CN216834297U

CN216834297U - Anti-icing airspeed head of fixed wing unmanned aerial vehicle

Info

Publication number: CN216834297U
Application number: CN202220386935.8U
Authority: CN
Inventors: 苏锦明
Original assignee: Shenzhen Mingde New Material Technology Co ltd
Current assignee: Shenzhen Mingde New Material Technology Co ltd
Priority date: 2022-02-23
Filing date: 2022-02-23
Publication date: 2022-06-28
Anticipated expiration: 2032-02-23

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an anti-icing airspeed head of a fixed-wing unmanned aerial vehicle; the utility model comprises a pitot tube shell and a dynamic pressure tube, wherein the dynamic pressure tube is sleeved in the pitot tube shell, the front end of the dynamic pressure tube penetrates out of the front end of the pitot tube shell, the rear end of the dynamic pressure tube is fixed with an atmosphere measuring module, an electric heating wire is arranged in the pitot tube shell, and the rear end of the dynamic pressure tube is sleeved with a dynamic pressure tube base; the utility model discloses built-in atmospheric measurement module can detect humidity and temperature in the flight, real-time detection atmospheric condition to correspondingly open electric heating wire heating function, carry out the heating of automatic rising, perhaps auto-power-off, low power dissipation, heat time are short.

Description

Anti-icing airspeed head of fixed wing unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field refers in particular to an anti-icing airspeed tube of fixed wing unmanned aerial vehicle.

Background

The anti-icing airspeed head of the existing fixed-wing unmanned aerial vehicle is a simple metal pipe or plastic pipe with a simple structure (pitot tube) adopted by the existing majority of fixed-wing unmanned aerial vehicles, and even some airspeeds can only measure dynamic pressure data without static pressure holes. The airspeed head with a simple structure has icing phenomena under the conditions of high altitude, low air temperature, high flying altitude in winter or extreme weather, so that the airspeed head is inaccurate or completely fails. The ordinary heating airspeed tube scheme can solve the problem of freezing, but has the problems of long continuous heating time, constant temperature step in the airspeed tube, high energy consumption, high material loss and the like.

Chinese patent publication No. CN211402422U discloses a pitot tube for unmanned aerial vehicle, which includes: the base is provided with a mounting part and a supporting part which are coaxially arranged, an air flow channel is formed in the middle pipe along the axis direction of the middle pipe, one end of the air flow channel is fixedly connected with the mounting part of the base, the peripheral wall of the middle pipe is wound with a heating wire, the heating wire is connected with a thermistor, the outer sleeve is sleeved outside the middle pipe, and the end part of the outer sleeve is fixedly connected with the mounting part of the base. The structure of the airspeed head is simple, and the defects are also existed.

Therefore, based on the above-mentioned shortcomings of the prior fixed-wing drone airspeed head, there is a need to improve upon the prior fixed-wing drone airspeed head.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a fixed wing unmanned aerial vehicle anti-icing airspeed tube to the not enough of prior art, this fixed wing unmanned aerial vehicle anti-icing airspeed tube has solved that current fixed wing unmanned aerial vehicle airspeed tube exists: long heating time and the like.

In order to achieve the purpose, the utility model is realized by the following technical scheme: fixed wing unmanned aerial vehicle anti-icing airspeed tube, including airspeed tube shell, dynamic pressure pipe, in airspeed tube shell was located to dynamic pressure pipe box, the front end of dynamic pressure pipe was worn out from the front end of airspeed tube shell, and the rear end of dynamic pressure pipe is fixed with the atmosphere and measures the module, installs electric heating wire in the airspeed tube shell, and the rear end overcoat of dynamic pressure pipe is equipped with dynamic pressure pipe base.

Furthermore, the pipe wall of the airspeed head shell is provided with a static pressure hole, and the static pressure hole is used for measuring static pressure data.

Furthermore, the rear end of the dynamic pressure tube is provided with a fixing ring, and the atmosphere measuring module is sleeved on the fixing ring and used for measuring relevant data of atmosphere.

Furthermore, electric heating wire be the heliciform, electric heating wire cover is located the outside of dynamic pressure pipe, can be used for generating heat and rise the temperature, prevents to freeze.

Furthermore, the power supply base is sleeved outside the dynamic pressure tube base, the atmosphere measurement module is provided with a second metal contact, and the second metal contact is in contact with a corresponding contact of the power supply base and is led out by the power supply base, so that the connection is simpler.

Furthermore, the rear end of the electric heating wire is provided with a first metal contact which is contacted with a corresponding contact of the power supply base, and the power supply base is led out of a power supply cable and led out of the power supply base, so that the connection is simpler.

Furthermore, the power supply base leads out the static pressure measuring tube, so that the whole body is simpler.

The beneficial effects of the utility model reside in that: the built-in atmosphere measurement module can detect humidity and temperature in flight, real-time detection atmospheric state to correspondingly open electric heating wire heating function, carry out the automatic heating up heating, perhaps auto-power-off, low power dissipation, heat time are short.

Drawings

Fig. 1 is a schematic structural diagram of the present invention.

Fig. 2 is an exploded view of the present invention.

Reference numbers and descriptions:

airspeed tube shell 1, dynamic pressure pipe 2, electric heating wire 3, atmosphere measurement module 4, dynamic pressure pipe base 5, power supply base 6, static pressure hole 7, solid fixed ring 8, first metal contact 9, second metal contact 10, power cable 11, static pressure survey buret 12.

Detailed Description

The present invention will be further described with reference to the accompanying drawings.

See fig. 1-fig. 2, the utility model discloses fixed wing unmanned aerial vehicle anti-icing airspeed tube includes: airspeed tube shell 1, dynamic pressure pipe 2, static pressure hole 7 has been seted up on airspeed tube shell 1's the pipe wall, and airspeed tube shell 1 is mainly for protecting inside spare part and rectification function, and static pressure hole 7 is used for measuring static pressure data simultaneously.

The utility model discloses a rear end of dynamic pressure pipe 2 has solid fixed ring 8, and solid fixed ring 8 covers is equipped with atmosphere measurement module 4. The atmosphere measurement module 4 mainly measures the temperature and humidity in the air in real time, is used for judging the possibility of environmental icing, and sends a corresponding instruction when an environmental value reaches a preset threshold value.

The utility model discloses an in airspeed tube shell 1 was located to dynamic pressure pipe 2 cover, the front end of dynamic pressure pipe 2 was worn out from airspeed tube shell 1's front end, and the outside cover of dynamic pressure pipe 2 is equipped with electric heating wire 3, and electric heating wire 3 is the heliciform. The electric heating wire 3 mainly provides a function of heating and increasing temperature, and is an important part, and executes corresponding heating and heating stopping functions after receiving an instruction sent by the atmosphere measuring module 4.

The utility model discloses a rear end overcoat of dynamic pressure pipe 2 is equipped with dynamic pressure pipe base 5, and dynamic pressure pipe base 5 mainly draws forth dynamic pressure pipe 2 and is used for connecting the flight control, also is used for the fuselage aircraft nose rigidity with unmanned aerial vehicle.

The utility model discloses a 5 overcoat of dynamic pressure pipe base is equipped with power supply base 6, and electric heating wire 3's rear end has two first metal contacts 9, these two first metal contacts 9 and power supply base 6's the contact of correspondence, and power supply base 6 draws forth power cable 11.

The utility model discloses an atmosphere measurement module 4 has four second metal contacts 10, and four second metal contacts 10 contact with the contact of the correspondence of power supply base 6, and power supply base 6 draws forth static pressure survey pipe 12.

The utility model discloses a dynamic pressure pipe 2 mainly provides the measurement dynamic pressure data and provides the installation basis for electric heating wire 3 and atmosphere measuring module 4.

The utility model discloses a 6 main 6 metal contacts through the design of power supply base connect atmosphere measuring module 4 and electric heating wire 3, make their normal work and be connected.

The utility model discloses a pitot tube, built-in atmospheric measurement module 4 can detect humidity and temperature in flight, but automatic identification temperature, humidity, real-time detection atmospheric state will open electric heating wire 3 heating function when reaching preset threshold value, carries out the heating of automatic rising, when reaching the interior auto-power-off of preset temperature range to realize the consumption of minimum, can hardly influence duration to pure unmanned aerial vehicle. The airspeed head has dynamic pressure pipe and static pressure hole, and the measuring result is more accurate, and structure weight is low, long service life.

Of course, the above-mentioned embodiments are only preferred examples of the present invention, and not intended to limit the scope of the present invention, so that all equivalent changes or modifications made by the structure, features and principles described in the claims of the present invention should be included in the claims of the present invention.

Claims

1. Fixed wing unmanned aerial vehicle anti-icing airspeed head, its characterized in that: including airspeed tube shell, dynamic pressure pipe, in the airspeed tube shell was located to dynamic pressure pipe box, the front end of dynamic pressure pipe was worn out from the front end of airspeed tube shell, and the rear end of dynamic pressure pipe is fixed with the atmosphere and is measured the module, installs electric heating wire in the airspeed tube shell, and the rear end overcoat of dynamic pressure pipe is equipped with dynamic pressure pipe base, and dynamic pressure pipe base overcoat is equipped with the power supply base, and the atmosphere is measured the module and is had the second metal contact, and the second metal contact contacts the contact with the correspondence of power supply base.

2. The anti-icing airspeed head of fixed-wing drone of claim 1, characterized in that: and the pipe wall of the shell of the airspeed head is provided with a static pressure hole.

3. The anti-icing airspeed head of fixed-wing drone of claim 1, characterized in that: the rear end of the dynamic pressure tube is provided with a fixing ring, and the atmosphere measuring module is sleeved on the fixing ring.

4. The anti-icing airspeed head of fixed-wing drone of claim 1, characterized in that: the electric heating wire is in a spiral shape and is sleeved outside the dynamic pressure pipe.

5. The anti-icing airspeed head of fixed-wing drone of claim 1, characterized in that: the rear end of the electric heating wire is provided with a first metal contact which is contacted with a corresponding contact of the power supply base, and the power supply base is led out of a power supply cable.

6. The anti-icing airspeed head of fixed-wing drone of claim 1, characterized in that: the power supply base leads out the static pressure measuring tube.