 arranged side by side and horizontally between the two protrusions 501; the opposite surfaces of the two protrusions 501 are provided with accommodating holes 503; the two ends of the two mounting posts 502 are respectively fixed to the lower ends of the two pairs of supporting posts 4; the two mounting posts 502 are rotatably connected to the flip blocks 504; the two flip blocks 504 are interspersed with positioning holes perpendicular to the mounting posts 502. The two positioning posts 505 are arranged horizontally above the two mounting posts 502, and one end of each positioning post 505 slides through the two receiving holes 503. The two positioning posts 505 slide in engagement with the two flip blocks 504. A pull ring 506 is fixed to the other end of each positioning post 505. A tensioning spring 507 is sleeved on each positioning post 505. The ends of the tensioning spring 507 are respectively fixed to the adjacent flip blocks 504 and the pull ring 506. During use, after the upper and lower surfaces of the field strength tester body 2 are respectively aligned with the lower surface of the elastic pad 6 and the upper surface of the support plate 3, the flip block 504 is rotated to align the receiving holes 503 and the positioning posts 505 coaxially. Then, under the elastic action of the tensioning spring 507, one end of the positioning post 505 slides through the corresponding receiving hole 503, thereby locking the support plate 3 in position and effectively improving the efficiency of installing or removing the field strength tester body 2.

[0030] The preferred embodiments of the present invention disclosed above are intended only to help illustrate the present invention. The preferred embodiments do not describe all details in detail, nor do they limit the present invention to the specific embodiments described. Obviously, many modifications and variations are possible based on the contents of this specification. These embodiments are selected and described in detail in this specification to better explain the principles and practical applications of the present invention, thereby enabling those skilled in the art to better understand and utilize the present invention. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A field strength test instrument carried by an unmanned aerial vehicle, comprising an unmanned aerial vehicle body (1) and a field strength tester body (2) arranged below the unmanned aerial vehicle body (1); characterized in that: The field strength tester body (2) is placed on the upper surface of a horizontally arranged support plate (3); the four side edges of the support plate (3) are vertically provided with limit flanges (301); the field strength tester body (2) is placed between the four limit flanges (301); one opposite side edge of the support plate (3) is provided with connecting ears (302) in parallel; the upper surfaces of two pairs of the connecting ears (302) are vertically provided with first through holes (303); the two pairs of the first through holes (303) are slidably inserted with supporting columns (4); the upper ends of the two pairs of the supporting columns (4) are fixed on the bottom wall of the casing of the drone body (1); and a positioning component (5) for locking the support plate (3) on the supporting columns (4) is installed below the drone body (1).

2. The UAV-mounted field strength test instrument according to claim 1, characterized in that: An elastic pad (6) is horizontally arranged between the drone body (1) and the field strength tester body (2); the elastic pad (6) is fixed on the bottom wall of the casing of the drone body (1).

3. The UAV-mounted field strength tester according to claim 2, characterized in that: A plurality of second through holes (601) are evenly distributed on the upper surface of the elastic pad (6).

4. The UAV-mounted field strength test instrument according to claim 2 or 3, characterized in that: An elastic detour portion (304) is provided at the connection between the limiting flange (301) and the support plate (3).

5. The UAV-mounted field strength test instrument according to claim 4, characterized in that: The positioning assembly (5) comprises a pair of protrusions (501) fixed side by side on the lower surface of the support plate (3) and a pair of mounting posts (502) arranged side by side and horizontally between the two protrusions (501); the opposite surfaces of the two protrusions (501) are provided with accommodating holes (503); the two ends of the two mounting posts (502) are respectively fixed on the lower ends of the two pairs of bearing posts (4); the two mounting posts (502) are rotatably connected with a flip block (504); the two flip blocks (504) are interspersed with a positioning post (505) perpendicular to the mounting post (502); when the two positioning posts (505) are horizontally arranged above the two mounting posts (502), one end of the two positioning posts (505) slides and is inserted into the two accommodating holes (503) respectively.

6. The UAV-mounted field strength tester according to claim 5, characterized in that: The two positioning posts (505) are respectively slidably matched with the two flip blocks (504); the other ends of the two positioning posts (505) are both fixed with pull rings (506).

7. The UAV-mounted field strength tester according to claim 6, characterized in that: A tensioning spring (507) is sleeved on each of the two positioning posts (505); two ends of the tensioning spring (507) are respectively fixed on the adjacent turning block (504) and the pull ring (506).

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