CN212766782U - Simple airspeed tube mechanism suitable for unmanned aerial vehicle - Google Patents
Simple airspeed tube mechanism suitable for unmanned aerial vehicle Download PDFInfo
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- CN212766782U CN212766782U CN202021226016.1U CN202021226016U CN212766782U CN 212766782 U CN212766782 U CN 212766782U CN 202021226016 U CN202021226016 U CN 202021226016U CN 212766782 U CN212766782 U CN 212766782U
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Abstract
The utility model discloses a simple pitot tube mechanism suitable for an unmanned aerial vehicle, which comprises a machine body of the unmanned aerial vehicle and a pitot tube component of the pitot tube mechanism, the airspeed head component consists of an airflow conveying structure and an airflow pressure measuring structure, one side of the machine body is provided with a machine head, the airflow conveying structure is fixedly arranged at the position close to the machine head of the machine body, one end of the air flow conveying structure penetrates and extends into the machine body, the air flow pressure measuring structure is arranged on the upper end surface of the machine body far away from the air flow conveying structure, one end of the airflow conveying structure penetrating into the machine body is communicated and connected with an airflow interface of the airflow pressure measuring structure through a connecting hose, airflow transport structure includes first airspeed head, airspeed head spring, second airspeed head and nut, circulation pipeline has all been seted up to the inside of first airspeed head and second airspeed head. The utility model discloses simple structure, convenient assembling, manufacturing cost is lower, can be applicable to unmanned aerial vehicle, and the practicality is higher.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle equipment field specifically is a simple and easy airspeed tube mechanism suitable for unmanned aerial vehicle.
Background
The airspeed head is also called pitot tube, total pressure pipe, total-static pressure pipe, and it is total pressure and the static pressure of feeling the air current to the pressure data transfer who will record sends atmospheric data computer, flight instrument's device, this kind of aviation device of airspeed head is mainly used for measuring flying speed, still has other multiple functions simultaneously concurrently, and in unmanned aerial vehicle's flight operation, need measure flying speed, this just need use airspeed head mechanism.
And current airspeed tube mechanism is generally the size great, the processing cost is higher and the structure is complicated, and unmanned aerial vehicle is because manufacturing cost, load capacity and self overall dimension's restriction, the great and higher airspeed tube of processing cost of unsuitable mounting dimension, need have a simple and easy airspeed tube mechanism that can satisfy unmanned aerial vehicle flight control.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a simple and easy airspeed tube mechanism suitable for unmanned aerial vehicle to solve traditional airspeed tube mechanism general size great, the processing cost is higher and the structure is complicated, thereby make its problem that is not convenient for be applicable to unmanned aerial vehicle equipment.
In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a simple and easy airspeed tube mechanism suitable for unmanned aerial vehicle, includes unmanned aerial vehicle's organism and airspeed tube assembly of airspeed tube mechanism, airspeed tube assembly comprises air current transport structure and air current pressure measurement structure, one side of organism is provided with the aircraft nose, air current transport structure fixed mounting is close to in its aircraft nose position department in the organism mouth, just the one end that the air current was carried runs through and extends to inside the organism, air current pressure measurement structrual installation is kept away from in air current transport structure department in the upper end surface of organism, air current transport structure runs through the air current interface intercommunication connection of connecting hose and air current pressure measurement structure to the inside one end of organism.
Preferably, the air flow conveying structure comprises a first pitot tube, a pitot tube spring, a second pitot tube and a nut, wherein a circulation pipeline is arranged inside the first pitot tube and the second pitot tube, one end of the first pitot tube is inserted into the pitot tube spring and fixedly connected with the pitot tube spring, the first pitot tube is inserted into one end inside the pitot tube spring, a hose connector is arranged at one end of the second pitot tube, which is far away from the first pitot tube, and one end of the second pitot tube is inserted into the pitot tube spring and is fixedly connected with the same end of the first pitot tube spring, a threaded connector is arranged at one end of the second pitot tube, which is far away from the pitot tube spring, the threaded connector penetrates through the inside of the machine body, the nut is in threaded connection with the threaded connector, and the threaded connector is fixedly mounted at the machine body by abutting against the nut and, the one end of coupling hose runs through the inside of threaded connection head and the inside flow pipe of second airspeed tube, just coupling hose runs through the one end and the hose connection head fixed connection of threaded connection head and second airspeed tube.
Preferably, the connecting hose is made of a silica gel material.
Preferably, the hose connector is a tapered connector that is tipped over.
Preferably, the airflow pressure measuring structure comprises a flight control module, the flight control module is fixedly installed at the top of the machine body and is far away from the first airspeed head, and one end, far away from the hose connector, of the connecting hose is communicated with an airflow interface of the flight control module.
Preferably, first airspeed head, hose connection head, second airspeed head and threaded connection head all adopt aluminum alloy material to make.
The utility model provides a simple and easy airspeed tube mechanism suitable for unmanned aerial vehicle possesses following beneficial effect:
the utility model discloses a be provided with first pitot tube, the pitot tube spring, the second pitot tube, coupling hose and flight control module, make its simple structure of whole pitot tube mechanism, the production and processing cost is lower, and the size is less, be convenient for install on unmanned aerial vehicle equipment, and when unmanned aerial vehicle flies, can be through first pitot tube, cooperation between second pitot tube and the coupling hose, carry the air current to flight control module department, then measure its dynamic pressure through the flight control module, static pressure in the simultaneous measurement unmanned aerial vehicle, calculate unmanned aerial vehicle's flying speed, the practicality is higher.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view showing the connection hose according to the present invention;
FIG. 3 is a top view of the connection hose of the present invention;
fig. 4 is an enlarged schematic view of a portion a in fig. 2.
In the figure: 1. a body; 2. an airflow interface; 3. a first pitot tube; 4. a pitot tube spring; 5. a second pitot tube; 6. a nut; 7. a connecting hose; 8. a hose connector; 9. a threaded connector; 10. and a flight control module.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
As shown in fig. 1-4, the utility model provides a technical solution: the utility model provides a simple and easy airspeed tube mechanism suitable for unmanned aerial vehicle, includes unmanned aerial vehicle's organism 1 and airspeed tube assembly of airspeed tube mechanism, airspeed tube assembly comprises air current transport structure and air current pressure measurement structure, one side of organism 1 is provided with the aircraft nose, air current transport structure fixed mounting is close to in its aircraft nose position department in 1 mouthful of organism, just the one end that the air current was carried runs through and extends to 1 insidely of organism, air current pressure measurement structrual installation is kept away from in air current transport structure department on the upper end surface of organism 1, air current transport structure runs through to 2 intercommunications of air current interface of 1 inside one end of organism through coupling hose 7 and air current pressure measurement structure and is connected.
The air flow conveying structure comprises a first pitot tube 3, a pitot tube spring 4, a second pitot tube 5 and a nut 6, wherein a circulation pipeline is arranged inside the first pitot tube 3 and the second pitot tube 5, one end of the first pitot tube 3 is inserted into the inside of the pitot tube spring 4 and is fixedly connected with the pitot tube spring 4, the first pitot tube 3 is inserted into one end inside the pitot tube spring 4 and is provided with a hose connector 8, one end of the second pitot tube 5 is inserted into one end of the pitot tube spring 4 far away from the first pitot tube 3, the second pitot tube 5 is fixedly connected with the pitot tube spring 4, one end of the second pitot tube 5 far away from the pitot tube spring 4 is provided with a threaded connector 9, the threaded connector 9 is inserted into the inside of the machine body 1 in a penetrating way, the nut 6 is connected with the threaded connector 9 through a thread, the threaded connector 9 is fixedly mounted at the position of the machine body 1 through the abutting connection between the nut 6 and the interior of the machine body 1, one end of the connecting hose 7 penetrates through a flow pipeline inside the threaded connector 9 and a flow pipeline inside the second pitot tube 5, and one end of the connecting hose 7 penetrates through the threaded connector 9 and the second pitot tube 5 and is fixedly connected with the hose connector 8, so that air flow enters from the first pitot tube 3 in the flying process of the unmanned aerial vehicle, the pitot tube spring 4 can buffer the pressure on the first pitot tube 3, after the air flow enters the hose connector 8, the air flow is conveyed to the flight control module 10 through the connecting hose 7, the dynamic pressure of the air flow is measured by the flight control module 10, the static pressure in the unmanned aerial vehicle is measured at the same time, the flying speed of the unmanned aerial vehicle is calculated, and the practicability is;
the connecting hose 7 is made of a silica gel material, and the silica gel has good electrical insulation performance, aging resistance, high and low temperature resistance and long service life;
the hose connector 8 is a tilted conical connector, so that the connecting hose 7 is not easy to separate from the hose connector 8 to cause falling off;
the airflow pressure measuring structure comprises a flight control module 10, the flight control module 10 is fixedly installed at the top of the machine body 1 far away from the first airspeed head 3, and one end, far away from the hose connector 8, of the connecting hose 7 is communicated and connected with an airflow interface 2 of the flight control module 10, so that the dynamic airflow pressure and the static pressure in the unmanned aerial vehicle can be measured through the flight control module 10, and the flying speed of the unmanned aerial vehicle is calculated;
The working principle is as follows: during the process of unmanned aerial vehicle flight, the air current gets into from first pitot tube 3, and pitot tube spring 4 can cushion the pressure that first pitot tube 3 received, back in the air current gets into hose connection head 8, rethread coupling hose 7 is carried it to flying among the control module 10, measure its dynamic pressure by flying control module 10, simultaneously measure the static pressure in the unmanned aerial vehicle, calculate unmanned aerial vehicle's flying speed, and its overall structure of whole pitot tube mechanism is simple, therefore, the production cost is lower, the size is less, can be applicable to unmanned aerial vehicle, high practicability.
In the description of the present invention, it should be understood that the indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.
In the present invention, unless otherwise explicitly specified or limited, for example, it may be fixedly connected, detachably connected, or integrated; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, and may be connected through the inside of two elements or in an interaction relationship between two elements, unless otherwise specifically defined, and the specific meaning of the above terms in the present invention will be understood by those skilled in the art according to specific situations.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides a simple and easy airspeed tube mechanism suitable for unmanned aerial vehicle, includes unmanned aerial vehicle's organism (1) and airspeed tube assembly of airspeed tube mechanism, its characterized in that: the airspeed tube assembly comprises air flow conveying structure and air flow pressure measuring structure, one side of organism (1) is provided with the aircraft nose, air flow conveying structure fixed mounting is close to in its aircraft nose position department in organism (1) mouth, just the one end that the air flow carried runs through and extends to inside organism (1), air flow pressure measuring structure installs and keeps away from in air flow conveying structure department on the upper end surface of organism (1), air flow conveying structure runs through to the one end of organism (1) inside and is connected through air flow interface (2) intercommunication of coupling hose (7) and air flow pressure measuring structure.
2. The pitot tube mechanism suitable for unmanned aerial vehicle of claim 1, characterized in that: the air flow conveying structure comprises a first airspeed head (3), an airspeed head spring (4), a second airspeed head (5) and a nut (6), wherein a circulation pipeline is arranged inside the first airspeed head (3) and the second airspeed head (5), one end of the first airspeed head (3) is inserted into the inside of the airspeed head spring (4) and is fixedly connected with the airspeed head spring (4), a hose connector (8) is arranged at one end of the first airspeed head (3) which is inserted into the inside of the airspeed head spring (4), one end of the second airspeed head (5) is inserted into the airspeed head spring (4) and is far away from the inside of one end of the first airspeed head (3), the second airspeed head (5) is fixedly connected with the airspeed head spring (4) in the same way, and a threaded connector (9) is arranged at one end of the second airspeed head (5) which is far away from the airspeed head spring (4), threaded connection head (9) run through the inside of inserting to organism (1), nut (6) and threaded connection head (9) pass through threaded connection, threaded connection head (9) are through the inside butt fixed mounting of nut (6) and organism (1) in organism (1) department, the one end of coupling hose (7) runs through the inside of threaded connection head (9) and the inside pipeline that flows of second airspeed tube (5), just coupling hose (7) run through the one end and hose connection head (8) fixed connection of threaded connection head (9) and second airspeed tube (5).
3. The pitot tube mechanism suitable for unmanned aerial vehicle of claim 1, characterized in that: the connecting hose (7) is made of a silica gel material.
4. The pitot tube mechanism suitable for unmanned aerial vehicle of claim 2, characterized in that: the hose connector (8) is a toppled conical connector.
5. The pitot tube mechanism suitable for unmanned aerial vehicle of claim 1, characterized in that: airflow pressure measurement structure is including flying control module (10), fly control module (10) fixed mounting keep away from in first airspeed tube (3) department at the top of organism (1), coupling hose (7) are kept away from the one end of hose connection head (8) and are connected with airflow interface (2) intercommunication of flying control module (10).
6. The pitot tube mechanism suitable for unmanned aerial vehicle of claim 2, characterized in that: first airspeed head (3), hose connector (8), second airspeed head (5) and threaded connection head (9) all adopt aluminum alloy material to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021226016.1U CN212766782U (en) | 2020-06-29 | 2020-06-29 | Simple airspeed tube mechanism suitable for unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021226016.1U CN212766782U (en) | 2020-06-29 | 2020-06-29 | Simple airspeed tube mechanism suitable for unmanned aerial vehicle |
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| CN212766782U true CN212766782U (en) | 2021-03-23 |
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| CN202021226016.1U Active CN212766782U (en) | 2020-06-29 | 2020-06-29 | Simple airspeed tube mechanism suitable for unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113866451A (en) * | 2021-12-06 | 2021-12-31 | 大同航源众诚动力科技有限公司 | Civil aircraft airspeed head self-separation protective sleeve |
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2020
- 2020-06-29 CN CN202021226016.1U patent/CN212766782U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113866451A (en) * | 2021-12-06 | 2021-12-31 | 大同航源众诚动力科技有限公司 | Civil aircraft airspeed head self-separation protective sleeve |
| CN113866451B (en) * | 2021-12-06 | 2022-02-18 | 大同航源众诚动力科技有限公司 | Civil aircraft airspeed head self-separation protective sleeve |
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