CN220843001U - Unmanned aerial vehicle radar nacelle structure - Google Patents
Unmanned aerial vehicle radar nacelle structure Download PDFInfo
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- CN220843001U CN220843001U CN202321746619.8U CN202321746619U CN220843001U CN 220843001 U CN220843001 U CN 220843001U CN 202321746619 U CN202321746619 U CN 202321746619U CN 220843001 U CN220843001 U CN 220843001U
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- fixedly connected
- heat dissipation
- aerial vehicle
- unmanned aerial
- nacelle
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- 230000017525 heat dissipation Effects 0.000 claims abstract description 43
- 238000009434 installation Methods 0.000 claims abstract description 15
- 230000007246 mechanism Effects 0.000 claims abstract description 12
- 238000010521 absorption reaction Methods 0.000 claims abstract description 10
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 18
- 230000000670 limiting effect Effects 0.000 claims description 15
- 229910052742 iron Inorganic materials 0.000 claims description 9
- 239000003351 stiffener Substances 0.000 claims description 9
- 238000001816 cooling Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 10
- 230000009471 action Effects 0.000 abstract description 6
- 230000003014 reinforcing effect Effects 0.000 description 5
- 230000003139 buffering effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 210000001503 joint Anatomy 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- 239000004020 conductor Substances 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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Abstract
The utility model discloses an unmanned aerial vehicle radar pod structure, which relates to the technical field of unmanned aerial vehicle radar pods and comprises a pod body and a positioning bracket, wherein an installation assembly is connected in a sliding manner in the positioning bracket, the lower end of the installation assembly is fixedly connected with the upper surface of the pod body, the front surface of the pod body is fixedly connected with a heat dissipation mechanism, a vent is formed in the side surface of the pod body, a base is arranged at the bottom of the pod body, and an adjusting knob is movably connected to the surface of the positioning bracket. According to the utility model, the heat absorption block absorbs the internal heat, the heat is enabled to be in the transverse groove under the action of the T-shaped guide rod, and the heat is discharged under the action of the heat dissipation through groove and the heat dissipation plate, so that the problem that the heat generated by radar equipment in the nacelle after working is slowly dissipated through the heat dissipation holes in the existing unmanned aerial vehicle radar nacelle structure is solved, and the effect of accelerating the internal heat dissipation degree is achieved.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicle radar pods, in particular to an unmanned aerial vehicle radar pod structure.
Background
Radar equipment is important equipment for unmanned aerial vehicle to carry out flight operation, and is often required to be installed and disassembled, and a mechanism for supporting rapid installation and disassembly is required to be arranged; when the unmanned aerial vehicle performs flight operation, accidents can occur, so that the unmanned aerial vehicle crashes, radar equipment can be damaged, and an operation task can not be continued; radar equipment is expensive and maintenance costs are high. The radar equipment needs a protection device; the utility model provides a many rotor unmanned aerial vehicle often have shake and vibration phenomenon when carrying out flight operation, but radar equipment needs to work under the relatively stable condition, needs to install vibration damper between radar equipment and the unmanned aerial vehicle, according to the circumstances of actual unmanned aerial vehicle flight operation, needs many rotor unmanned aerial vehicle's radar installation and protection device to just appear many rotor unmanned aerial vehicle radar nacelle structure and satisfy this demand.
According to patent publication number CN217022911U, a multi-rotor unmanned aerial vehicle radar nacelle structure in the technical field of unmanned aerial vehicle radar nacelle is disclosed, comprising a nacelle body, a mounting assembly, a docking assembly and two positioning brackets; the installation component fixed mounting is at the top of nacelle body, and the butt joint subassembly cooperates with support installation component mutually, and two locating brackets are installed at the both ends at butt joint subassembly top respectively. The whole process of the utility model can complete the installation and the disassembly of the nacelle body only by rotating the adjusting knob, and the operation is very convenient.
The following problems exist with respect to the prior art of publication number CN 217022911U:
in the existing unmanned aerial vehicle radar nacelle structure, the problem that the heat dissipation is slow due to the fact that the heat generated by radar equipment in the nacelle after working cannot be quickly dissipated is caused by the fact that the heat dissipation is carried out through the heat dissipation holes; meanwhile, as the bottom of the nacelle is not provided with a buffer structure, the problem that the surface of the nacelle is damaged due to vibration generated when the unmanned aerial vehicle falls down to the nacelle to be contacted with the ground when accidents happen is solved.
Disclosure of utility model
The utility model provides an unmanned aerial vehicle radar nacelle structure for solving the problems in the background art.
In order to solve the technical problems, the utility model adopts the following technical scheme:
The utility model provides an unmanned aerial vehicle radar nacelle structure, includes nacelle body and locating support, the inside sliding connection of locating support has the installation component, the lower extreme of installation component and the upper surface fixed connection of nacelle body, the front fixedly connected with cooling body of nacelle body, the vent has been seted up to the side of nacelle body, the bottom of nacelle body is provided with the base, the surface swing joint of locating support has adjust knob.
The heat dissipation mechanism comprises a heat dissipation mechanism body, wherein the heat dissipation mechanism body is characterized in that an installation groove is formed in the middle of the heat dissipation mechanism body, a fixing frame is fixedly connected to the inner wall of the installation groove body, a heat absorption block is fixedly connected to one end of the fixing frame, transverse grooves are formed in two sides of the installation groove body, T-shaped guide rods are arranged in the transverse grooves, one ends of the T-shaped guide rods extend to the inside of the installation groove body, and one ends of the T-shaped guide rods are fixedly connected with the surface of the heat absorption block.
The technical scheme of the utility model is further improved as follows: and one side of the transverse groove is provided with a heat dissipation through groove, and the inside of the heat dissipation through groove is fixedly connected with a heat dissipation plate.
By adopting the technical scheme, the transverse grooves, the radiating through grooves and the radiating plates are matched with each other in the scheme, so that the effect of radiating the internal heat is achieved.
The technical scheme of the utility model is further improved as follows: the lower extreme of nacelle body extends to the inside of base, the inside sliding connection of surface and the base of nacelle body, the both sides fixedly connected with dog of nacelle body, the lower surface fixedly connected with iron sheet of base.
By adopting the technical scheme, the stop block is arranged in the scheme to prevent the phenomenon of detachment due to the position limiting effect, and the iron sheet is arranged to prevent the detachment.
The technical scheme of the utility model is further improved as follows: one side of dog is provided with the bracing piece, the upper end and the nacelle body bottom fixed connection of bracing piece, the lower extreme of bracing piece is provided with the sleeve, telescopic bottom and the bottom fixed connection of base inner chamber, telescopic both sides fixedly connected with fixed block, the upper surface fixedly connected with spring of fixed block, the upper end and the bottom fixed connection of nacelle body of spring, the bracing piece is in the inside of spring.
By adopting the technical scheme, the supporting rod, the sleeve, the fixed block and the spring are matched with each other in the scheme, so that the buffer effect is achieved.
The technical scheme of the utility model is further improved as follows: one side fixedly connected with stiffener of fixed block, the middle part of stiffener and the bottom fixed connection of base inner chamber, the upper end of stiffener is provided with the plate, the upper surface and the nacelle body bottom fixed connection of plate.
By adopting the technical proposal, the fixing effect on the sleeve is enhanced through the arrangement of the reinforcing rod,
The technical scheme of the utility model is further improved as follows: the inside elastic ring that is provided with of telescopic, the upper end overlap joint of elastic ring has the limiting plate, the upper surface of limiting plate and the bottom fixed connection of bracing piece, the both ends and the telescopic inside sliding connection of limiting plate, the surface and the telescopic inside sliding connection of bracing piece.
By adopting the technical scheme, the elastic rings and the limiting plates are matched with each other in the scheme, so that the phenomenon of extrusion is enhanced and the buffering effect is enhanced.
By adopting the technical scheme, compared with the prior art, the utility model has the following technical progress:
1. The utility model provides an unmanned aerial vehicle radar nacelle structure, which adopts the mutual matching of a mounting groove, a fixing frame, a heat absorption block, a transverse groove, a T-shaped guide rod, a heat dissipation through groove and a heat dissipation plate, absorbs internal heat through the heat absorption block, ensures that the heat is in the transverse groove through the action of the T-shaped guide rod, and discharges the heat through the action of the heat dissipation through groove and the heat dissipation plate, thereby solving the problem that the heat dissipation of the radar equipment in the nacelle is slow after working in the existing unmanned aerial vehicle radar nacelle structure through the heat dissipation hole and achieving the effect of accelerating the internal heat dissipation degree.
2. The utility model provides an unmanned aerial vehicle radar nacelle structure, which adopts the mutual matching of a stop block, a sleeve, a fixed block, a supporting rod, a spring, a reinforcing rod, a plate and an iron sheet, when an unmanned aerial vehicle accidentally drops, the iron sheet in a base is contacted with the ground, the base slides upwards on the surface of a nacelle body and extrudes the supporting rod, so that the supporting rod is contracted in the sleeve, and meanwhile, the spring is extruded so as to buffer the nacelle body, the problem that the surface of the nacelle is damaged due to the vibration generated by the contact of the unmanned aerial vehicle dropping nacelle with the ground when the accident happens is solved, and the effect of protecting the surface of the nacelle body is achieved.
Drawings
FIG. 1 is a schematic diagram of the structure of the present utility model;
FIG. 2 is a schematic diagram of a front cross-sectional structure of a heat dissipating mechanism according to the present utility model;
FIG. 3 is a schematic view of a front cross-sectional structure of a base of the present utility model;
fig. 4 is a schematic view of the internal cross-section of the sleeve according to the present utility model.
In the figure: 1. a nacelle body; 2. a positioning bracket; 3. an adjustment knob; 4. a mounting assembly; 5. a heat dissipation mechanism; 51. a mounting groove; 52. a fixing frame; 53. a heat absorbing block; 54. a transverse groove; 55. a T-shaped guide rod; 56. a heat dissipation through groove; 57. a heat dissipation plate; 6. a base; 61. a stop block; 62. a sleeve; 621. a limiting plate; 622. an elastic ring; 63. a fixed block; 64. a support rod; 65. a spring; 66. a reinforcing rod; 67. a plate; 68. iron sheet; 7. and (5) a ventilation opening.
Detailed Description
The utility model is further illustrated by the following examples:
Example 1
As shown in fig. 1-4, the utility model provides an unmanned aerial vehicle radar nacelle structure, which comprises a nacelle body 1 and a positioning bracket 2, wherein a mounting assembly 4 is connected in a sliding manner in the positioning bracket 2, the lower end of the mounting assembly 4 is fixedly connected with the upper surface of the nacelle body 1, a heat dissipation mechanism 5 is fixedly connected to the front surface of the nacelle body 1, a ventilation opening 7 is formed in the side surface of the nacelle body 1, a base 6 is arranged at the bottom of the nacelle body 1, an adjusting knob 3 is movably connected to the surface of the positioning bracket 2, a mounting groove 51 is formed in the middle of the heat dissipation mechanism 5, a fixing frame 52 is fixedly connected to the inner wall of the mounting groove 51, one end of the fixing frame 52 is fixedly connected with a heat absorption block 53, transverse grooves 54 are formed in two sides of the mounting groove 51, T-shaped guide rods 55 are arranged in the inner parts of the transverse grooves 54, one ends of the T-shaped guide rods 55 extend to the inner parts of the mounting groove 51, one ends of the T-shaped guide rods 55 are fixedly connected with the surface of the heat absorption block 53, a through groove 56 is formed in one side of the transverse grooves 54, and a heat dissipation plate 57 is fixedly connected to the inner part of the heat dissipation through groove 56.
In this embodiment, when the nacelle body 1 and the positioning bracket 2 are required to be assembled, the mounting assembly 4 is inserted into the positioning bracket 2 and the mounting assembly 4 is fixed and limited by rotating the adjusting knob 3, when heat dissipation is required, heat generated when the radar device in the nacelle body 1 works is absorbed by the heat absorbing block 53, the heat is transferred into the transverse groove 54 after the heat absorption and through the action of the T-shaped guide rod 55, the T-shaped guide rod 55 is a good heat conductor and can quickly transfer the heat, when the heat is in the transverse groove 54, the heat enters the heat dissipation through groove 56 and is dissipated to the inside of the heat dissipation through the action of the heat dissipation plate 57, and the vent 7 is provided with a certain heat dissipation effect.
Example 2
As shown in fig. 1-4, on the basis of embodiment 1, the present utility model provides a technical solution: preferably, the lower extreme of nacelle body 1 extends to the inside of base 6, the inside sliding connection of the surface of nacelle body 1 and base 6, the both sides fixedly connected with dog 61 of nacelle body 1, the lower surface fixedly connected with iron sheet 68 of base 6, one side of dog 61 is provided with bracing piece 64, the upper end and the nacelle body 1 bottom fixed connection of bracing piece 64, the lower extreme of bracing piece 64 is provided with sleeve 62, the bottom of sleeve 62 and the bottom fixed connection of base 6 inner chamber, the both sides fixedly connected with fixed block 63 of sleeve 62, the upper surface fixedly connected with spring 65 of fixed block 63, the upper end and the bottom fixed connection of nacelle body 1 of spring 65, bracing piece 64 is in the inside of spring 65, one side fixedly connected with stiffener 66 of fixed block 63, the middle part of stiffener 66 and the bottom fixed connection of base 6 inner chamber, the upper end of stiffener 66 is provided with plate 67, the upper surface and the nacelle body 1 bottom fixed connection of plate 67.
In this embodiment, when the unmanned aerial vehicle accidentally drops, the iron sheet 68 in the base 6 contacts the ground, and the base 6 slides upward on the surface of the nacelle body 1 and presses the supporting rod 64, so that the supporting rod 64 is contracted inside the sleeve 62, and simultaneously presses the spring 65, so that the spring 65 is contracted from a normal state, and the plate 67 contacts the reinforcing rod 66, and the reinforcing rod 66 functions to reinforce and fix the sleeves 62 on both sides, thereby effectively preventing the nacelle body 1 from being damaged on the surface, and the stopper 61 is provided to limit the nacelle body 1 in position to prevent the nacelle body 1 from being separated from the base 6.
Example 3
As shown in fig. 1-4, on the basis of embodiment 1, the present utility model provides a technical solution: preferably, an elastic ring 622 is arranged in the sleeve 62, a limiting plate 621 is lapped at the upper end of the elastic ring 622, the upper surface of the limiting plate 621 is fixedly connected with the bottom of the supporting rod 64, two ends of the limiting plate 621 are slidably connected with the inside of the sleeve 62, and the surface of the supporting rod 64 is slidably connected with the inside of the sleeve 62.
In the present embodiment, when the support rod 64 slides down inside the sleeve 62 and drives the limiting plate 621, the limiting plate 621 presses the elastic ring 622, so that the buffering effect is enhanced, and the effect of the limiting plate 621 has the effect of position limitation, so that the support rod 64 is prevented from being separated from the inside of the sleeve 62.
The working principle of the unmanned aerial vehicle radar nacelle structure is specifically described below.
As shown in fig. 1 to 4, when the nacelle body 1 and the positioning bracket 2 are required to be assembled, the mounting assembly 4 is inserted into the positioning bracket 2 and the mounting assembly 4 is fixedly limited by rotating the adjusting knob 3, when heat dissipation is required, heat is absorbed by the heat absorbing block 53 and is mutually matched by the T-shaped guide rod 55, the transverse groove 54, the heat dissipation through groove 56 and the heat dissipation plate 57, so that the heat dissipation effect is achieved, when the unmanned aerial vehicle accidentally drops, the iron sheet 68 in the base 6 is contacted with the ground, the base 6 slides upwards on the surface of the nacelle body 1 and extrudes the supporting rod 64 and the spring 65, and the lower end of the supporting rod 64 extrudes the elastic ring 622, so that the nacelle body 1 is buffered, and the surface is effectively prevented from being damaged.
The foregoing utility model has been generally described in great detail, but it will be apparent to those skilled in the art that modifications and improvements can be made thereto. Accordingly, it is intended to cover modifications or improvements within the spirit of the inventive concepts.
Claims (6)
1. Unmanned aerial vehicle radar nacelle structure, including nacelle body (1) and locating support (2), its characterized in that: the inside sliding connection of locating support (2) has installation component (4), the lower extreme of installation component (4) is fixedly connected with the upper surface of nacelle body (1), the front fixedly connected with cooling machanism (5) of nacelle body (1), vent (7) have been seted up to the side of nacelle body (1), the bottom of nacelle body (1) is provided with base (6), the surface swing joint of locating support (2) has adjust knob (3);
The heat dissipation mechanism is characterized in that a mounting groove (51) is formed in the middle of the heat dissipation mechanism (5), a fixing frame (52) is fixedly connected to the inner wall of the mounting groove (51), a heat absorption block (53) is fixedly connected to one end of the fixing frame (52), transverse grooves (54) are formed in two sides of the mounting groove (51), T-shaped guide rods (55) are arranged in the transverse grooves (54), one ends of the T-shaped guide rods (55) extend to the inside of the mounting groove (51), and one ends of the T-shaped guide rods (55) are fixedly connected with the surface of the heat absorption block (53).
2. A unmanned aerial vehicle radar pod structure according to claim 1, wherein: a heat dissipation through groove (56) is formed in one side of the transverse groove (54), and a heat dissipation plate (57) is fixedly connected to the inside of the heat dissipation through groove (56).
3. A unmanned aerial vehicle radar pod structure according to claim 1, wherein: the lower extreme of nacelle body (1) extends to the inside of base (6), the inside sliding connection of the surface of nacelle body (1) and base (6), both sides fixedly connected with dog (61) of nacelle body (1), the lower surface fixedly connected with iron sheet (68) of base (6).
4. A drone radar pod structure according to claim 3, wherein: one side of dog (61) is provided with bracing piece (64), the upper end and the nacelle body (1) bottom fixed connection of bracing piece (64), the lower extreme of bracing piece (64) is provided with sleeve (62), the bottom of sleeve (62) and the bottom fixed connection of base (6) inner chamber, the both sides fixedly connected with fixed block (63) of sleeve (62), the upper surface fixedly connected with spring (65) of fixed block (63), the upper end of spring (65) and the bottom fixed connection of nacelle body (1), bracing piece (64) are in the inside of spring (65).
5. The unmanned aerial vehicle radar pod structure of claim 4, wherein: one side fixedly connected with stiffener (66) of fixed block (63), the middle part of stiffener (66) and the bottom fixed connection of base (6) inner chamber, the upper end of stiffener (66) is provided with plate (67), the upper surface of plate (67) and nacelle body (1) bottom fixed connection.
6. The unmanned aerial vehicle radar pod structure of claim 4, wherein: the inside of sleeve (62) is provided with elastic ring (622), the upper end overlap joint of elastic ring (622) has limiting plate (621), the bottom fixed connection of limiting plate (621) and bracing piece (64), the both ends of limiting plate (621) and the inside sliding connection of sleeve (62), the surface of bracing piece (64) and the inside sliding connection of sleeve (62).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321746619.8U CN220843001U (en) | 2023-07-05 | 2023-07-05 | Unmanned aerial vehicle radar nacelle structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321746619.8U CN220843001U (en) | 2023-07-05 | 2023-07-05 | Unmanned aerial vehicle radar nacelle structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220843001U true CN220843001U (en) | 2024-04-26 |
Family
ID=90777071
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321746619.8U Active CN220843001U (en) | 2023-07-05 | 2023-07-05 | Unmanned aerial vehicle radar nacelle structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220843001U (en) |
-
2023
- 2023-07-05 CN CN202321746619.8U patent/CN220843001U/en active Active
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