CN211844923U - Fuel tank device for airplane - Google Patents
Fuel tank device for airplane Download PDFInfo
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- CN211844923U CN211844923U CN202020264212.1U CN202020264212U CN211844923U CN 211844923 U CN211844923 U CN 211844923U CN 202020264212 U CN202020264212 U CN 202020264212U CN 211844923 U CN211844923 U CN 211844923U
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Abstract
The utility model discloses a fuel tank device for aircraft, including aircraft main body frame, the axis left and right sides of aircraft main body frame is fixed respectively and is provided with first oil tank group and the second oil tank group that is used for saving aircraft fuel, and wherein first oil tank group and second oil tank group communicate each other, and pass through the surplus oil mass in the detection component real-time detection oil tank respectively. The utility model discloses think about ingenious, rational in infrastructure, can the current space on the abundant rational utilization aircraft design this oil tank device, and then promote the fuel reserve volume of aircraft when the maximize utilizes the cavity, increase the continuation of the journey mileage, use the panel beating welding to process the oil tank simultaneously, make oil tank cost greatly reduced to through the level sensor in each oil tank, can be convenient read remaining fuel volume percentage.
Description
Technical Field
The utility model relates to an aircraft tank, specific theory relates to a simple structure, can install by the existing space on the rational utilization aircraft, and can save a large amount of aircraft fuel's fuel tank device for aircraft belongs to oil tank system technical field.
Background
The helicopter is widely applied to the fields of environmental survey, scientific research experiments, pesticide spraying, mountain forest fire control and the like, the existing helicopter basically adopts an engine to provide power to drive a rotor wing and a tail rotor to rotate so as to realize flight, the endurance time of the helicopter is one of important indexes for measuring the performance of the helicopter, but the existing fuel tank has small volume, small volume and complex internal structure due to the fact that the helicopter is in a streamline curved surface design, the endurance time is difficult to guarantee, and the overall shape of the existing fuel tank is square and positive, so that the existing fuel tank occupies large space when the existing fuel tank is large in volume and cannot meet the capacity requirement when the existing fuel tank is small in volume.
SUMMERY OF THE UTILITY MODEL
The to-be-solved main technical problem of the utility model is to provide a simple structure can install in the existing space on the rational utilization aircraft, and can save a large amount of aircraft fuel's fuel tank device for aircraft.
In order to solve the technical problem, the utility model provides a following technical scheme:
the utility model provides a fuel tank device for aircraft, includes aircraft main body frame, and the axis left and right sides of aircraft main body frame is fixed respectively and is provided with first oil tank group and the second oil tank group that is used for saving aircraft fuel, first oil tank group and second oil tank group communicate each other, and detect the surplus oil mass in the oil tank constantly through the determine module respectively.
The following is the utility model discloses to above-mentioned technical scheme's further optimization:
first oil tank group includes first oil tank and second oil tank, and the second oil tank sets up the below at first oil tank, and is an organic whole structure through first oil tank frame fixed connection between first oil tank and the second oil tank.
Further optimization: and a first communicating pipe used for communicating the first oil tank with the second oil tank is arranged between the lower end of the first oil tank and the upper end of the second oil tank.
Further optimization: the second oil tank group comprises a third oil tank and a fourth oil tank, the fourth oil tank is arranged below the third oil tank, and the third oil tank and the fourth oil tank are fixedly connected through a second oil tank rack to form an integral structure.
Further optimization: and a second communicating pipe used for communicating the third oil tank with the fourth oil tank is arranged between the lower end of the third oil tank and the upper end of the fourth oil tank.
Further optimization: and a bottom interconnecting pipe used for communicating the second oil tank with the fourth oil tank is arranged between the lower end of the second oil tank and the lower end of the fourth oil tank.
Further optimization: the lowest liquid level section of the bottom interconnecting pipe is communicated with an oil outlet pipe, and the upper end of the first oil tank is fixedly connected with an oil return pipe.
Further optimization: be provided with the exhaust pipe between first oil tank group and the second oil tank group, the exhaust pipe includes main blast pipe, and main blast pipe's upper end intercommunication has the head of loosing gas, and main blast pipe's other end intercommunication has twice blast pipe, and the other end of twice blast pipe communicates with the upper end of first oil tank and third oil tank respectively.
Further optimization: and a communicating air pipe is respectively arranged between the first oil tank and the second oil tank and between the third oil tank and the fourth oil tank.
Further optimization: the detection assembly comprises liquid level sensors which are respectively and independently arranged between the first oil tank and the second oil tank and on the third oil tank and the fourth oil tank, and the output end of each liquid level sensor is electrically connected to the main processor.
The above technical scheme is adopted in the utility model, organize first oil tank and second oil tank respectively through first oil tank frame and second oil tank frame and organize fixed mounting in the both sides of aircraft main part support, then make things convenient for the integral erection, then the convenient fuel tank device for this aircraft is added with the aircraft fuel with the oil filler on user's accessible first oil tank and the third oil tank, then the aircraft fuel in this fuel tank device for the aircraft is provided the engine through going out the oil pipe.
At the moment, air pressure fluctuation in the fuel tank device for the airplane caused by fuel oil filling or fuel oil use can be used for communicating air in the fuel tank with the external atmosphere through the main exhaust pipe, the air dispersing head, the secondary exhaust pipe and the communicating air pipe, and therefore the air pressure in the fuel tank is guaranteed to be normal.
When the quantity of the residual oil in the fuel tank device for the airplane needs to be detected, the residual oil quantity in the corresponding fuel tank can be read through each liquid level sensor, the detection electric signal is transmitted to the main processor, and the main processor calculates the percentage of the residual oil quantity in the current fuel tank.
The above technical scheme is adopted in the utility model, think about ingenious, rational in infrastructure, can the on-plane current space of abundant rational utilization design this oil tank device, and then promote the fuel reserve volume of aircraft when the maximize utilizes the cavity, increase continuation of the journey mileage, use the panel beating welding to process the oil tank simultaneously, make oil tank cost greatly reduced to through the level sensor in each oil tank, can be convenient read remaining fuel volume percentage.
The present invention will be further explained with reference to the drawings and examples.
Drawings
Fig. 1 is a schematic diagram of the overall structure of an embodiment of the present invention;
FIG. 2 is a top view of FIG. 1;
fig. 3 is a schematic structural diagram of the embodiment of the present invention in use.
In the figure: 1-a first tank; 2-a second oil tank; 3-a third oil tank; 4-a fourth tank; 5-a first tank chassis; 6-a first intercommunication tube; 7-a second tank chassis; 8-a second intercommunication tube; 9-bottom interconnecting pipe; 10-an oil outlet pipe; 11-an oil return pipe; 12-oil filler; 13-main exhaust pipe; 14-a gas dispersing head; 15-a secondary exhaust pipe; 16-connecting air pipe; 17-liquid level sensor.
Detailed Description
Referring to fig. 1 to 3, a fuel tank device for an aircraft includes an aircraft main body frame, wherein a first fuel tank set and a second fuel tank set for storing aircraft fuel are respectively and fixedly disposed on left and right sides of a central axis of the aircraft main body frame, the first fuel tank set and the second fuel tank set are communicated with each other, and residual fuel in the fuel tanks is respectively detected in real time through a detection assembly.
The first oil tank group comprises a first oil tank 1 and a second oil tank 2, and the second oil tank 2 is arranged below the first oil tank 1.
The first oil tank 1 and the second oil tank 2 are fixedly connected with a first oil tank frame 5 through a fixed lug plate to form an integral structure.
Be provided with first intercommunication pipe 6 between the lower extreme of first oil tank 1 and the second oil tank 2 upper end, first intercommunication pipe 6 is used for making first oil tank 1 and second oil tank 2 communicate each other.
The second oil tank group comprises a third oil tank 3 and a fourth oil tank 4, and the fourth oil tank 4 is arranged below the third oil tank 3.
And the third oil tank 3 and the fourth oil tank 4 are fixedly connected with each other through a fixed lug plate and a second oil tank frame 7 to form an integral structure.
A second communicating pipe 8 is arranged between the lower end of the third oil tank 3 and the upper end of the fourth oil tank 4, and the second communicating pipe 8 is used for enabling the third oil tank 3 and the fourth oil tank 4 to be communicated with each other.
A bottom interconnection pipe 9 is arranged between the lower end of the second tank 2 and the lower end of the fourth tank 4, the bottom interconnection pipe 9 being used for interconnecting the second tank 2 and the fourth tank 4.
By the design, the first oil tank group and the second oil tank group are fixedly arranged on two sides of the aircraft main body support through the first oil tank frame 5 and the second oil tank frame 7 respectively, and then the integral installation is facilitated.
And the first oil tank 1, the second oil tank 2, the third oil tank 3 and the fourth oil tank 4 are sequentially connected in series through the first interconnecting pipe 6, the second interconnecting pipe 8 and the bottom interconnecting pipe 9 and are communicated with one another, so that more aircraft fuel oil is stored, and the cruising ability of the aircraft is ensured.
The first oil tank 1, the second oil tank 2, the third oil tank 3 and the fourth oil tank 4 are integrally welded by oil extraction metal plates respectively.
The lowest liquid level section of the bottom interconnecting pipe 9 is fixedly communicated with an oil outlet pipe 10 through a three-way connector, and one end, far away from the bottom interconnecting pipe 9, of the oil outlet pipe 10 is communicated with an engine and used for providing fuel oil for the engine.
The upper end of the first oil tank 1 is fixedly connected with an oil return pipe 11, and the oil return pipe 11 is communicated with an engine.
And the first oil tank 1 and the fourth oil tank 4 are respectively provided with an oil filling port 12 on the upper end surfaces thereof, and the oil filling ports 12 are used for filling aircraft fuel for the first oil tank group and the second oil tank group.
Be provided with between first oil tank group and the second oil tank group and be used for discharging the gas in each oil tank, guarantee the normal exhaust pipe of oil tank atmospheric pressure.
The exhaust pipeline comprises a main exhaust pipe 13, the upper end of the main exhaust pipe 13 is communicated with an air dispersing head 14, and one end, far away from the air dispersing head 14, of the main exhaust pipe 13 is communicated with two secondary exhaust pipes 15 through a three-way connector.
One end of the secondary exhaust pipe 15, which is far away from the main exhaust pipe 13, is respectively communicated with the upper ends of the first oil tank 1 and the third oil tank 3.
A communication air pipe 16 is respectively arranged between the first oil tank 1 and the second oil tank 2 and between the third oil tank 3 and the fourth oil tank 4, and the communication air pipe 16 is used for enabling the air in the first oil tank 1 and the second oil tank 2 to be mutually communicated and the air in the third oil tank 3 and the fourth oil tank 4 to be mutually communicated.
By means of the design, the air in the oil tank can be communicated with the external atmosphere through the main exhaust pipe 13, the air dispersing head 14, the secondary exhaust pipe 15 and the communication air pipe 16, and accordingly the air pressure in the oil tank is guaranteed to be normal.
The detection assembly comprises liquid level sensors 17 which are respectively and independently arranged between the first oil tank 1 and the second oil tank 2 and on the third oil tank 3 and the fourth oil tank 4.
The output end electrical signal of the liquid level sensor 17 is connected to the main processor, each liquid level sensor 17 respectively reads the residual oil quantity in the corresponding oil tank and transmits the detection electrical signal to the main processor, and the main processor calculates the percentage of the residual oil quantity in the current oil tank.
The formula for calculating the amount of oil in the main processor is prior art and will not be described herein.
In use, the first oil tank group and the second oil tank group are fixedly arranged on two sides of the aircraft main body support through the first oil tank frame 5 and the second oil tank frame 7 respectively, so that the integral installation is facilitated, then a user can conveniently add aircraft fuel into the aircraft fuel tank device through the oil filling ports 12 on the first oil tank 1 and the third oil tank 3, and then the aircraft fuel in the aircraft fuel tank device is supplied to an engine through the oil outlet pipe 10.
At this time, when the fuel is filled or used, the air pressure in the fuel tank device for the aircraft fluctuates, and the air in the fuel tank can be communicated with the external atmosphere through the main exhaust pipe 13, the air dispersing head 14, the secondary exhaust pipe 15 and the communication air pipe 16, so that the air pressure in the fuel tank is ensured to be normal.
When the quantity of the residual oil in the fuel tank device for the airplane needs to be detected, the residual oil quantity in the corresponding fuel tank can be read through each liquid level sensor 17, the detection electric signal is transmitted to the main processor, and the main processor calculates the percentage of the residual oil quantity in the current fuel tank.
For those skilled in the art, based on the teachings of the present invention, changes, modifications, substitutions and variations can be made to the embodiments without departing from the principles and spirit of the invention.
Claims (10)
1. The utility model provides a fuel tank device for aircraft, includes aircraft main part frame, its characterized in that: the axis left and right sides of aircraft main part frame is fixed respectively and is provided with first oil tank group and the second oil tank group that is used for saving the aircraft fuel, first oil tank group and second oil tank group communicate each other, and pass through the surplus oil mass in the detection subassembly real-time detection oil tank respectively.
2. A fuel tank assembly as set forth in claim 1 in which: first oil tank group includes first oil tank (1) and second oil tank (2), and second oil tank (2) set up the below at first oil tank (1), and is an organic whole structure through first oil tank frame (5) fixed connection between first oil tank (1) and second oil tank (2).
3. A fuel tank assembly as set forth in claim 2 in which: a first communicating pipe (6) used for enabling the first oil tank (1) and the second oil tank (2) to be communicated with each other is arranged between the lower end of the first oil tank (1) and the upper end of the second oil tank (2).
4. A fuel tank assembly as set forth in claim 3 in which: the second oil tank group comprises a third oil tank (3) and a fourth oil tank (4), the fourth oil tank (4) is arranged below the third oil tank (3), and the third oil tank (3) and the fourth oil tank (4) are fixedly connected through a second oil tank rack (7) to form an integral structure.
5. An aircraft fuel tank assembly as defined in claim 4, wherein: and a second mutual through pipe (8) used for enabling the third oil tank (3) and the fourth oil tank (4) to be mutually communicated is arranged between the lower end of the third oil tank (3) and the upper end of the fourth oil tank (4).
6. An aircraft fuel tank assembly as defined in claim 5, wherein: and a bottom interconnecting pipe (9) used for communicating the second oil tank (2) and the fourth oil tank (4) with each other is arranged between the lower end of the second oil tank (2) and the lower end of the fourth oil tank (4).
7. An aircraft fuel tank assembly as defined in claim 6, wherein: the lowest liquid level section of the bottom interconnecting pipe (9) is communicated with an oil outlet pipe (10), and the upper end of the first oil tank (1) is fixedly connected with an oil return pipe (11).
8. A fuel tank assembly as set forth in claim 7 in which: be provided with the exhaust pipe between first oil tank group and the second oil tank group, the exhaust pipe includes main exhaust pipe (13), and the upper end intercommunication of main exhaust pipe (13) has gas dispersing head (14), and the other end intercommunication of main exhaust pipe (13) has twice blast pipe (15), and the other end of twice blast pipe (15) communicates with the upper end of first oil tank (1) and third oil tank (3) respectively.
9. A fuel tank assembly as set forth in claim 8 in which: and a communicating air pipe (16) is respectively arranged between the first oil tank (1) and the second oil tank (2) and between the third oil tank (3) and the fourth oil tank (4).
10. A fuel tank assembly as set forth in claim 9 in which: the detection assembly comprises liquid level sensors (17) which are respectively and independently arranged between the first oil tank (1) and the second oil tank (2) and on the third oil tank (3) and the fourth oil tank (4), and the output end of each liquid level sensor (17) is connected to the main processor in an electric signal mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020264212.1U CN211844923U (en) | 2020-03-06 | 2020-03-06 | Fuel tank device for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020264212.1U CN211844923U (en) | 2020-03-06 | 2020-03-06 | Fuel tank device for airplane |
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| Publication Number | Publication Date |
|---|---|
| CN211844923U true CN211844923U (en) | 2020-11-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020264212.1U Active CN211844923U (en) | 2020-03-06 | 2020-03-06 | Fuel tank device for airplane |
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| CN (1) | CN211844923U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148195A (en) * | 2021-04-26 | 2021-07-23 | 浙江万丰飞机制造有限公司 | General aircraft fuel tank of aviation kerosene fixed wing |
-
2020
- 2020-03-06 CN CN202020264212.1U patent/CN211844923U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148195A (en) * | 2021-04-26 | 2021-07-23 | 浙江万丰飞机制造有限公司 | General aircraft fuel tank of aviation kerosene fixed wing |
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