CN219608952U - Unmanned aerial vehicle and airspeed system thereof - Google Patents
Unmanned aerial vehicle and airspeed system thereof Download PDFInfo
- Publication number
- CN219608952U CN219608952U CN202320907572.2U CN202320907572U CN219608952U CN 219608952 U CN219608952 U CN 219608952U CN 202320907572 U CN202320907572 U CN 202320907572U CN 219608952 U CN219608952 U CN 219608952U
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- airspeed
- unmanned aerial
- aerial vehicle
- shell
- tube assembly
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model discloses an unmanned aerial vehicle and an airspeed system thereof, and relates to the technical field of unmanned aerial vehicle equipment. The airspeed system is convenient to install and good in universality, so that the airspeed system can be matched with unmanned aerial vehicles of different models, and the aerodynamic resistance can be reduced. It will be appreciated that mounting the airspeed meter in the direction of extension of the airspeed tube assembly reduces the space occupied by the airspeed system in the overall structure, so that the airspeed system protrudes less from the surface of the unmanned aerial vehicle after being mounted to the unmanned aerial vehicle, thereby reducing aerodynamic drag.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicle equipment, in particular to an airspeed system. The utility model also relates to an unmanned aerial vehicle with the airspeed system.
Background
Currently, industrial unmanned aerial vehicles are increasingly widely used in map mapping, geological survey, disaster monitoring, meteorological detection, air traffic control, border patrol monitoring, emergency rescue, logistics, military use and other aspects.
Airspeed systems are known to be critical to the functioning of an aircraft, and to be responsible for its important mission during a safe take-off and landing. The airspeed system comprises an airspeed tube assembly and an airspeed meter, wherein the airspeed tube assembly is used for detecting the total pressure and the static pressure of air flow, converting the detected pressure into digital information data through the airspeed meter and transmitting the digital information data to the flight control computer, and the airspeed tube assembly and the airspeed meter are one of main components of the aircraft, and the performance of the airspeed tube assembly and the airspeed meter is directly related to the use safety of the aircraft. Airspeed systems of the prior art are extremely important measurement tools on board an aircraft, with their mounting locations generally directly in front of the nose, in front of the tail or wing tip. However, the existing airspeed system has the defects of more structural parts, complex installation, limited use and incapability of being universally used for aircrafts of various models, and meanwhile, after the airspeed system is installed, the structure of the airspeed system protrudes out of the surface of an unmanned aerial vehicle body more, so that aerodynamic resistance is high, and the flying of the unmanned aerial vehicle is influenced. Accordingly, there is a need in the art for an airspeed system that is easy to install, versatile, and that reduces aerodynamic drag.
Disclosure of Invention
The utility model aims to provide an airspeed system which is convenient to install, good in universality and capable of reducing pneumatic resistance. It is another object of the present utility model to provide a drone including the airspeed system described above.
To achieve the above object, the present utility model provides an airspeed system comprising:
the shell is used for connecting the unmanned aerial vehicle;
the airspeed tube assembly extends out of one end of the shell and is used for detecting the pressure parameter of the airflow;
the other end of the shell is provided with an airspeed data output interface;
and the airspeed meter is arranged in the shell and positioned in the extending direction of the airspeed tube assembly and is used for outputting the detected pressure parameter through the airspeed data output interface.
In some embodiments, the housing includes a receiving structure having a receiving cavity for receiving the pitot meter and a connecting tube disposed on a side of the housing adjacent the pitot tube assembly for connecting to a mounting ring external to the pitot tube assembly.
In some embodiments, the housing further comprises a protrusion, the protrusion is arranged between the accommodating structure and the connecting pipe, the protrusion protrudes from the accommodating structure along the first direction, the protrusion is provided with a connecting structure, and the housing is connected with the unmanned aerial vehicle through the connecting structure.
In some embodiments, the connection tube is provided with a threaded surface to which the mounting ring is threaded.
In some embodiments, the housing includes an upper shell and a lower shell, the upper shell and the lower shell being closable.
In some embodiments, both the upper and lower shells are internally provided with a stop station for stopping the bottom plate of the airspeed meter.
In some embodiments, both the upper and lower shells are identical in structure.
In some embodiments, the pitot tube assembly includes a pitot tube and a pitot tube, the pitot tube being connected to the pitot meter by the pitot tube.
The utility model also provides an unmanned aerial vehicle comprising the airspeed system of any one of the above.
In some embodiments, the drone is provided with a universal mounting interface for mounting the airspeed system.
Compared with the background art, the airspeed system provided by the embodiment of the utility model is used for an unmanned aerial vehicle and comprises a shell, an airspeed tube assembly and an airspeed meter, wherein the shell is used for being connected with the unmanned aerial vehicle, the airspeed tube assembly extends out of one end of the shell and is used for detecting pressure parameters of air flow, the pressure parameters comprise total pressure and static pressure of the air flow, an airspeed data output interface is arranged at the other end of the shell, the airspeed meter is arranged in the shell and is positioned in the extending direction of the airspeed tube assembly, and the airspeed meter is used for outputting the pressure parameters detected by the airspeed tube assembly through the airspeed data output interface. Compared with the traditional airspeed system, the airspeed system provided by the embodiment of the utility model has the advantages that the airspeed meter is arranged in the extending direction of the airspeed tube assembly, namely, the airspeed meter and the airspeed tube assembly are arranged in a straight shape, so that the airspeed system is convenient to install and good in universality, the airspeed system can be matched with unmanned aerial vehicles of different models, and the aerodynamic resistance can be reduced. It can be appreciated that, because the existing airspeed meter and the airspeed tube assembly form a U-shaped structure, the airspeed meter is arranged on the extending direction of the airspeed tube assembly, the space occupied by the airspeed system on the whole structure can be reduced, and the airspeed system protrudes out of the surface of the unmanned aerial vehicle body after being arranged on the unmanned aerial vehicle, so that the aerodynamic resistance is reduced.
Drawings
In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present utility model, and that other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the overall structure of a hollow speed system according to an embodiment of the present utility model;
FIG. 2 is an exploded view of the airspeed system of FIG. 1;
FIG. 3 is a schematic diagram of the installation of a hollow speed system and an unmanned aerial vehicle wing in an embodiment of the present utility model;
FIG. 4 is a schematic diagram of an embodiment of the present utility model after assembly of a hollow speed system with an unmanned wing;
fig. 5 is a schematic diagram of an assembled hollow speed system and a head of an unmanned aerial vehicle according to an embodiment of the present utility model.
Wherein:
1-airspeed system, 2-wing, 3-nose;
11-housing, 12-pitot tube assembly, 13-airspeed meter, 14-mounting ring, 15-first bolt, 16-first nut, 17-second bolt, 18-second nut;
21-a universal mounting interface;
111-an accommodating structure, 112-a connecting pipe, 113-a bulge, 114-an upper shell, 115-a lower shell and 116-a limiting table;
121-airspeed tube, 122-airspeed hose;
1111-receiving cavity, 1121-threaded surface, 1131-connecting structure, 1132-mounting screw.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
The present utility model will be further described in detail below with reference to the drawings and detailed description for the purpose of enabling those skilled in the art to better understand the aspects of the present utility model.
The terms "upper end, lower end, left side, right side" and the like are defined based on the drawings of the specification.
Referring to fig. 1 to 5, fig. 1 is a schematic diagram of the overall structure of a hollow speed system according to an embodiment of the present utility model; FIG. 2 is an exploded view of the airspeed system of FIG. 1; FIG. 3 is a schematic diagram of the installation of a hollow speed system and an unmanned aerial vehicle wing in an embodiment of the present utility model; FIG. 4 is a schematic diagram of an embodiment of the present utility model after assembly of a hollow speed system with an unmanned wing; fig. 5 is a schematic diagram of an assembled hollow speed system and a head of an unmanned aerial vehicle according to an embodiment of the present utility model.
As shown in fig. 1 and fig. 2, the airspeed system 1 provided by the embodiment of the utility model is used for an unmanned aerial vehicle and comprises a shell 11, an airspeed tube assembly 12 and an airspeed meter 13, wherein the shell 11 is used for being connected with the unmanned aerial vehicle, the airspeed tube assembly 12 extends out of one end of the shell 11 and is used for detecting pressure parameters of air flow, the pressure parameters comprise total pressure and static pressure of the air flow, an airspeed data output interface is arranged at the other end of the shell 11, the airspeed meter 13 is installed in the shell 11, the airspeed meter 13 is located in the extending direction of the airspeed tube assembly 12, and the airspeed meter 13 is used for outputting the pressure parameters detected by the airspeed tube assembly 12 through the airspeed data output interface.
The shell 11 is arranged outside the airspeed meter 13 for protection, so that the purposes of dust prevention and water prevention can be achieved. At the same time, the airspeed meter 13 is arranged at the rear of the airspeed tube assembly 12, so that the airspeed tube assembly 12 is conveniently connected with the airspeed tube assembly 12, the space utilization is the highest, and the airspeed meter 13 is supported and fixed by utilizing a box type structure and the airspeed meter 13 is protected.
Compared with the traditional airspeed system 1, the airspeed system 1 provided by the embodiment of the utility model has the airspeed meter 13 arranged in the extending direction of the airspeed tube assembly 12, namely, the airspeed meter 13 and the airspeed tube assembly 12 are arranged in a straight line, so that the purpose of reducing the envelope space is achieved, and the airspeed system 1 is convenient to install and good in universality, so that the airspeed system 1 can be matched with unmanned aerial vehicles of different models, and the aerodynamic resistance can be reduced.
It will be appreciated that, because the existing airspeed meter 13 and airspeed tube assembly 12 both form a U-shaped configuration, mounting airspeed meter 13 in the direction of extension of airspeed tube assembly 12 may reduce the space occupied by airspeed system 1 in the overall structure, making the structure of airspeed system 1 that protrudes from the surface of the unmanned aerial vehicle after being mounted to the unmanned aerial vehicle less, thereby reducing aerodynamic drag.
In some embodiments, the shell 11 includes a accommodating structure 111 and a connecting pipe 112, where the accommodating structure 111 has an accommodating cavity 1111 for accommodating the airspeed gauge 13, and the accommodating structure 111 may be a square box body, and when installed, the box body is opened, the airspeed gauge 13 connected with the airspeed tube assembly 12 is placed into the box body, and then the box body is closed; a connecting tube 112 is provided on the side of the housing 11 adjacent the pitot tube assembly 12. The connecting tube 112 is used to connect to the mounting ring 14 outside of the pitot tube assembly 12.
It should be noted that, since the portion of the pitot tube assembly 12 extending out of the housing 11 is long, a supporting structure needs to be added to support and fix the pitot tube assembly 12 extending out of the housing 11, so as to ensure stability and reliability of the pitot tube assembly 12. Specifically, a mounting ring 14 is detachably connected to the connection pipe 112 of the housing 11, and the mounting ring 14 is sleeved on the outside of the pitot tube assembly 12, so as to support and fix the pitot tube assembly 12.
In some embodiments, the outer wall of the connection tube 112 is provided with a threaded surface 1121 and the mounting ring 14 is provided with a threaded hole through which the mounting ring 14 is threadedly engaged with the threaded surface 1121 to threadably engage the connection tube 112. This corresponds to further extension of the connecting tube 112 to ensure support stability and reliability of the pitot tube assembly 12.
It will be appreciated that for supporting and securing the pitot tube assembly 12 for installation, the mounting structure is designed to support pitot tube 121 with the tubular shape of pitot tube 121 while utilizing a mechanical threaded structure for clamping and securing pitot tube 121.
In some embodiments, the housing 11 further includes a protrusion 113, the protrusion 113 is disposed between the accommodating structure 111 and the connecting pipe 112, the protrusion 113 protrudes from the accommodating structure 111 along the first direction, the protrusion 113 is provided with a connection structure 1131, and the housing 11 is connected to the unmanned aerial vehicle through the connection structure 1131.
Specifically, the first direction is a direction perpendicular to the axis of the pitot tube assembly 12 in the horizontal plane, in other words, the protrusions 113 are protruded along the left and right sides of the accommodating structure 111, which is provided for the purpose of facilitating the fixing of the pitot system 1 to the unmanned aerial vehicle through the connection structure 1131 by providing the connection structure 1131 on the protrusions 113.
In this way, the protrusion 113 and the accommodating structure 111 may be combined to form a T-shaped structure.
It will be appreciated that taking the airspeed system 1 as an example of being mounted on the unmanned aerial vehicle wing 2, the unmanned aerial vehicle wing 2 is provided with a universal mounting interface 21, and the universal mounting interface 21 can accommodate at least part of the housing 11 structure of the airspeed system 1, in this embodiment, the protrusion 113 and the housing structure (accommodating structure 111) on the side of the protrusion 113 away from the mounting ring 14 can be accommodated in the universal mounting interface 21 of the wing 2, and then the protrusion 113 is fixedly mounted on the wing 2 through the connecting structure 1131, so as to realize the fixed mounting of the airspeed system 1 on the unmanned aerial vehicle wing 2.
Preferably, the coupling structure 1131 includes, but is not limited to, a threaded hole, a light hole, or the like, that mates with a removable coupling (such as a bolt or screw) such that the air speed system 1 is fixedly mounted to the drone.
In some embodiments, the housing 11 includes an upper shell 114 and a lower shell 115, the upper shell 114 and the lower shell 115 being closable and connected by a detachable connection.
The structures of the upper case 114 and the lower case 115 may be the same or different, provided that the upper case 114 and the lower case 115 can form a receiving chamber 1111 for receiving the airspeed gauge 13, a connection pipe 112 for connecting the mounting ring 14, and a protrusion 113 disposed between the receiving structure 111 and the connection pipe 112 after being connected by a cap.
Of course, according to actual needs, the upper shell 114 and the lower shell 115 may further pass through the upper shell 114 and the lower shell 115 through a plurality of groups of bolt assemblies to achieve fixed connection. For example, one set of bolt assemblies is provided on the boss 113 and another set of bolt assemblies is provided on the side of the boss 113 remote from the connection tube 112 that extends through the bottom plate of the airspeed meter 13.
In some embodiments, both the upper shell 114 and the lower shell 115 are internally provided with a limiting table 116, the limiting table 116 can be arranged at a corner position of the shell 11, and the limiting table 116 is used for supporting a bottom plate of the airspeed meter 13, so that after the upper shell 114 and the lower shell 115 are in cover connection, the limiting table 116 in the upper shell 114 and the limiting table 116 in the lower shell 115 can be abutted against the bottom plate of the airspeed meter 13 from the upper side and the lower side, thereby ensuring the stability and the reliability of the support of the airspeed meter 13.
The housing 11 may be made of an aluminum alloy material and/or plastic, and the aluminum alloy material and plastic may be used in combination to make the weight lighter while ensuring structural strength.
In some embodiments, pitot tube assembly 12 includes pitot tube 121 and pitot tube 122, with pitot tube 121 being connected to pitot meter 13 by pitot tube 122.
As shown in fig. 2, during assembly, the airspeed tube 121 and the airspeed tube 122 are connected with the airspeed meter 13, placed into the lower shell 115, then covered with the upper shell 114, and connected with the first nut 16 after passing through the protrusion 113 by using the first bolt 15, and connected with the second nut 18 after passing through the accommodating structure 111 and the bottom plate of the airspeed meter 13 by using the second bolt 17, so as to fix the housing 11, and finally the mounting ring 14 is screwed into the connecting tube 112 of the housing 11, thereby completing the assembly of the airspeed system 1.
The unmanned aerial vehicle provided by the utility model comprises the airspeed system 1 described in the specific embodiment, and other parts of the unmanned aerial vehicle can refer to the prior art and are not developed herein.
The unmanned aerial vehicle and the airspeed system 1 thereof have the advantages of simple structure, low cost, light weight, high strength, low structural failure rate and high reliability.
In some embodiments, the drone is provided with a universal mounting interface 21 for mounting the airspeed system 1, and preferably, the universal mounting interface 21 may be a T-slot configuration.
For example, the universal mounting interface 21 may be disposed on the wing 2 of the unmanned aerial vehicle, in this embodiment, the protrusion 113 and the accommodating structure 111 can be all accommodated in the universal mounting interface 21 of the wing 2, and then the protrusion 113 is fixedly mounted on the wing 2 through the cooperation of the detachable connection piece and the connection structure 1131, so as to fixedly mount the airspeed system 1 on the wing 2 of the unmanned aerial vehicle.
As shown in FIG. 3, the airspeed system 1 is mounted on the wing 2 by connecting an output line first, and locking and fixing the airspeed system 1 on the wing 2 by using a mounting screw 1132. The installation effect of the airspeed system 1 on the wing 2 is as shown in fig. 4, the airspeed system 1 has a small convex surface structure and a small cross section, the airspeed system 1 is in a streamline structure, and is integrated with the wing 2, so that the aerodynamic drag is minimum and attractive.
Of course, the airspeed system 1 may also be installed at the position of the nose 3 of the unmanned aerial vehicle, which is not particularly limited herein.
Specifically, when the aircraft nose 3 is installed, the installation process is consistent with that of the wing 2, the installation effect of the airspeed system 1 to the aircraft nose 3 is as shown in fig. 5, the convex surface structure of the airspeed system 1 is small, the cross section is small, the airspeed system 1 is in a streamline structure, the airspeed system 1 and the aircraft nose 3 are integrated, and the aerodynamic resistance is minimum and attractive.
It should be noted that in this specification relational terms such as first and second are used solely to distinguish one entity from another entity without necessarily requiring or implying any actual such relationship or order between such entities.
The unmanned aerial vehicle and the airspeed system thereof provided by the utility model are described in detail above. The principles and embodiments of the present utility model have been described herein with reference to specific examples, the description of which is intended only to facilitate an understanding of the inventive arrangements and their core ideas. It should be noted that it will be apparent to those skilled in the art that various modifications and adaptations of the utility model can be made without departing from the principles of the utility model and these modifications and adaptations are intended to be within the scope of the utility model as defined in the following claims.
Claims (10)
1. An airspeed system, comprising:
a housing;
the airspeed tube assembly extends out of one end of the shell and is used for detecting the pressure parameter of the airflow; the other end of the shell is provided with an airspeed data output interface;
and the airspeed meter is arranged in the shell and positioned in the extending direction of the airspeed tube assembly and is used for outputting the detected pressure parameter through an airspeed data output interface.
2. The airspeed system of claim 1, wherein the housing includes a receiving structure having a receiving chamber for receiving the airspeed meter, and a connecting tube disposed on a side of the housing adjacent the airspeed tube assembly for connecting to a mounting ring external to the airspeed tube assembly.
3. The airspeed system of claim 2, wherein the housing further comprises a protrusion disposed between the receiving structure and the connecting tube, the protrusion protruding from the receiving structure in a first direction, the protrusion being provided with a connecting structure by which the housing is connected to the drone.
4. Airspeed system according to claim 2, wherein the connection tube is provided with a threaded surface to which the mounting ring is screwed.
5. Airspeed system according to any one of claims 1-4, wherein the housing comprises an upper shell and a lower shell, the upper shell being closable with the lower shell.
6. Airspeed system according to claim 5, wherein both the upper and lower shells are internally provided with a stop for limiting the bottom plate of the airspeed meter.
7. The airspeed system of claim 5, wherein the upper housing and the lower housing are identical in structure.
8. The airspeed system of claim 1, wherein the airspeed tube assembly comprises a airspeed tube and an airspeed hose, the airspeed tube being connected to the airspeed meter by the airspeed hose.
9. A drone comprising an airspeed system according to any one of claims 1 to 8.
10. The unmanned aerial vehicle of claim 9, wherein the unmanned aerial vehicle is provided with a universal mounting interface for mounting connection to the airspeed system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320907572.2U CN219608952U (en) | 2023-04-21 | 2023-04-21 | Unmanned aerial vehicle and airspeed system thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320907572.2U CN219608952U (en) | 2023-04-21 | 2023-04-21 | Unmanned aerial vehicle and airspeed system thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219608952U true CN219608952U (en) | 2023-08-29 |
Family
ID=87757098
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320907572.2U Active CN219608952U (en) | 2023-04-21 | 2023-04-21 | Unmanned aerial vehicle and airspeed system thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219608952U (en) |
-
2023
- 2023-04-21 CN CN202320907572.2U patent/CN219608952U/en active Active
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