CN214397266U - Power system and unmanned aerial vehicle - Google Patents
Power system and unmanned aerial vehicle Download PDFInfo
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- CN214397266U CN214397266U CN202022158933.7U CN202022158933U CN214397266U CN 214397266 U CN214397266 U CN 214397266U CN 202022158933 U CN202022158933 U CN 202022158933U CN 214397266 U CN214397266 U CN 214397266U
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Abstract
The utility model discloses a driving system and unmanned aerial vehicle relates to machining technical field. One embodiment of the power system comprises: an engine; a first pump body and a second pump body; a first fuel tank for storing fuel, the first fuel tank being provided on an airfoil; a second fuel tank for supplying fuel to the engine, the first fuel tank being in communication with the second fuel tank through the first pump, the second fuel tank being in communication with the engine through the second pump. This embodiment can set up a plurality of fuel tanks on the wing, can promote unmanned aerial vehicle fuel loading and high altitude flight ability.
Description
Technical Field
The utility model relates to a machining technology field especially relates to a driving system and unmanned aerial vehicle.
Background
In the prior art, the existing power system mainly comprises a simple fuel system, wherein the simple fuel system mainly comprises a single fuel pump, a fuel filter and the like, and the existing power system does not have a wing fuel tank design and a high-altitude pressurization scheme, so that the requirements for increasing high-altitude performance and long-time endurance of the unmanned aerial vehicle cannot be met.
SUMMERY OF THE UTILITY MODEL
In view of this, the embodiment of the utility model provides a driving system and unmanned aerial vehicle can solve current driving system design and do not have the problem that the design of wing oil tank can't satisfy high altitude performance demand and long-time duration demand.
To achieve the above object, according to one aspect of the embodiments of the present invention, a power system is provided.
The utility model discloses driving system includes:
an engine;
a first pump body and a second pump body;
a first fuel tank for storing fuel, the first fuel tank being provided on an airfoil;
a second fuel tank for supplying fuel to the engine, the first fuel tank being in communication with the second fuel tank through the first pump, the second fuel tank being in communication with the engine through the second pump.
Optionally, the number of the first fuel tanks is at least two, and the power system further comprises: the two ends of the first pipeline and the second pipeline are respectively communicated with first fuel tanks oppositely arranged on different wings, and the second pipeline is also communicated with the second fuel tank.
Optionally, the power system further comprises:
a controller connected to the first pump body and the second pump body;
and any one or more of a fuel quantity sensor, a temperature sensor and a pressure sensor, wherein the controller is respectively connected with any one or more of the fuel quantity sensor, the temperature sensor and the pressure sensor, and the fuel quantity sensor is used for detecting the residual capacity of the fuel in the first fuel tank and/or the second fuel tank; the temperature sensor is used for detecting the temperature in the first fuel tank and/or the second fuel tank; the pressure sensor is configured to detect a pressure within the first and/or second fuel tanks.
Optionally, the power system further comprises:
a boost vent valve having both ends in communication with the first fuel tank and the engine, respectively.
Optionally, the power system further comprises:
a pressure annunciator disposed between the first pump body and the second fuel tank, and/or between the second pump body and the engine.
Optionally, the power system further comprises:
a check valve having an input in communication with the first fuel tank and an output in communication with the second fuel tank.
Optionally, the power system further comprises:
and the shut-off valve is respectively communicated with the engine and the second fuel tank.
Optionally, the power system further comprises:
a relief valve and a vacuum protection valve, both disposed on the first fuel tank.
Optionally, the power system further comprises:
at least one filter element disposed between the second fuel tank and the second pump body and/or between the second pump body and the engine.
In order to achieve the above object, according to the utility model discloses an aspect provides an unmanned aerial vehicle.
The utility model discloses unmanned aerial vehicle includes: a power system as described above.
An embodiment in the above-mentioned utility model has following advantage or beneficial effect:
the embodiment of the utility model provides an in, this driving system can set up a plurality of fuel tanks on the wing, can promote unmanned aerial vehicle fuel loading and high altitude flight ability.
Further effects of the above-mentioned non-conventional alternatives will be described below in connection with the embodiments.
Drawings
The accompanying drawings are included to provide a better understanding of the present invention and are not intended to constitute an undue limitation on the invention. Wherein:
fig. 1 is a schematic structural view of a power system according to a first embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a powertrain according to a second embodiment of the present invention;
fig. 3 is a schematic illustration of an installation of a power system according to a second embodiment of the present invention.
Detailed Description
Exemplary embodiments of the invention are described below with reference to the accompanying drawings, in which various details of embodiments of the invention are included to assist understanding, and which are to be considered exemplary only. Accordingly, those of ordinary skill in the art will recognize that various changes and modifications of the embodiments described herein can be made without departing from the scope and spirit of the invention. Also, descriptions of well-known functions and constructions are omitted in the following description for clarity and conciseness.
The problem that can't satisfy high altitude performance demand and long-time continuation of the journey demand in order to solve current driving system design does not have the wing oil tank design, the embodiment of the utility model provides a driving system, this driving system's application main part can be power equipment such as unmanned aerial vehicle or aircraft.
Fig. 1 to 3 are schematic structural diagrams of a power system according to an embodiment of the present invention. As shown in fig. 1 to 3, the power system may include: an engine 1, a first pump body 2, a second pump body 3, a first fuel tank 4 and a second fuel tank 5. Wherein, the pump body includes at least: a first pump body 2 and a second pump body 3; the first tank 4 communicates with the second tank 5 through the first pump 2, and the second tank 5 communicates with the engine 1 through the second pump 3.
Wherein the engine 1 is used for providing power for an unmanned plane or an airplane, the first pump body 2 is used for providing pressure so as to convey fuel in the first fuel tank 4 to the second fuel tank 5, and the second pump body 3 is used for providing pressure for a centrifugal oil nozzle of the engine 1. The first fuel tank 4 is used for storing fuel, which may be oil (e.g., aviation fuel oil) and/or natural gas, etc. Wherein the fuel is preferably aviation fuel oil, and the fuel is aviation fuel oil as an example. The first fuel tank 4 is arranged on a wing 21, see fig. 3. The second tank 5 is intended to collect the fuel of the first tank 4, and in order to prevent the second pump 3 from sucking air, it is necessary to ensure a substantially full state inside the second tank 5. The first fuel tank 4 is provided at the top with an inlet 19, through which inlet 19 fuel can be injected into the first fuel tank 4. The bottom of the first fuel tank 4 is provided with a drain 20, through which drain 20 the oil in the first and second fuel tanks 4, 5 is emptied.
With continued reference to fig. 2 to 3, in order to ensure that the wings 21 on both sides of the machine body are stressed equally, the number of the first fuel tanks 4 is at least two, and the wings 21 on both sides of the machine body are respectively provided with the same number of the first fuel tanks 4. Meanwhile, the power system further comprises: a first pipeline 6 (or referred to as a breather pipe) and a second pipeline 7, both ends of the first pipeline 6 and the second pipeline 7 are respectively communicated with the first fuel tanks 4 oppositely arranged on different wings 21, the first pipeline 6 is used for enabling the upper parts of the first fuel tanks 4 on both sides of the first pipeline 6 to be in air communication to balance the air pressure on both sides of the first pipeline 6, and it can be understood that the air pressure of the first fuel tanks 4 oppositely arranged on different wings 21 can be balanced through the first pipeline 6. The second line 7 is used to ensure the balance of the fuel remaining in the first fuel tank 4 on both sides of the second line 7. The second pipeline 7 may be a pipe with a diameter not exceeding 20mm, the second pipeline 7 is connected to the bottom of the first fuel tank 4 at two sides of the second pipeline 7, and the top of the second fuel tank 5 is communicated with the second pipeline 7, and is used as a vent pipe of the second fuel tank 5 in an initial refueling state.
The embodiment of the utility model provides an in, this driving system can set up a plurality of fuel tanks on wing 21, can promote unmanned aerial vehicle fuel loading and high altitude flight ability.
With continued reference to fig. 2-3, to detect any one or more of remaining fuel, temperature, and pressure within the first fuel tank 4, the power system further includes: a controller (not shown in the figures) connected to the first pump body 2 and to the second pump body 3, and any one or more of a fuel quantity sensor 8, a temperature sensor 9 and a pressure sensor 10, which can be used to control the state parameters of the first pump body 2 and of the second pump body 3; in addition, the controller is connected to any one or more of the oil amount sensor 8, the temperature sensor 9, and the pressure sensor 10. Wherein the fuel quantity sensor 8 is used for detecting the fuel remaining in the first fuel tank 4; the temperature sensor 9 is used for detecting the temperature in the first fuel tank 4; the pressure sensor 10 is used to detect the pressure in the first fuel tank 4.
Likewise, any one or more of the remaining fuel in the second fuel tank 5, temperature and pressure may also be detected. For this purpose, one or more of an oil quantity sensor, a temperature sensor and a pressure sensor may also be provided on the second fuel tank 5. At this time, the oil amount sensor 8 is configured to detect the remaining capacity of the fuel in the second fuel tank 5, the temperature sensor 9 is configured to detect the temperature in the second fuel tank 5, and the pressure sensor 10 is configured to detect the pressure in the second fuel tank 5.
It will be understood that the controller functions to monitor the oil sensor 8, the temperature sensor 9 and/or the pressure sensor 10, and also to control the first pump body 2, the second pump body 3 and the various valve bodies. At the same time, the temperature, the pressure and the residual capacity in the first fuel tank 4 and/or the second fuel tank 5 can be jointly monitored by the fuel quantity sensor 8, the temperature sensor 9 and/or the pressure sensor 10. When the fuel in the first fuel tank 4 is oil, the temperature T and the pressure P in the first fuel tank 4 may reflect the fuel environment. The residual capacity of the first fuel tank 4 on different wings 21 can be monitored by the fuel quantity sensor 8 in the first fuel tank 4 respectively, so as to determine whether the residual capacity of the fuel in the first fuel tank 4 on different wings 21 is balanced and prevent the lateral imbalance. The oil quantity sensor 8 in the second fuel tank 5 is used for monitoring whether the second fuel tank 5 is in a full state or not, and the oil transportation process is prevented.
It should be noted that fig. 2 to 3 show a case where the oil amount sensor 8, the temperature sensor 9, and the pressure sensor 10 are provided on the first fuel tank 4, and the embodiment of the present invention is not limited to the case shown in fig. 2 to 3.
With continued reference to fig. 2-3, to achieve pressurization of the first fuel tank 4 when the pressure within the first fuel tank 4 is below a pressure threshold, the power system further comprises: and a boost vent valve 11, both ends of the boost vent valve 11 are respectively communicated with the first fuel tank 4 and the engine 1, and when the pressure in the first fuel tank 4 is lower than a pressure threshold value, the boost vent valve 11 is opened to boost the first fuel tank 4.
With continued reference to fig. 2 to 3, in order to generate an alarm in the event of an anomaly in the pressure inside the first and second cylinders 2, 3, the power system further comprises: a pressure annunciator 12, said pressure annunciator 12 being disposed between said first pump body 2 and said second fuel tank 5, and/or between said second pump body 3 and said engine 1. It is understood that the pressure signaller 12 can determine whether the first pump body 2 and/or the second pump body 3 are functioning properly. In addition, the pressure annunciator 12 can be connected to the controller, so that the controller can adjust the operating parameters of the first pump body 2 and/or the second pump body 3 in time.
With continued reference to fig. 2-3, to prevent fuel in the second fuel tank 5 from flowing back into the first fuel tank 4, the power system further includes: a check valve 13, an input end of the check valve 13 being communicated with the first fuel tank 4, and an output end of the check valve 13 being communicated with the second fuel tank 5. It will be understood that the non-return valve 13 prevents the fuel from returning in a reverse direction to the first tank 4 under the action of the first pump body 2.
With continued reference to fig. 2-3, to ensure that the pressure within the first fuel tank 4 is within a predetermined range, the power system further includes: a relief valve 15 and a vacuum protection valve 16, both the relief valve 15 and the vacuum protection valve 16 being provided on the first fuel tank 4. It will be appreciated that it is possible to ensure, by means of the safety valve 15, that the pressure in the first fuel tank 4 does not exceed a first threshold value, which may be 30 kpa. At the same time, the vacuum protection valve 16 ensures that the pressure in the first fuel tank 4 is not lower than the ambient pressure, i.e. 20 kpa.
With continued reference to fig. 2-3, in order to shut off the fuel circuit when the engine 1 is stopped, the power system is further provided with a shut-off valve 14, which shut-off valve 14 is in communication with the engine 1 and the second fuel tank 5, respectively. The shut-off valve 14 is located between the first pump body 2 and the engine 1. The shut-off valve 14 can be used when the engine 1 is stopped.
With continued reference to fig. 2-3, to filter contaminants from the fuel, the power system further includes: at least one filter cartridge arranged between the second fuel tank 5 and the second pump body 3 and/or between the second pump body 3 and the engine 1. Wherein at least one filter element comprises: first filter core 17 and second filter core 18, the filter screen size of first filter core 17 is greater than the filter screen size of second filter core 18, first filter core 17 respectively with second fuel tank 5 with the second pump body 3 intercommunication, and be located between the two. The second filter cartridge 18 communicates with the second pump body 3 and the engine 1, respectively, and is located between the shut-off valve 14 and the engine 1.
The embodiment of the utility model provides an in, this driving system can set up a plurality of fuel tanks on wing 21, can also realize the pressure boost control of engine 1, can promote unmanned aerial vehicle fuel loading and high altitude flight ability.
The above detailed description does not limit the scope of the present invention. Those skilled in the art will appreciate that various modifications, combinations, sub-combinations, and substitutions can occur, depending on design requirements and other factors. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A power system, comprising:
an engine (1);
a first pump body (2) and a second pump body (3);
a first fuel tank (4) for storing fuel, the first fuel tank (4) being arranged on a wing (21);
-a second tank (5) for supplying fuel to the engine (1), the first tank (4) being in communication with the second tank (5) through the first pump body (2), the second tank (5) being in communication with the engine (1) through the second pump body (3).
2. The power system according to claim 1, wherein the number of the first fuel tanks (4) is at least two, the power system further comprising: the aircraft comprises a first pipeline (6) and a second pipeline (7), wherein two ends of the first pipeline (6) and two ends of the second pipeline (7) are respectively communicated with first fuel tanks (4) which are oppositely arranged on different wings (21), and the second pipeline (7) is also communicated with a second fuel tank (5).
3. The power system of claim 1, further comprising:
a controller connected to the first pump body (2) and the second pump body (3);
and any one or more of a fuel quantity sensor (8), a temperature sensor (9) and a pressure sensor (10), the controller being connected to any one or more of the fuel quantity sensor (8), the temperature sensor (9) and the pressure sensor (10), respectively, the fuel quantity sensor (8) being configured to detect a remaining capacity of fuel within the first fuel tank (4) and/or the second fuel tank (5); the temperature sensor (9) is used for detecting the temperature in the first fuel tank (4) and/or the second fuel tank (5); the pressure sensor (10) is used for detecting the pressure in the first fuel tank (4) and/or the second fuel tank (5).
4. The power system of claim 1 or 3, further comprising:
a boost vent valve (11), both ends of the boost vent valve (11) being in communication with the first fuel tank (4) and the engine (1), respectively.
5. The power system of claim 1, further comprising:
a pressure annunciator (12), the pressure annunciator (12) being disposed between the first pump body (2) and the second fuel tank (5), and/or between the second pump body (3) and the engine (1).
6. The power system of claim 1, further comprising:
a check valve (13), an input end of the check valve (13) is communicated with the first fuel tank (4), and an output end of the check valve (13) is communicated with the second fuel tank (5).
7. The power system of claim 1, further comprising:
a shut-off valve (14), the shut-off valve (14) respectively with engine (1) with second fuel tank (5) intercommunication.
8. The power system of claim 1, further comprising:
a safety valve (15) and a vacuum protection valve (16), both the safety valve (15) and the vacuum protection valve (16) being provided on the first fuel tank (4).
9. The power system of claim 1, further comprising:
at least one filter cartridge arranged between the second fuel tank (5) and the second pump body (3) and/or between the second pump body (3) and the engine (1).
10. An unmanned aerial vehicle, comprising: a power system according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022158933.7U CN214397266U (en) | 2020-09-27 | 2020-09-27 | Power system and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022158933.7U CN214397266U (en) | 2020-09-27 | 2020-09-27 | Power system and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214397266U true CN214397266U (en) | 2021-10-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202022158933.7U Active CN214397266U (en) | 2020-09-27 | 2020-09-27 | Power system and unmanned aerial vehicle |
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|---|---|
| CN (1) | CN214397266U (en) |
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- 2020-09-27 CN CN202022158933.7U patent/CN214397266U/en active Active
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