CN215972076U - Aircraft nose cover - Google Patents
Aircraft nose cover Download PDFInfo
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- CN215972076U CN215972076U CN202122439913.1U CN202122439913U CN215972076U CN 215972076 U CN215972076 U CN 215972076U CN 202122439913 U CN202122439913 U CN 202122439913U CN 215972076 U CN215972076 U CN 215972076U
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- nose
- aircraft nose
- rotor
- cover
- aircraft
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Abstract
The utility model discloses an aircraft nose cover, which comprises a nose, wherein the outer side surface of the nose is provided with the nose cover, the front side surface and the rear side surface of the nose cover are respectively provided with a mounting hole, the outer side surface of the nose is provided with a mounting frame at a position corresponding to the mounting hole, one end of the mounting frame far away from the nose is rotatably provided with a rotor, a sealing element is arranged between the mounting frame and the mounting hole, the rotor rotates around at least two axes and comprises an axis at least along the horizontal direction when the nose flies and a rotation along the longitudinal axis of the nose, the rotor is partially positioned at the outer side of the nose cover, the rotors are symmetrically arranged around the axis of the nose, and the mounting frame is vertical to the outer surface of the nose cover. The utility model has the advantages that: the sensor is convenient to install and the aircraft drag is reduced.
Description
Technical Field
The utility model relates to the technical field of airplane parts, in particular to an airplane nose cover.
Background
In the prior art, an aircraft nose hood is basically arranged according to a downstream direction, a raindrop type head and a wedge-shaped tail are adopted, the airflow diffusion angle of the tail is generally about 10 degrees, and the pressure difference resistance can be well reduced within a certain specific speed range by the aid of the fairing. However, the aircraft nose is often provided with a sensor, and the arrangement of the sensor on the nose part can increase the resistance of the aircraft during flying, so the utility model provides a new technology.
SUMMERY OF THE UTILITY MODEL
The utility model provides an aircraft nose cover which is convenient for installing a sensor and reduces aircraft drag.
In order to solve the technical problems, the technical scheme provided by the utility model is as follows: the utility model provides an aircraft nose cover, includes the aircraft nose, the aircraft nose lateral surface is equipped with the nose cover, the side all is equipped with the mounting hole around the nose cover, the aircraft nose lateral surface and all be equipped with the mounting bracket with the corresponding department in mounting hole position, the one end that the aircraft nose was kept away from to the mounting bracket is rotated and is equipped with the rotor, be equipped with the sealing member between mounting bracket and the mounting hole, the rotor is rotatory around two at least axes, including at least along the axle center of horizontal direction when the aircraft nose flies and along the rotation of aircraft nose longitudinal axis, the rotor part is located the nose cover outside, the rotor sets up about aircraft nose axis symmetry, mounting bracket perpendicular to nose cover surface.
Further, the rotor outer side is provided with one or more sensors, which may include infrared sensors, such as a front view infrared sensor, a night vision sensor or other optical sensor, a laser sensor, a sound sensor, a motion sensor, a high resolution camera, radar or any other type of sensor. Such sensors may have a wide variety of uses, including intelligence, surveillance, target acquisition, and reconnaissance, and may form an integrated sensor package.
Further, the rotor is of a sphere shape, and rotation is facilitated.
Compared with the prior art, the utility model has the advantages that: when the aircraft moves at a high speed, the airflow enters the mounting frame and the rotor, the airflow forms vortex in the mounting frame and drives the rotor to rotate, the rotor offsets partial airflow and disperses the airflow out without contacting with the aircraft body, so that the friction between the airflow and the outer surface of the aircraft body is reduced, the resistance of the aircraft during flight is reduced, and the sensor can be smoothly installed at the aircraft nose, so that the monitoring, target acquisition and reconnaissance are facilitated.
Drawings
Fig. 1 is a front view of an aircraft nose cover according to the present invention.
FIG. 2 is a schematic view of a rotor and mounting bracket structure of an aircraft nose cover of the present invention.
As shown in the figure: 1. the device comprises a machine head, 2, a machine head cover, 3, a sensor, 4, a mounting hole, 5, a mounting frame, 6 and a rotor.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Combine figure 1, fig. 2, an aircraft nose cover, including aircraft nose 1, 1 lateral surface of aircraft nose is equipped with nose cover 2, the side all is equipped with mounting hole 4 around the nose cover 2, 1 lateral surface of aircraft nose and all be equipped with mounting bracket 5 with 4 position correspondences of mounting hole, the one end rotation that aircraft nose 1 was kept away from to mounting bracket 5 is equipped with rotor 6, be equipped with the sealing member between mounting bracket 5 and the mounting hole 4, rotor 6 is rotatory around two at least axes, including at least along aircraft nose 1 when flying horizontal direction's axle center and along aircraft nose 1 longitudinal axis rotatory, 6 parts of rotor are located the 2 outsides of nose cover, rotor 6 sets up about 1 axle center symmetry of aircraft nose, 2 surfaces of mounting bracket 5 perpendicular to nose cover.
Further, one or more sensors 3 are arranged on the outer side surface of the rotor 6.
Further, the rotor 6 is of a spherical shape.
When the aircraft is in high-speed motion, airflow enters the mounting frame and the rotor, the airflow forms vortex in the mounting frame and drives the rotor to rotate, the rotor offsets partial airflow and disperses the airflow out without contacting with the aircraft body, so that the friction force between the airflow and the outer surface of the aircraft body is reduced, the resistance of the aircraft during flight is reduced, and the sensor can be smoothly mounted at the aircraft nose, so that monitoring, target acquisition and reconnaissance are facilitated.
The present invention and its embodiments have been described above, and the description is not intended to be limiting, and the drawings are only one embodiment of the present invention, and the actual structure is not limited thereto. In summary, those skilled in the art should appreciate that they can readily use the disclosed conception and specific embodiments as a basis for designing or modifying other structures for carrying out the same purposes of the present invention without departing from the spirit and scope of the utility model as defined by the appended claims.
Claims (3)
1. An aircraft nose cover characterized in that: including aircraft nose (1), aircraft nose (1) lateral surface is equipped with hood cover (2), the side all is equipped with mounting hole (4) around hood cover (2), aircraft nose (1) lateral surface and correspond the department with mounting hole (4) position and all be equipped with mounting bracket (5), the one end that aircraft nose (1) was kept away from in mounting bracket (5) is rotated and is equipped with rotor (6), be equipped with the sealing member between mounting bracket (5) and mounting hole (4), rotor (6) are rotatory around two at least axes, including at least along aircraft nose (1) when flying horizontal direction's axle center and rotatory along aircraft nose (1) longitudinal axis, rotor (6) part is located the hood (2) outside, rotor (6) set up about aircraft nose (1) axle center line symmetry, mounting bracket (5) perpendicular to hood (2) surface.
2. An aircraft nose cover according to claim 1, wherein: one or more sensors (3) are arranged on the outer side face of the rotor (6).
3. An aircraft nose cover according to claim 1, wherein: the rotor (6) is of a sphere shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122439913.1U CN215972076U (en) | 2021-10-11 | 2021-10-11 | Aircraft nose cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122439913.1U CN215972076U (en) | 2021-10-11 | 2021-10-11 | Aircraft nose cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215972076U true CN215972076U (en) | 2022-03-08 |
Family
ID=80507526
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122439913.1U Active CN215972076U (en) | 2021-10-11 | 2021-10-11 | Aircraft nose cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215972076U (en) |
-
2021
- 2021-10-11 CN CN202122439913.1U patent/CN215972076U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |