CN216374997U - Line clamping structure for aircraft arm of space track aircraft - Google Patents
Line clamping structure for aircraft arm of space track aircraft Download PDFInfo
- Publication number
- CN216374997U CN216374997U CN202122827266.1U CN202122827266U CN216374997U CN 216374997 U CN216374997 U CN 216374997U CN 202122827266 U CN202122827266 U CN 202122827266U CN 216374997 U CN216374997 U CN 216374997U
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- aerial vehicle
- unmanned aerial
- horn
- mounting seat
- wire
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Abstract
The utility model relates to a wire clamping structure of a space track aircraft horn, which comprises an unmanned aerial vehicle and a shell covering the unmanned aerial vehicle; the unmanned aerial vehicle comprises a mounting seat and a plurality of arms connected to the mounting seat, wherein the arms are provided with rotor wings and are connected with the shell; the upper part of the mounting seat is provided with a unmanned aerial vehicle control assembly, the lower part of the mounting seat is detachably connected with a battery assembly, the unmanned aerial vehicle control assembly is electrically connected with the battery assembly through a power line, and a wire clamping groove corresponding to the power line is arranged on the horn or the mounting seat; the structure of using this application sets up the card wire casing on the horn or on the mount pad, and the middle part card of connecting unmanned aerial vehicle control assembly and battery pack's power cord is in the card wire casing, and the problem of power cord is beaten to the difficult rotor that appears, and when changing battery pack, the lower extreme joint of power cord is in near battery pack mounted position simultaneously, and it is also comparatively convenient to operate.
Description
Technical Field
The utility model relates to the technical field of space track, in particular to a wire clamping structure of an aircraft arm of a space track aircraft.
Background
The space race track is a novel competition game, and the aerial vehicle flies on the race track erected in a certain space to achieve the competition effect; at present, power lines of aircrafts adopted in the space race track are mostly unreasonable in arrangement, and the situation that the power lines are hit by the rotor wings is easy to occur.
SUMMERY OF THE UTILITY MODEL
The technical problem to be solved by the present invention is to provide a wire-clamping structure for the aircraft arm of a space track aircraft, aiming at the above-mentioned defects of the prior art.
The technical scheme adopted by the utility model for solving the technical problems is as follows:
the method comprises the following steps of constructing a wire clamping structure of a spatial track aircraft horn, wherein the wire clamping structure comprises an unmanned aerial vehicle and a shell covering the outer part of the unmanned aerial vehicle; the unmanned aerial vehicle comprises a mounting seat and a plurality of arms connected to the mounting seat, wherein the arms are provided with rotor wings and connected with the shell; the upper portion of mount pad is provided with unmanned aerial vehicle control assembly, the connection can be dismantled to the lower part of mount pad is provided with battery pack, unmanned aerial vehicle control assembly pass through the power cord with the battery pack electricity is connected, the horn or be provided with on the mount pad with the card wire casing that the power cord corresponds.
The utility model relates to a wire clamping structure of a space track aircraft horn, wherein a power wire comprises a positive connecting wire and a negative connecting wire; the wire clamping groove comprises a first clamping groove corresponding to the positive connecting wire and a second clamping groove corresponding to the negative connecting wire.
The aircraft horn wire clamping structure of the space track aircraft comprises a mounting seat, wherein the mounting seat comprises a mounting plate connected with a plurality of aircraft horns, and the outer side surface of the mounting plate is provided with a first clamping groove and a second clamping groove.
The aircraft horn wire clamping structure of the space track aircraft is characterized in that the horn is connected to the corner of the mounting plate, and the first clamping groove and the second clamping groove are arranged on two sides of one of the plurality of horns.
The utility model relates to a wire clamping structure of a space track aircraft horn, wherein an unmanned aerial vehicle control assembly comprises a plurality of layers of circuit boards, a mounting column for mounting the plurality of layers of circuit boards is arranged on a mounting seat, a plurality of limiting rings are sleeved on the mounting column, and the limiting rings are arranged between the adjacent circuit boards.
The utility model has the beneficial effects that: the structure of using this application sets up the card wire casing on the horn or on the mount pad, and the middle part card of connecting unmanned aerial vehicle control assembly and battery pack's power cord is in the card wire casing, and the problem of power cord is beaten to the difficult rotor that appears, and when changing battery pack, the lower extreme joint of power cord is in near battery pack mounted position simultaneously, and it is also comparatively convenient to operate.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the present invention will be further described with reference to the accompanying drawings and embodiments, wherein the drawings in the following description are only part of the embodiments of the present invention, and for those skilled in the art, other drawings can be obtained without inventive efforts according to the accompanying drawings:
FIG. 1 is a schematic illustration of a preferred embodiment of the utility model showing a configuration of a yoke clip without a housing;
FIG. 2 is a schematic structural diagram of a wire clamping structure with a housing of a spacecraft arm of the space track aircraft according to the preferred embodiment of the utility model;
fig. 3 is an enlarged view of the mounting seat of the wire-clamping structure of the aircraft arm of the space track aircraft according to the preferred embodiment of the utility model.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention, and it is obvious that the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without inventive step, are within the scope of the present invention.
The aircraft arm wire clamping structure of the space track aircraft according to the preferred embodiment of the utility model is shown in fig. 1, and also refers to fig. 2 and 3, and comprises an unmanned aerial vehicle and a shell 1 covering the exterior of the unmanned aerial vehicle; the unmanned aerial vehicle comprises a mounting base 2 and a plurality of arms 3 connected to the mounting base 2, wherein the arms 3 are provided with rotor wings 4, and the arms 3 are connected with the shell 1; the upper part of the mounting seat 2 is provided with an unmanned aerial vehicle control assembly 20, the lower part of the mounting seat 2 is detachably connected with a battery assembly 21, the unmanned aerial vehicle control assembly 20 is electrically connected with the battery assembly 21 through a power line (not shown in the figure), and the horn 3 or the mounting seat 2 is provided with a wire clamping groove 22 corresponding to the power line;
use the structure of this application, set up card wire casing 22 on the horn or mount pad 2, the middle part card of the power cord of connecting unmanned aerial vehicle control assembly 20 and battery pack 21 is in card wire casing 22, is difficult for appearing rotor 4 and hits the problem of power cord, and when changing battery pack 21, the lower extreme joint of power cord is in near of battery pack 21 mounted position simultaneously, and it is also comparatively convenient to operate.
Preferably, the power line comprises a positive connecting line and a negative connecting line; the wire clamping groove 22 comprises a first clamping groove 220 corresponding to the positive connecting wire and a second clamping groove 221 corresponding to the negative connecting wire; the positive and negative connecting wires are separated through different clamping grooves, so that the reverse connection condition is reduced.
Preferably, the mounting base 2 includes a mounting plate 200 connected to the plurality of arms, and a first engaging groove 220 and a second engaging groove 221 are formed on an outer surface of the mounting plate 200; the wholeness is good, and processing is convenient.
Preferably, the horn 3 is connected to a corner of the mounting plate 200, and the first and second engaging grooves 220 and 221 are disposed on two sides of one of the plurality of horns; the integrity is good, is qualified for the next round of competitions from different position, can further increase the degree of discernment, reduces the reversal.
Preferably, the unmanned aerial vehicle control assembly 20 includes a multilayer circuit board 201, a mounting column 202 for mounting the multilayer circuit board is arranged on the mounting base 2, a plurality of spacing rings 203 are sleeved on the mounting column 202, and the spacing rings 203 are arranged between the adjacent circuit boards 201; the structure is reasonable and compact, the volume is small, and the stability is good;
preferably, the spacing ring 203 is made of an insulating material.
It will be understood that modifications and variations can be made by persons skilled in the art in light of the above teachings and all such modifications and variations are intended to be included within the scope of the utility model as defined in the appended claims.
Claims (5)
1. A wire clamping structure of a space track aircraft horn is characterized by comprising an unmanned aerial vehicle and a shell covering the unmanned aerial vehicle; the unmanned aerial vehicle comprises a mounting seat and a plurality of arms connected to the mounting seat, wherein the arms are provided with rotor wings and connected with the shell; the upper portion of mount pad is provided with unmanned aerial vehicle control assembly, the connection can be dismantled to the lower part of mount pad is provided with battery pack, unmanned aerial vehicle control assembly pass through the power cord with the battery pack electricity is connected, the horn or be provided with on the mount pad with the card wire casing that the power cord corresponds.
2. The spacecraft arm jamming line structure of claim 1, wherein the power line includes a positive connection line and a negative connection line; the wire clamping groove comprises a first clamping groove corresponding to the positive connecting wire and a second clamping groove corresponding to the negative connecting wire.
3. The space track aircraft horn wire trap structure of claim 2, wherein the mount includes a mounting plate connected to the plurality of horns, the mounting plate having the first and second slots disposed on an outer surface thereof.
4. The space track aircraft horn wire trap structure of claim 3, wherein the horn is connected to a corner of the mounting plate, and the first and second card slots are disposed on both sides of one of the plurality of horns.
5. The space track aircraft horn wire clamping structure of claim 3, wherein the unmanned aerial vehicle control assembly comprises a multilayer circuit board, a mounting column for mounting the multilayer circuit board is arranged on the mounting seat, a plurality of limiting rings are sleeved on the mounting column, and the limiting rings are arranged between the adjacent circuit boards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122827266.1U CN216374997U (en) | 2021-11-16 | 2021-11-16 | Line clamping structure for aircraft arm of space track aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122827266.1U CN216374997U (en) | 2021-11-16 | 2021-11-16 | Line clamping structure for aircraft arm of space track aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216374997U true CN216374997U (en) | 2022-04-26 |
Family
ID=81254335
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122827266.1U Active CN216374997U (en) | 2021-11-16 | 2021-11-16 | Line clamping structure for aircraft arm of space track aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216374997U (en) |
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2021
- 2021-11-16 CN CN202122827266.1U patent/CN216374997U/en active Active
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| GR01 | Patent grant | ||
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