CN216035106U - Aircraft paddle protection device - Google Patents
Aircraft paddle protection device Download PDFInfo
- Publication number
- CN216035106U CN216035106U CN202120563054.4U CN202120563054U CN216035106U CN 216035106 U CN216035106 U CN 216035106U CN 202120563054 U CN202120563054 U CN 202120563054U CN 216035106 U CN216035106 U CN 216035106U
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- wing
- flying saucer
- motor
- cabin body
- protection device
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Abstract
The utility model provides an aircraft blade protection device which comprises a flying saucer cabin body, a flying saucer cabin cover arranged on the flying saucer cabin body, and a plurality of propellers annularly arranged on the flying saucer cabin body, wherein a plurality of mounting holes penetrating up and down are annularly arranged on the flying saucer cabin body, a support seat extending into the mounting holes is arranged on the flying saucer cabin body, each propeller comprises a motor arranged on the support seat, a wing arranged on the motor, and an electric controller arranged below the support seat and used for controlling the motor, the motor and the wing are both positioned in the mounting holes, and the wing forms an anti-collision protection outer cover through the mounting holes. The problem that the propeller is exposed to the outside to hurt people or damage objects can be solved, so that even if the aircraft collides with a barrier, only the shell of the aircraft body is damaged, the wings cannot be damaged, and the flying effect cannot be influenced.
Description
Technical Field
The utility model relates to the technical field of butterfly aircrafts, in particular to an aircraft blade protection device.
Background
The existing aircrafts mainly comprise airplanes, gliders, helicopters and hot air balloons, and for disc aircrafts, the existing aircrafts are mainly embodied in movies and pictures, so that the existing research and development are relatively few, and the aircrafts have many limitations in flying, such as: the special runway is needed, and on the other hand, the existing aircrafts are not in a central symmetrical structure, and have the defects of serious interference and inflexible steering when flying in the air, so that the improvement of the aircrafts mainly taking a disc shape is necessary, the outer outline of the butterfly aircraft mainly comprises a flying disc cabin body and a flying disc cabin cover, a plurality of aircraft propellers are symmetrically arranged around the flying disc cabin body, but the existing aircraft propellers are generally exposed and easily hit people or objects, and once the propellers hit obstacles, the propellers are easily damaged, so that the accident of crash is caused, and therefore, the blade parts of the aircrafts need to be protected.
Disclosure of Invention
In order to solve certain or some technical problems in the prior art, the utility model provides an aircraft blade protection device which can solve the problem that a propeller is exposed to the outside to hurt people or objects, so that even if an aircraft collides with an obstacle, only the shell of an aircraft body is damaged, the wings cannot be damaged, and the flight effect cannot be influenced.
In order to solve the above-mentioned existing technical problem, the utility model adopts the following scheme:
the utility model provides an aircraft paddle protection device, includes the flying saucer cabin body, establishes flying saucer cabin cover, the ring in the flying saucer cabin body are established a plurality of screws in the flying saucer cabin body, the flying saucer cabin body is fitted with a contraceptive ring and is equipped with a plurality of mounting holes that run through from top to bottom, be equipped with in the flying saucer cabin body and stretch into supporting seat in the mounting hole, the screw is including establishing motor on the supporting seat, establishing wing on the motor, establishing the mount pad below is right the electricity that the motor controlled is transferred, the motor with the wing all is located in the mounting hole, the wing passes through the mounting hole forms anticollision dustcoat.
Furthermore, the middle of the supporting seat adopts a sinking structure.
Furthermore, one side of the supporting seat is provided with a power interface, and the motor and the electric regulator supply power after being inserted into a power supply through the power interface.
Further, a duct structure is formed between the end part of the wing and the side wall of the mounting hole, and the distance between the wing and the side wall of the mounting hole is 2.2 mm.
Further, a fairing is arranged on the wing.
Further, the distance from the wing to the top end of the mounting hole is 11-13 mm.
Further, the wing adopts five wing structures.
Compared with the prior art, the utility model has the beneficial effects that:
the flying saucer cabin body flies through the screw, a plurality of mounting holes which run through from top to bottom are formed in the flying saucer cabin body, the mounting holes have certain depth, the screw is arranged in the mounting holes, the motor and the wings are located on the inner side of the mounting holes, the wings are in a non-exposed state, people cannot be injured or objects cannot be damaged in the flying process of the aircraft, and even if the aircraft hits a barrier, the shell of the aircraft body is damaged, the wings are not damaged, and the flying effect cannot be influenced.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an enlarged view of a portion of the present invention;
in the figure: the device comprises an electric speed regulator 1, a motor 2, a supporting seat 3, a flying saucer cabin cover 4, a flying saucer cabin body 5, a mounting hole 6, a propeller 7, a fairing 8, wings 9 and a power supply interface 10.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and the detailed description, and it should be noted that any combination of the embodiments or technical features described below can be used to form a new embodiment without conflict.
As shown in fig. 1 and 2, an aircraft paddle protection device, include the flying saucer cabin body 5, establish flying saucer cabin cover 4, the ring on the flying saucer cabin body 5 are established a plurality of screws 7 in the flying saucer cabin body 5, the flying saucer cabin body 5 is fitted with a contraceptive ring and is equipped with a plurality of mounting holes 6 that run through from top to bottom, be equipped with on the flying saucer cabin body 5 and stretch into supporting seat 3 in the mounting hole 6, screws 7 are including establishing motor 2 on the supporting seat 3, establishing wing 9 on the motor 2, establishing 3 below of supporting seat are right the electricity regulation 1 that motor 2 carries out the control, motor 2 with wing 9 all is located in the mounting hole 6, wing 9 passes through mounting hole 6 forms the anticollision protection dustcoat.
In the in-service use process, the flying saucer cabin body 5 flies through screw 7, set up a plurality of mounting holes 6 that run through from top to bottom on the flying saucer cabin body 5, mounting hole 6 has certain degree of depth, and be provided with supporting seat 3 in the mounting hole 6, can make screw 7 set up in mounting hole 6 through supporting seat 3, it is more convenient to the location of screw 7, it is more firm to the fixed of motor 2 and electricity accent 1, and motor 2 and electricity accent 1 set up respectively in the upper and lower both ends of supporting seat 3, it is more simple and convenient when the dismouting, wherein motor 2 and wing 9 all are located mounting hole 6 inboardly, make wing 9 be in the non-exposed state, in-process at the aircraft flight, can not hurt people or break the object, even the aircraft hits the barrier, also only the shell of organism is impaired, it is not wing 9 damages, can not influence the flight effect.
The improved structure is characterized in that a sunken structure is adopted in the middle of the supporting seat 3, so that the installation space of the motor 2 and the wing 9 is larger when the end part of the supporting seat 3 is positioned in the middle of the installation hole 6, and the protection of the wing 9 can be ensured under the condition that the hole depth of the installation hole 6 is fixed.
The improved structure is characterized in that a power interface 10 is arranged on one side of the supporting seat 3, and the motor 2 and the electric regulator 1 are powered after being inserted into a power supply through the power interface 10.
Because the motor 2 and the electronic tuning 1 are respectively arranged at the upper end and the lower end of the supporting seat 3, after the power cord is inserted into the power interface 10 on the supporting seat 3, the power cord and the supporting seat can simultaneously perform functions on the power cord and the supporting seat through the power interface 10, and a plurality of power interfaces 10 are not required to be arranged.
In a further improvement, a duct structure is formed between the end part of the wing 9 and the side wall of the mounting hole 6, and the distance between the wing 9 and the side wall of the mounting hole 6 is 2.2 mm; because the size of the oar of the wing 9 is close to the size of the side wall of the mounting hole 6, the wing 9 generates huge negative pressure with the air of the side wall when rotating, thereby forming a stroke duct and improving the lift force of aerodynamic force, and the length of the wing 9 can be shorter, the size of the reduced oar is reduced, and the weight of the aircraft is reduced.
In a further improvement, a fairing 8 is arranged on the wing 9, and the fairing 8 can play a double role of protecting the wing 9 and reducing air resistance.
In a further improvement, the distance from the wing 9 to the top end of the mounting hole 6 is 11-13mm, so that the wing 9 can be greatly protected from foreign objects and the wing 9 can hurt people and objects.
The further improvement is that the wing 9 adopts a five-wing structure, so that the driving effect of the wing 9 is better.
The above embodiments are only preferred embodiments of the present invention, and the protection scope of the present invention is not limited thereby, and any insubstantial changes and substitutions made by those skilled in the art based on the present invention are within the protection scope of the present invention.
Claims (7)
1. The utility model provides an aircraft paddle protection device, includes the flying saucer cabin body, establishes flying saucer cabin cover, ring in the flying saucer cabin body are established a plurality of screw in the flying saucer cabin body, its characterized in that: the flying saucer cabin body is fitted with a contraceptive ring and is equipped with a plurality of mounting holes that run through from top to bottom, be equipped with in the flying saucer cabin body and stretch into supporting seat in the mounting hole, the screw is including establishing motor on the supporting seat, establishing wing on the motor, establishing the supporting seat below is right the electricity that the motor controlled is transferred, the motor with the wing all is located in the mounting hole, the wing passes through the mounting hole forms the anticollision protective housing.
2. An aircraft blade protection device according to claim 1, wherein: the middle of the supporting seat adopts a sinking structure.
3. An aircraft blade protection device according to claim 1, wherein: one side of the supporting seat is provided with a power supply interface, and the motor and the electricity are adjusted through the power supply interface to supply power after being inserted into a power supply.
4. An aircraft blade protection device according to claim 1, wherein: a duct structure is formed between the end part of the wing and the side wall of the mounting hole, and the distance between the wing and the side wall of the mounting hole is 2.2 mm.
5. An aircraft blade protection device according to any one of claims 1 to 4, wherein: and a fairing is arranged on the wing.
6. An aircraft blade protection device according to any one of claims 1 to 4, wherein: the distance from the wing to the top end of the mounting hole is 11-13 mm.
7. An aircraft blade protection device according to claim 1, wherein: the wing adopts five wing structures.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120563054.4U CN216035106U (en) | 2021-03-19 | 2021-03-19 | Aircraft paddle protection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120563054.4U CN216035106U (en) | 2021-03-19 | 2021-03-19 | Aircraft paddle protection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216035106U true CN216035106U (en) | 2022-03-15 |
Family
ID=80596093
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120563054.4U Active CN216035106U (en) | 2021-03-19 | 2021-03-19 | Aircraft paddle protection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216035106U (en) |
-
2021
- 2021-03-19 CN CN202120563054.4U patent/CN216035106U/en active Active
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