CN211402422U - Airspeed head and fixed wing unmanned aerial vehicle for unmanned aerial vehicle - Google Patents
Airspeed head and fixed wing unmanned aerial vehicle for unmanned aerial vehicle Download PDFInfo
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- CN211402422U CN211402422U CN202020353771.XU CN202020353771U CN211402422U CN 211402422 U CN211402422 U CN 211402422U CN 202020353771 U CN202020353771 U CN 202020353771U CN 211402422 U CN211402422 U CN 211402422U
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Abstract
The utility model discloses a pitot tube for unmanned aerial vehicle, include: 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 airspeed head is formed by assembling a base, an outer sleeve and a middle pipe, the structure is ingenious and reasonable, the whole airspeed head does not need to be fixed by screws, the convenience of installation and maintenance is improved, and a convex cap is further arranged at the end part of the middle pipe to limit the outer sleeve, so that the overall structure of the airspeed head is more reliable; and moreover, temperature control heating is realized by arranging the temperature sensing element and the heating element, the freezing hidden danger of the airspeed tube in the high-altitude low-temperature environment is eliminated, the airspeed tube is prevented from losing efficacy due to freezing, and the flight safety is further improved.
Description
Technical Field
The utility model relates to a airspeed head for unmanned aerial vehicle belongs to unmanned air vehicle technical field.
Background
The airspeed head is an aviation device, also called pitot tube, total pressure tube and total-static pressure tube, and can sense total pressure (also called total pressure) and static pressure of air flow, and transfer the measured pressure data to air data computer or flight instrument, mainly used for measuring flying speed of aircraft, and possesses other several functions. Inside the air inlet messenger air current that the airspeed tube set up on through the body got into the airspeed tube, its inside air current pipe guided the air current to the terminal inductor of pipe, experienced the impact strength (being the dynamic pressure) of air current through the inductor, converted the dynamic pressure through electronic equipment or monitoring devices again, can detect out the real-time flying speed of aircraft, and finally, just can audio-visually show the flight speed per hour of aircraft through the panel board.
Utility model patent of application number 201822273837.X discloses a pitot tube also uses on the aircraft, including pitot tube body and casing, the material of pitot tube body is the glass steel for guide air current gets into measuring device, this pitot tube body with the casing is connected and installs on the organism through this casing. The material of the airspeed head tube body disclosed by the utility model is glass fiber reinforced plastic, and the glass fiber reinforced plastic has the wave-transmitting characteristic, so that the effect of inhibiting radar reflection is achieved, and the stealth effect of an airplane can be met; compared with the traditional airspeed head made of metal, the airspeed head made of glass fiber reinforced plastic has the advantages of lighter weight and higher strength.
In prior art, unmanned aerial vehicle's flying height is limited, and one of them important reason is that unmanned aerial vehicle can meet with low temperature environment when high altitude flight, probably leads to the airspeed head for the unmanned aerial vehicle to freeze and block up, has the inefficacy risk, and then can influence flight safety.
SUMMERY OF THE UTILITY MODEL
For solving prior art's not enough, the utility model aims to provide a pitot tube for unmanned aerial vehicle, the installation is convenient, can eliminate the hidden danger that freezes simultaneously, ensures flight safety.
In order to achieve the above object, the utility model adopts the following technical scheme:
a pitot tube for an unmanned aerial vehicle, comprising: the base is provided with an installation 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 installation 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, and the outer sleeve is sleeved outside the middle pipe and the end part of the outer sleeve is fixedly connected with the installation part of the base.
Preferably, the front base is provided with a metal column on an end surface far away from the middle pipe, and the metal column is circumferentially provided with threads. Through threaded connection with metal column and organism fixed connection to install the airspeed head on the organism.
More preferably, the other end of the middle pipe far away from the base is provided with a convex cap which is fixed with the middle pipe through threaded connection. The convex cap is of a hemispherical structure, the outer sleeve can be limited by the hemispherical structure, and after the airspeed head is installed, the outer sleeve is located between the convex cap and the base. And the middle pipe is provided with threads at one end close to the base, and the middle pipe is fixedly connected with the mounting part through threaded connection.
Preferably, the thermistor is fixed in the mounting seat by thermal conductive silica gel, and of course, a sufficient space position for accommodating the thermistor is left in the mounting seat.
Preferably, the outer wall surface of the outer sleeve is streamlined, the through hole on the inner wall surface of the outer sleeve is a three-section stepped through hole, the aperture of the inner through hole corresponding to the mounting seat is the largest, and the aperture corresponding to the middle pipe is two-section stepped. The reason is that a small section of the non-winding heating wire is reserved at the front end of the middle pipe, the inner diameter of the outer sleeve corresponding to the section is the smallest, so that the outer sleeve is tightly attached to the middle pipe which is not wound with the heating wire, and the inner diameter of the outer sleeve wound with the heating wire is slightly larger, so that the heating wire is prevented from being extruded.
More preferably, the base, the outer sleeve and the middle tube are all made of aluminum alloy materials.
Further preferably, aforementioned airspeed head for unmanned aerial vehicle still includes a control panel, the control panel is connected with thermistor and is in order to realize that temperature detects and control circuit break-make heating, and the control panel generally sets up on unmanned aerial vehicle's integrated management board, realizes communication and signal transmission through wired or wireless mode with thermistor.
Preferably, the heating wire is a 12V direct current low-power heating wire, and a high-temperature insulating tape is wound outside the heating wire, or the heating wire is directly used as the insulating heating wire.
The utility model also discloses a fixed wing unmanned aerial vehicle, including the organism, still include as before airspeed tube for the unmanned aerial vehicle, the base and the organism of airspeed tube pass through screw thread fixed connection.
The utility model discloses an useful part lies in:
(1) the utility model discloses a pitot tube is assembled by base, outer tube and well pipe, and the structure is ingenious reasonable, wholly need not the screw fixation, has improved the convenience of installation and maintenance, still installs a protruding cap in well tub of tip in order to play limiting displacement to the outer tube, avoids axial displacement, makes the overall structure of pitot tube more reliable;
(2) the temperature sensing element (thermistor) and the heating element (heating wire) are arranged in the airspeed head to realize temperature control heating, so that the freezing hidden danger of the airspeed head in a high-altitude low-temperature environment is eliminated, and the airspeed head is prevented from being out of work due to freezing; moreover, the convex cap arranged at the end part of the middle pipe adopts a hemispherical structure, so that the space of a non-heating area can be reduced as much as possible, the heating effectiveness is improved, the icing risk is further eliminated, and the flight safety is further improved;
(3) the through hole in the outer sleeve of the airspeed tube is of a three-section stepped structure (the tail part is maximum, the front part is minimum), when the airspeed tube is installed, the outer sleeve is sleeved from the front end to the rear end of the middle tube, the heating wire can be prevented from being extruded, the front part of the outer sleeve is ensured to be attached to the front end of the middle tube after the installation, the convex cap is installed after the sleeving is completed, the outer sleeve can be reliably fixed on the periphery of the middle tube, and therefore the relative motion between the outer sleeve and the middle tube is;
(4) the outer wall surface of the outer sleeve of the airspeed head is streamline, so that the pressure on the side surface of the outer sleeve can be reduced when the unmanned aerial vehicle flies, the damage rate of the airspeed head is reduced, and the service life of the airspeed head is ensured.
Drawings
Fig. 1 is a schematic cross-sectional structure diagram of a pitot tube of the present invention;
FIG. 2 is a schematic view of the enlarged partial structure of FIG. 1;
fig. 3 is a schematic structural view of the assembled base and middle tube of a pitot tube of the present invention;
FIG. 4 is an enlarged partial schematic view of FIG. 3;
fig. 5 is a schematic structural view of an outer sleeve of a pitot tube according to the present invention;
fig. 6 is a schematic view of the inner structure of the outer sleeve of fig. 5.
The meaning of the reference symbols in the figures: 1. the device comprises a base, 101, an installation part, 102, a supporting part, 103, a metal column, 2, an outer sleeve, 3, a middle pipe, 4, an airflow channel, 5, a convex cap, 6, a heating wire, 7 and a thermistor.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Referring to fig. 1, the utility model discloses an airspeed head is applicable to middle-size and small-size fixed wing unmanned aerial vehicle, specifically includes: the base 1, the outer sleeve 2 and the middle tube 3 are all made of aluminum alloy materials. An air flow channel 4 is formed in the middle pipe 3 along the axial direction, the air flow is guided to an inductor at the tail end of the channel through the air flow channel 4, the impact force of the air flow is sensed through the inductor, and the dynamic pressure is converted through electronic equipment or a monitoring device, so that the real-time flight speed of the airplane can be detected. For convenient fixed with airspeed head and unmanned aerial vehicle, as shown in fig. 3, base 1 is equipped with a metal column 103 on keeping away from well tubular 3's terminal surface, and metal column 103 is formed with the screw thread along circumference, can be with metal column 103 and organism fixed connection through threaded connection to install airspeed head on the organism fast.
The utility model discloses an among the airspeed head, outer tube 2 and well pipe 3 all pass through screw thread mode fixed connection with base 1, do not use the screw to improve the convenience of installation and maintenance. As shown in fig. 3, the base 1 is formed with a mounting portion 101 and a supporting portion 102 which are coaxially arranged, the mounting portion 101 is formed with an internal thread and an external thread, one end of the middle tube 3 is fixedly connected with the internal thread of the mounting portion 101 of the base 1, and the outer sleeve 2 is sleeved outside the middle tube 3 and the end of the outer sleeve is fixedly connected with the external thread of the mounting portion 101 of the base 1, so that a main structure of the pitot tube is formed. Furthermore, as shown in fig. 3 and 4, a convex cap 5 is installed on the other end of the middle pipe 3 far from the base 1, and is fixed with the middle pipe 3 through threaded connection. Thus, after the airspeed tube is assembled, the outer sleeve 2 is limited between the convex cap 5 and the base 1, and the outer sleeve 2 and the middle tube 3 of the airspeed tube can be prevented from generating axial relative displacement.
As shown in fig. 2 and 3, a heating wire 6 is wound around the peripheral wall of the middle tube 3, the heating wire 6 is connected with a thermistor 7, the heating wire 6 can be a 12V dc low-power heating wire, and a high-temperature insulating tape is wound on the outside, or the heating wire 6 itself is directly an insulating heating wire. The thermistor 7 is fixedly hidden in the mounting seat through the heat-conducting silica gel, and of course, enough space position for accommodating the thermistor 7 is reserved in the mounting seat. Therefore, temperature control heating can be realized through the temperature sensing element (thermistor 7) and the heating element (heating wire 6), the icing hidden danger of the airspeed head in a low-temperature environment is eliminated, and the airspeed head is prevented from losing efficacy due to icing.
Further, the utility model discloses an airspeed head still includes a control panel, and this control panel is connected with thermistor 7, can realize long-range settlement target temperature, carries out temperature detection and control circuit break-make heating, and the control panel generally sets up on unmanned aerial vehicle's integrated management board, realizes communication and signal transmission through wired or wireless mode with thermistor 7.
It should be noted that the convex cap 5 at the end of the middle tube 3 adopts a hemispherical structure, so as to reduce the space of the non-heating area as much as possible, improve the heating effectiveness, further eliminate the risk of icing, and further improve the flight safety.
The utility model discloses a design of outer tube 2 is also very unique, see figure 5, and its outer wall is streamlined, and unmanned aerial vehicle can reduce the pressure of outer tube 2 sides when flying, reduces the spoilage of airspeed tube, ensures the life of airspeed tube. Referring to fig. 6, the through hole on the inner wall surface of the outer sleeve 2 is a three-section stepped through hole, the inner through hole corresponding to the mounting seat has the largest aperture, and the aperture corresponding to the middle tube 3 is two-section stepped. This is because a small section of the non-wound heating wire 6 is left at the front end of the middle tube 3, the inner diameter of the outer tube 2 corresponding to the section is the smallest, so that the outer tube 2 is tightly attached to the middle tube 3 where the heating wire 6 is not wound, and the inner diameter of the outer tube 2 where the heating wire 6 is wound is slightly larger, so as to avoid extruding the heating wire 6. When the outer sleeve 2 is installed, the outer sleeve 2 is sleeved from the front end to the rear end of the middle tube 3, the heating wire 6 can be prevented from being extruded, the front portion of the outer sleeve 2 can be ensured to be attached to the front end of the middle tube 3 after installation, the convex cap 5 is installed after the sleeving is completed, and the outer sleeve 2 can be reliably fixed on the periphery of the middle tube 3 so as to limit the relative displacement or rotation between the outer sleeve 2 and the middle tube 3 of the airspeed tube.
To sum up, the utility model discloses an airspeed head is formed by base 1, outer tube 2 and the equipment of well pipe 3, and the structure is ingenious reasonable, wholly need not the screw fixation, has improved the convenience of installation and maintenance, still installs a protruding cap 5 in well 3 tip of pipe in order to play limiting displacement to outer tube 2, makes airspeed head overall structure more reliable. Moreover, this airspeed head can prevent that unmanned aerial vehicle from blocking up the problem because freezing that the temperature is low to lead to when high altitude flies, avoids the airspeed head to become invalid, and then ensures flight safety. Therefore, the unmanned aerial vehicle using the airspeed head is higher in safety and higher in practicability.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It should be understood by those skilled in the art that the above embodiments do not limit the present invention in any way, and all technical solutions obtained by adopting equivalent replacement or equivalent transformation fall within the protection scope of the present invention.
Claims (10)
1. A airspeed head for unmanned aerial vehicle, characterized by, includes: the base is provided with an installation 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 installation 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, and the outer sleeve is sleeved outside the middle pipe and the end part of the outer sleeve is fixedly connected with the installation part of the base.
2. The pitot tube of claim 1, wherein the base has a metal post on the end surface away from the middle tube, the metal post having a thread formed circumferentially.
3. The pitot tube of claim 1, wherein a convex cap is mounted on the other end of the middle tube away from the base, the convex cap is of a hemispherical structure and is fixed to the middle tube by threaded connection.
4. The pitot tube of claim 1, wherein the thermistor is secured within the mounting cup by thermally conductive silicone.
5. The pitot tube of claim 1, wherein the inner wall surface through hole of the outer sleeve is three stepped through holes, and the outer wall surface of the outer sleeve is streamlined.
6. The pitot tube of claim 1, wherein the base, outer sleeve and middle tube are made of aluminum alloy.
7. The pitot tube of any of claims 1-6, further comprising a control board, wherein the control board is connected to the thermistor.
8. The pitot tube of claim 7, wherein the heating wire is a 12V DC low power heating wire, and a high temperature insulating tape is wound on the outside of the heating wire.
9. The pitot tube of claim 7, wherein the heating wire is a 12V dc low power insulated heating wire.
10. The utility model provides a fixed wing unmanned aerial vehicle, includes the organism, its characterized in that still includes the airspeed head for the unmanned aerial vehicle of any one of claims 1-9, the base of airspeed head passes through screw thread fixed connection with the organism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020353771.XU CN211402422U (en) | 2020-03-19 | 2020-03-19 | Airspeed head and fixed wing unmanned aerial vehicle for unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020353771.XU CN211402422U (en) | 2020-03-19 | 2020-03-19 | Airspeed head and fixed wing unmanned aerial vehicle for unmanned aerial vehicle |
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| CN211402422U true CN211402422U (en) | 2020-09-01 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113619779A (en) * | 2021-08-16 | 2021-11-09 | 佛山智壹科技有限公司 | Hang up fixed wing unmanned aerial vehicle |
| CN113674596A (en) * | 2021-09-06 | 2021-11-19 | 北京理工大学 | Airspeed tube teaching demonstration device based on Bernoulli principle |
| CN116552773A (en) * | 2023-03-29 | 2023-08-08 | 哈尔滨理工大学 | Aircraft wing with good anti-icing effect |
-
2020
- 2020-03-19 CN CN202020353771.XU patent/CN211402422U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113619779A (en) * | 2021-08-16 | 2021-11-09 | 佛山智壹科技有限公司 | Hang up fixed wing unmanned aerial vehicle |
| CN113619779B (en) * | 2021-08-16 | 2023-06-02 | 佛山智壹科技有限公司 | Unmanned aerial vehicle with vertical fixed wing |
| CN113674596A (en) * | 2021-09-06 | 2021-11-19 | 北京理工大学 | Airspeed tube teaching demonstration device based on Bernoulli principle |
| CN116552773A (en) * | 2023-03-29 | 2023-08-08 | 哈尔滨理工大学 | Aircraft wing with good anti-icing effect |
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