CN216894624U - Novel aviation range extender system - Google Patents
Novel aviation range extender system Download PDFInfo
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- CN216894624U CN216894624U CN202123138766.0U CN202123138766U CN216894624U CN 216894624 U CN216894624 U CN 216894624U CN 202123138766 U CN202123138766 U CN 202123138766U CN 216894624 U CN216894624 U CN 216894624U
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- range extender
- cooling
- power generation
- rectifier
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- 239000004606 Fillers/Extenders Substances 0.000 title claims abstract description 47
- 238000001816 cooling Methods 0.000 claims abstract description 47
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 39
- 238000010248 power generation Methods 0.000 claims abstract description 29
- 238000003860 storage Methods 0.000 claims description 13
- 239000002826 coolant Substances 0.000 claims description 6
- 239000000498 cooling water Substances 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 230000010354 integration Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 abstract description 3
- 230000017525 heat dissipation Effects 0.000 description 15
- 239000000110 cooling liquid Substances 0.000 description 7
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/72—Electric energy management in electromobility
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Abstract
The utility model provides a novel aviation range extender system, which relates to the technical field of unmanned aerial vehicles and comprises the following components: the cooling system comprises an engine system, a power generation system connected with the engine system, a system controller connected with the engine system and the cooling system used for dissipating heat for the engine system and the power generation system, wherein the engine system, the power generation system, the system controller and the cooling system are assembled on a bottom plate in an integrated mode. According to the utility model, the radiator, the water tank, the cooling fan, the water pump, the rectifier, the engine, the generator and the system controller are integrated into a whole, so that the system integration is achieved, the small space size is realized, the purpose of facilitating the carrying and arrangement of the range extender system is improved, and the cooling system has the advantages of simple structure, easiness in assembly, low process requirement and low manufacturing cost.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a novel aviation range extender system.
Background
When the aviation range extender hybrid power system is carried on an unmanned aerial vehicle for use, because an engine of the aviation range extender hybrid power system needs to be cooled by a cooling system, a water cooling system needs to be arranged, and a rectifier of a power generation system of the aviation range extender also needs to be cooled by the cooling system and also needs to be arranged. The cooling system consists of a radiator, an expansion water tank, a water pump, a water pipe and a cooling fan, the design of the cooling system is indispensable in a hybrid power system of the aviation range extender, and the performance of the aviation range extender is influenced by the condition of the design of the cooling system and whether the design is reasonable or not.
The existing aviation range extender system has the defects of multiple sub-parts of the range extender system, complex structure, high installation requirement, complex electronic control, high energy consumption loss, high manufacturing cost and the like.
SUMMERY OF THE UTILITY MODEL
The utility model provides a novel aviation range extender system, which aims to solve the problems that the existing aviation range extender system assembly is scattered, a system controller is distributed on an unmanned aerial vehicle complete machine, wiring harnesses are crossed, signal interference influences control precision, a cooling system occupies the whole unmanned aerial vehicle complete machine frame space, a water path is complex, flow resistance is large, the complete machine heat dissipation is influenced, and the performance of a range extender is unstable.
The utility model provides a novel aviation range extender system, which comprises: the cooling system comprises an engine system, a power generation system connected with the engine system, a system controller connected with the engine system and the cooling system used for dissipating heat for the engine system and the power generation system, wherein the engine system, the power generation system, the system controller and the cooling system are assembled on a bottom plate in an integrated mode.
In one embodiment of the utility model, the engine system comprises an aircraft engine for providing power and a steering engine system for controlling the opening degree of a throttle valve of the aircraft engine, the aircraft engine is connected with the engine system, and the steering engine system is connected with the aircraft engine.
In one embodiment of the utility model, the system controller is connected with the steering engine system, and the system controller and the steering engine system are positioned on two opposite sides of the bottom plate.
In one embodiment of the utility model, the power generation system includes a rectifier connected to the aircraft engine in the engine system and to the generator for converting alternating current to direct current, and the generator and rectifier are located on opposite sides of the bedplate.
In one embodiment of the utility model, the generator and the rectifier are both integrally mounted on the base plate, and the rectifier is located on the same side of the base plate as the system controller.
In one embodiment of the utility model, the cooling system comprises a radiator for radiating heat of the cooling liquid, a water storage tank connected with the radiator and used for storing the cooling liquid, and a water pump connected with the water storage tank and used for providing circulating power for the cooling liquid.
In one embodiment of the utility model, the radiator, the water storage tank and the water pump are all integrally installed on the bottom plate.
In one embodiment of the utility model, the cooling water line in the cooling system is led out from the water pump, passes through the rectifier in the power generation system and the aircraft engine in the engine system in sequence, and is connected to the radiator.
In an embodiment of the present invention, the cooling system further includes a heat dissipation fan, and the heat dissipation fan is integrally installed on the bottom plate and located at one side of the heat sink.
In one embodiment of the utility model, the heat dissipation fan is located between the heat sink and a generator in the power generation system.
The utility model provides a novel aviation range extender system, which integrates and assembles the engine system, the power generation system, the system controller and the cooling system on a bottom plate to realize a highly integrated aviation range extender system, so that the volume of the aviation range extender system assembly is small, the cooling system is integrated with the engine, the arrangement of an unmanned aerial vehicle on the cooling system is reduced, the assembly link of the unmanned aerial vehicle system is reduced, and stable electric power output can be realized.
The utility model provides a novel aviation range extender system, which integrates a radiator, a water tank, a cooling fan, a water pump, a rectifier, an engine, a generator and a system controller into a whole, thereby achieving the purposes of system integration, realizing small space size and improving the range extender system which is convenient for carrying and arranging an unmanned aerial vehicle, so that the cooling system disclosed by the utility model has the advantages of simple structure, easiness in assembly, low process requirement, simplicity in electronic control and reduction in manufacturing cost.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a block diagram illustrating a novel aviation range extender system according to an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a novel aviation range extender system according to an embodiment of the present invention.
Fig. 3 is a schematic structural diagram of another angle of the novel aviation range extender system in an embodiment of the present invention.
Description of reference numerals:
an airborne range extender system 100; an engine system 10; an aircraft engine 101; a steering engine system 102; a power generation system 20; a generator 201; a rectifier 202; a system controller 30; a cooling system 40; a heat sink 401; a water storage tank 402; a water pump 403; a support 4011; a heat dissipation fan 404; a base plate 50.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The utility model is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention.
It should be noted that the drawings provided in the present embodiment are only for illustrating the basic idea of the present invention, and the components related to the present invention are only shown in the drawings rather than drawn according to the number, shape and size of the components in actual implementation, and the type, quantity and proportion of the components in actual implementation may be changed freely, and the layout of the components may be more complicated.
The utility model provides a novel aviation range extender system, which aims to solve the problems that the existing aviation range extender system assembly is scattered, a system controller is distributed on an unmanned aerial vehicle complete machine, wiring harnesses are crossed, signal interference influences control precision, a cooling system occupies the whole unmanned aerial vehicle complete machine frame space, a water path is complex, the flow resistance is large, the heat dissipation of the complete machine is influenced, and the performance of the range extender is unstable, as shown in fig. 1-3, in particular, the aircraft range extender system 100 includes an engine system 10, a power generation system 20, a system controller 30, a cooling system 40 and a base plate 50, the engine system 10, the power generation system 20, the system controller 30 and the cooling system 40 are integrally mounted on the base plate 50, the above components are assembled into a whole through the bottom plate 50, so that the structure is more compact and integrated, and meanwhile, the water path arrangement is shorter and the flow resistance is smaller.
As shown in fig. 1 to 3, in the present embodiment, the engine system 10 includes an aircraft engine 101 and a steering engine system 102, specifically, the aircraft engine 101 is mounted on one side of the base plate 50, the aircraft engine 101 is used for providing power, the steering engine system 102 is connected to the aircraft engine 101, and the steering engine system 102 is used for controlling a throttle opening of the aircraft engine 101, so as to control a rotation speed of the aircraft engine 101.
As shown in fig. 1 to 3, in the present embodiment, the power generation system 20 includes a generator 201 and a rectifier 202, the generator 201 is integrally and fixedly mounted on the base plate 50, and is located on the same side of the base plate 50 as the aircraft engine 101, the aircraft engine 101 is connected to the generator 201, the generator 201 is driven by the aircraft engine 101 to generate power, and the rectifier 202 is also fixedly mounted on the base plate 50 and is located on a side of the base plate 50 opposite to the generator 201, that is, the generator 201 and the rectifier 202 are located on two sides of the base plate 50 opposite to each other, and the rectifier 202 is connected to the generator 201 for converting the alternating current generated by the generator 201 into direct current, specifically, in the present embodiment, the aircraft engine 101 performs combustion work, the electric energy is generated by the rotation of the outer rotor of the generator 201 and the cutting of the magnetic field of the inner stator through the outer rotor of the generator 201, so that the generator 201 outputs alternating current, the output alternating current is rectified into direct current through the rectifier 202, the direct current charges the power battery, the power battery synchronously discharges to supply power to the propeller motor of the unmanned aerial vehicle, and the flight of the unmanned aerial vehicle is ensured.
As shown in fig. 1 to 3, in this embodiment, the system controller 30 is also fixedly mounted on the bottom plate 50 and located on the same side of the bottom plate 50 as the rectifier 202, the system controller 30 is connected to the steering engine system 102 and is configured to control the throttle opening of the aircraft engine 101 through the steering engine system 102, specifically, the system controller 30 controls the throttle of the aircraft engine 101 through the steering engine system 102 according to a load requirement of the unmanned aerial vehicle, adjusts the power of the aircraft engine 101 by adjusting the throttle opening of the aircraft engine 101 so as to adjust the rotation speed and the torque of the aircraft engine 101, and the generator 201 adjusts the output electric power according to the input torque and the rotation speed of the aircraft engine 101.
It should be noted that, the hybrid power system of the aviation range extender needs to ensure stable and reliable power output, and at least performs closed-loop management of the given power and the actual output power, that is, power closed loop, and performs closed-loop management of the required power and the actual power, so as to prevent the battery from being overcharged. In this embodiment, the aviation range extender system 100 needs to have a constant power generation function, a power generation constant voltage control function, and a power generation power following function, specifically, the constant power generation function refers to continuously and stably outputting power at a certain specified power point; the aviation range extender system 100 with the power generation constant voltage control function has a direct-current voltage output management function and prevents overvoltage and undervoltage of a battery and the system; the generated power following function refers to that the oil-electricity hybrid power system should respond to power requirements in time when power changes according to flight control or other instruction input modes.
As shown in fig. 1 to 3, in the present embodiment, the cooling system 40 is also integrally mounted on the base plate 50, and the cooling system 40 is used for dissipating heat from the rectifier 202 and the engine 101 through circulation of a cooling liquid. Specifically, the cooling system 40 includes a radiator 401, a water storage tank 402 and a water pump 403, and the radiator 401, the water storage tank 402 and the water pump 403 are all integrally mounted on the base plate 50, the radiator 401 is mounted on the base plate 50 through a support 4011, the water storage tank 402 is fixedly mounted together with the radiator 401, the radiator 401 dissipates heat of the coolant to enable the coolant to be recycled, the support 4011 and the aircraft engine 101 are located on the same side of the base plate 50, the water pump 403 is fixedly mounted on the base plate 50 and located on the same side of the base plate 50 as the system controller 30, and the water pump is communicated with the water storage tank 402 through a coolant pipeline.
As shown in fig. 1 to 3, in the present embodiment, the cooling water line in the cooling system 40 is led out from the water pump 403, then passes through the rectifier 202 in the power generation system 20 and the aircraft engine 101 in the engine system 10 in sequence, and finally is connected to the radiator 401, so as to form the cooling liquid circulation line, that is, the water pump 403 extracts the cooling liquid from the water storage tank 402, passes through the cooling water line and passes through the rectifier 202 and the aircraft engine 101 in sequence, carries away heat generated by the rectifier 202 and the aircraft engine 101 so as to dissipate heat of the rectifier 202 and the aircraft engine 101, and returns to the radiator 401, and performs heat dissipation and temperature reduction treatment on the cooling liquid that has been increased in temperature by passing through the rectifier 202 and the aircraft engine 101 in the radiator 401, and is stored in the water storage tank 402, so that the cooling system 40 and the aircraft engine 101 are integrated together, the space occupied by the cooling system 40 is reduced, the cooling pipeline is shorter, and the heat dissipation efficiency is higher.
As shown in fig. 1 to fig. 3, in this embodiment, the cooling system 40 further includes a heat dissipation fan 404, the heat dissipation fan 404 is integrally mounted on the bottom plate 50 and is located at one side of the heat sink 401, that is, the heat dissipation fan 404 is used for exchanging air for the heat sink 401, so as to enhance the heat dissipation effect of the heat sink 401, and the heat dissipation fan 404 is located between the heat sink 401 and the generator 201 in the power generation system 20, so that the heat dissipation fan 404 can also provide flowing air for the generator 201 and the aircraft engine 101, thereby further enhancing the heat dissipation effect.
The utility model provides a novel aviation range extender system, which integrates and assembles the engine system, the power generation system, the system controller and the cooling system on a bottom plate to realize a highly integrated aviation range extender system, so that the volume of the aviation range extender system assembly is small, the cooling system is integrated with the engine, the arrangement of an unmanned aerial vehicle on the cooling system is reduced, the assembly link of the unmanned aerial vehicle system is reduced, and stable electric power output can be realized.
The utility model provides a novel aviation range extender system, which integrates a radiator, a water tank, a cooling fan, a water pump, a rectifier, an engine, a generator and a system controller into a whole, thereby achieving the purposes of system integration, realizing small space size and improving the range extender system which is convenient for carrying and arranging an unmanned aerial vehicle, so that the cooling system disclosed by the utility model has the advantages of simple structure, easiness in assembly, low process requirement, simplicity in electronic control and reduction in manufacturing cost.
The above description is only a preferred embodiment of the present application and the explanation of the technical principle used, and it should be understood by those skilled in the art that the scope of the present application is not limited to the technical solution of the specific combination of the above technical features, and also covers other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept, for example, the technical solutions formed by mutually replacing the above technical features (but not limited to) having similar functions disclosed in the present application.
Other technical features than those described in the specification are known to those skilled in the art, and are not described herein in detail in order to highlight the innovative features of the present invention.
Claims (10)
1. A novel aviation range extender system, comprising: the cooling system comprises an engine system, a power generation system connected with the engine system, a system controller connected with the engine system and a cooling system used for dissipating heat for the engine system and the power generation system, wherein the engine system, the power generation system, the system controller and the cooling system are assembled on a bottom plate in an integrated mode.
2. The novel aviation range extender system as claimed in claim 1, wherein said engine system comprises an aircraft engine for providing power and a steering engine system for controlling the opening of a throttle valve of said aircraft engine, said aircraft engine is connected to said engine system, and said steering engine system is connected to said aircraft engine.
3. The novel aviation range extender system of claim 2, wherein said system controller is connected to said steering engine system and is located on opposite sides of said base plate.
4. The novel aerospace range extender system of claim 1, wherein the power generation system comprises a generator connected to an aero-engine in the engine system and a rectifier connected to the generator for converting alternating current to direct current, and wherein the generator and the rectifier are located on opposite sides of the base plate.
5. The novel aerospace range extender system of claim 4, wherein the generator and the rectifier are both integrally mounted on the base plate, and the rectifier is located on the same side of the base plate as the system controller.
6. The novel aerospace range extender system of claim 1, wherein the cooling system comprises a radiator for dissipating heat from the coolant, a water storage tank connected to the radiator for storing the coolant, and a water pump connected to the water storage tank for providing circulating power to the coolant.
7. The novel aerospace range extender system of claim 6, wherein the heat sink, the water storage tank and the water pump are all integrally mounted on the base plate.
8. The novel aerospace range extender system of claim 6, wherein the cooling water line in the cooling system leads from the water pump sequentially through a rectifier in the power generation system and an aero-engine in the engine system and connects to the radiator.
9. The novel aerospace range extender system of claim 6, wherein the cooling system further comprises a heat sink fan integrally mounted on the base plate and located to one side of the heat sink.
10. The novel aerospace range extender system of claim 9, wherein the heat sink fan is located between the heat sink and a generator in the power generation system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123138766.0U CN216894624U (en) | 2021-12-14 | 2021-12-14 | Novel aviation range extender system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123138766.0U CN216894624U (en) | 2021-12-14 | 2021-12-14 | Novel aviation range extender system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216894624U true CN216894624U (en) | 2022-07-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123138766.0U Active CN216894624U (en) | 2021-12-14 | 2021-12-14 | Novel aviation range extender system |
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|---|---|
| CN (1) | CN216894624U (en) |
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2021
- 2021-12-14 CN CN202123138766.0U patent/CN216894624U/en active Active
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