CN218276089U - Power supply equipment grid-connected system for aircraft - Google Patents
Power supply equipment grid-connected system for aircraft Download PDFInfo
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- CN218276089U CN218276089U CN202221862971.3U CN202221862971U CN218276089U CN 218276089 U CN218276089 U CN 218276089U CN 202221862971 U CN202221862971 U CN 202221862971U CN 218276089 U CN218276089 U CN 218276089U
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Abstract
The application discloses a power supply equipment grid-connected system for an aircraft, which comprises power supply equipment, wherein the power supply equipment comprises a fuel engine and a generator, the power supply equipment is provided with a main controller, and the main controller controls the opening of an accelerator of the fuel engine; the grid-connected regulation controller is connected with a main controller of the power supply equipment through a data transmission line; the grid-connected regulation controller is respectively connected with each power supply device to balance the output power of each power supply device. The utility model discloses a power supply unit is incorporated into the power networks system for aircraft uses two or more than two power supply unit parallel connection, can be convenient carry out the power dilatation; the grid-connected regulation controller is used for respectively regulating and controlling each power supply device, balancing the output power of each power supply device and ensuring the normal operation of the system; meanwhile, due to the fact that a plurality of power supply devices exist, the power supply devices are mutually backed up, and the risk resistance of the aircraft is improved.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to a power supply equipment grid-connected system for an aircraft.
Background
Direct current generators are widely applied to direct current electrical equipment or systems, and a demand for power capacity expansion exists in system application. For example, the original demand 7 KW's of an unmanned aerial vehicle system of a load 20KG power, use the DC generator of 1 7KW power, the demand increases the load to 40KG now, system power demand 14KW, traditional method is exactly to change this DC generator into the DC generator of another 1 KW power, this DC generator of redesign usually needs, and drive the engine of this generator, will lead to the system development degree of difficulty like this, development time and development cost increase sharply.
SUMMERY OF THE UTILITY MODEL
In order to solve one of the technical problems mentioned in the background art, the application provides a power supply equipment grid-connected system for an aircraft, wherein a plurality of power supply equipment can be connected in parallel to improve the output power, and the output power of each power supply equipment is balanced through a grid-connected regulation controller to ensure the normal operation of the system.
According to the utility model discloses power supply unit system that is incorporated into power networks for aircraft of first aspect embodiment, include:
the power supply equipment comprises a fuel engine and a generator driven by the fuel engine, the fuel engine comprises an accelerator, the output end of the generator is provided with a rectifying loop, the power supply equipment is provided with a main controller, the main controller collects the working output states of the fuel engine, the generator and the rectifying loop, and the main controller controls the opening of the accelerator;
the grid-connected regulation controller is connected with the main controller of the power supply equipment through a data transmission line;
the fuel engine system comprises a power supply device, a grid-connected regulation controller, a plurality of fuel engines and a plurality of fuel engines, wherein the power supply device is provided with more than two power supply devices, the power supply devices are connected in parallel, the grid-connected regulation controller is respectively connected with the power supply devices, and the grid-connected regulation controller is used for respectively regulating and controlling the accelerator opening of the fuel engines and balancing the output power of the power supply devices.
According to the utility model discloses power supply unit system of being incorporated into power networks for aircraft of the embodiment of the first aspect has following beneficial effect at least: the utility model discloses a power supply unit is incorporated into the power networks system for aircraft uses two or more than two power supply unit parallel connection, can be convenient carry out the power dilatation; the grid-connected regulation controller is used for respectively regulating and controlling each power supply device, balancing the output power of each power supply device and ensuring the normal operation of the system; meanwhile, the power supply equipment grid-connected system for the aircraft has the advantages that the plurality of power supply equipment are used as backups for each other, when part of the power supply equipment fails to work or the performance of the power supply equipment is reduced, the output of other power supply equipment can be increased through the grid-connected regulation controller to supplement power loss, the aircraft can stably fly to land in a short time, and the risk resistance of the aircraft is improved.
According to the utility model discloses the first aspect power supply unit system of being incorporated into power networks for aircraft, it is a plurality of the specification parameter of power supply unit's the same accessory is unanimous, and power supply unit adopts the same accessory, can guarantee power supply unit's uniformity, is convenient for be incorporated into power networks the regulation and control, each power supply unit's of better balance output.
According to the utility model discloses first aspect power supply unit system that is incorporated into power networks for aircraft, power supply unit's output has charge-discharge battery in parallel. When the output power of the generator is insufficient, the charging and discharging battery discharges to improve the output power; when the output power of the generator is surplus, the charging and discharging battery is charged.
According to the utility model discloses an aircraft is with power supply unit system of being incorporated into power networks, be provided with the generator drive circuit that is used for the auxiliary starting generator in the power supply unit, generator drive circuit electricity respectively connects charge-discharge battery with the generator. The generator driving loop is used for driving the generator rotor to rotate, so that the engine is driven to act, the power supply equipment is started, after the power supply equipment is started, direct current is output through the rectifying loop, and the generator driving loop is isolated outside the output loop.
According to the utility model discloses an aircraft power supply unit system of being incorporated into power networks, the regulation and control controller that is incorporated into power networks including:
the data collection module is used for collecting the current, voltage and power data output by the generator and fed back by each power supply device;
the data comparison module is connected with the data collection module and is used for comparing the output power of each power supply device;
and the regulation and control instruction output module is connected with the data comparison module and outputs regulation and control instructions to the main controller of each power supply device according to the comparison result of the output power, and the main controller controls the opening degree of the accelerator of each fuel engine to balance the output power of each power supply device.
According to the utility model discloses first aspect power supply unit system of being incorporated into power networks for aircraft, the regulation and control controller that is incorporated into power networks is provided with the communication interface that is used for connecting external equipment, through communication interface connection external equipment, the remote monitoring of being convenient for.
Additional features and advantages of the application will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by the practice of the application. The objectives and other advantages of the application may be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
The accompanying drawings are included to provide a further understanding of the claimed subject matter and are incorporated in and constitute a part of this specification, illustrate embodiments of the subject matter and together with the description serve to explain the principles of the subject matter and not to limit the subject matter.
Fig. 1 is a schematic diagram of a grid-connected system of power supply equipment for an aircraft according to the present embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more clearly understood, the present application is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the term "connected" is to be understood in a broad sense, e.g. it may be a fixed connection or a movable connection, a detachable connection or a non-detachable connection, or an integral connection; may be mechanically connected, may be electrically connected or may be in communication with each other; they may be directly connected or indirectly connected through intervening agents or structures, or may be connected through one or more other elements, indirectly connected or interacting with each other.
In the description of the present application, it is to be noted that several means are one or more, plural (or plural) means are two or more, more than, less than, more than, etc. are understood as excluding the present number, and more than, less than, etc. are understood as including the present number. If the description of "first", "second", etc. is used for the purpose of distinguishing technical features, it is not intended to indicate or imply relative importance or to implicitly indicate the number of indicated technical features or to implicitly indicate the precedence of the indicated technical features.
The embodiments of the present application will be further explained with reference to the drawings.
Referring to fig. 1, the power supply equipment grid-connected system for an aircraft according to the present embodiment includes a plurality of power supply equipment A1, A2, and A3, where each of the power supply equipment A1, A2, and A3 includes a fuel engine 100, a generator 200, and a rectifier circuit 300, which are sequentially connected. The generator 200 driven by the fuel engine 100 generates ac power, and the ac power is converted into dc power through the rectifier circuit 300. The power supply devices A1, A2, A3 are further provided with a main controller 400, the main controller 400 collects various state parameters of the fuel engine 100, the generator 200 and the rectifier circuit 300, such as the rotating speed and the temperature of the fuel engine 100, the rotating speed and the output current of the generator 200, the output voltage and the output current of the rectifier circuit 300, and the like, and the main controller 400 controls the accelerator opening of the fuel engine 100.
It is easy to think that the specification parameters of the same accessories in the plurality of power supply devices A1, A2, A3 are consistent, and the power supply devices A1, A2, A3 adopt the same accessories, so that the consistency of the power supply devices A1, A2, A3 can be ensured, grid-connected regulation and control are facilitated, and the output power of each power supply device A1, A2, A3 is better balanced.
Further, the output end of each of the power supply devices A1, A2, and A3 is connected in parallel with a charging/discharging battery B. When the output power of the generator 200 of the power supply equipment is insufficient, the charging and discharging battery B discharges, so that the output power is improved; when the output power of the generator 200 is surplus, the charge/discharge battery B is charged. Through the compensation of the charge-discharge battery B, the output power can be more stable, and the control of the aircraft is facilitated.
Further, the power supply devices A1, A2, and A3 are each provided therein with a generator drive circuit for assisting in starting the generator 200, and the generator drive circuits are electrically connected to the charging/discharging battery B and the generator 200, respectively. The generator driving loop is used for driving the generator 200 rotor to rotate, so as to drive the engine to act and start the power supply equipment; after the power supply equipment is started, direct current is output through the rectifying loop 300, and the generator driving loop is isolated outside the output loop.
As shown in fig. 1, the outputs of a plurality of power supply devices A1, A2, and A3 are connected in parallel to form a dc power grid, and a grid-connected regulation controller 500 is connected to the main controller 400 of each power supply device A1, A2, and A3 through data transmission lines. Since the performances of the power supply apparatuses A1, A2, and A3 are not identical and are not synchronized in time, the output powers of the power supply apparatuses A1, A2, and A3 are unbalanced, and even some power supply apparatuses are operated fully and some power supply apparatuses are not operated. Therefore, a grid-connected regulation controller 500 is required for coordination.
Specifically, the main controller 400 of the power supply devices A1, A2, and A3 uploads real-time operating condition parameters to the grid-connected regulation controller 500 for analysis and calculation, the grid-connected regulation controller 500 integrally plans the operating conditions of the power supply devices A1, A2, and A3, makes a decision, and simultaneously distributes instructions to the power supply devices A1, A2, and A3 to control the power output of the power supply devices A1, A2, and A3, and the main controller 400 of the power supply devices A1, A2, and A3 adjusts the power output of the power supply devices by adjusting the throttle opening of the fuel engine 100, and stabilizes the power output within a range required by the instructions. The load of the direct current power grid is changed continuously, and the power output of each power supply device A1, A2 and A3 is also adjusted and changed continuously, which is a real-time continuous regulation and control process.
In order to accomplish the above regulation, the grid-connected regulation controller 500 includes a data collection module, a data comparison module, and a regulation instruction output module. The data collection module is used for collecting various state parameters of the fuel engine 100, the generator 200 and the rectification loop 300 fed back by each power supply device A1, A2 and A3, wherein the state parameters at least comprise current, voltage and power data output by each power supply device A1, A2 and A3; the data comparison module is connected with the data collection module and is used for comparing the output power of each power supply device A1, A2 and A3; the regulation and control instruction output module is connected with the data comparison module, and outputs regulation and control instructions to the main controller 400 of each power supply device A1, A2 and A3 according to the comparison result of the output power, and the main controller 400 controls the accelerator opening of each fuel engine 100 to balance the output power of each power supply device A1, A2 and A3.
Further, the grid-connected regulation controller 500 is provided with a communication interface C for connecting external equipment, and the communication interface C is connected with the external equipment, so that remote monitoring is facilitated.
The utility model discloses a power supply unit grid-connected system for aircraft uses more than two power supply units to connect in parallel, can be convenient carry out power dilatation; the modular power supply equipment can be manufactured in a standardized and large-scale manner, so that the manufacturing cost is greatly reduced; the grid-connected regulation controller 500 is used for respectively regulating and controlling each power supply device, balancing the output power of each power supply device and ensuring the normal operation of the system; meanwhile, the power supply equipment grid-connected system for the aircraft has the advantages that the plurality of power supply equipment are mutually backup, when part of the power supply equipment fails or performance is reduced due to faults, the output of other power supply equipment can be increased through the grid-connected regulation controller 500 to supplement power loss, the aircraft can keep stable flight for landing in a short time, and the risk resistance of the aircraft is improved.
Further, what has been discussed above is the case that the performances of the power supply devices A1, A2, and A3 are basically the same, that is, the same module extension structure, and actually, the power supply devices with different powers may also be extended in a matching manner, and of course, the operating voltages must be the same, and the communication protocols of the main controller 400 must be the same. When power supply equipment with different powers is expanded, the power cannot be distributed evenly, and the maximum power capacity of each power supply equipment needs to be considered for reasonable allocation.
While the preferred embodiments of the present invention have been described, the present invention is not limited to the above embodiments, and those skilled in the art can make various equivalent modifications or substitutions without departing from the spirit of the present invention, and such equivalent modifications or substitutions are included in the scope of the present invention defined by the claims.
Claims (6)
1. A power supply equipment grid-connected system for an aircraft is characterized by comprising:
the power supply equipment comprises a fuel engine and a generator driven by the fuel engine, the fuel engine comprises an accelerator, the output end of the generator is provided with a rectifying circuit, the power supply equipment is provided with a main controller, the main controller collects the working output states of the fuel engine, the generator and the rectifying circuit, and the main controller controls the opening degree of the accelerator;
the grid-connected regulation controller is connected with the main controller of the power supply equipment through a data transmission line;
the fuel engine system comprises a power supply device, a grid-connected regulation controller, a plurality of fuel engines and a plurality of fuel engines, wherein the power supply device is provided with more than two power supply devices, the power supply devices are connected in parallel, the grid-connected regulation controller is respectively connected with the power supply devices, and the grid-connected regulation controller is used for respectively regulating and controlling the accelerator opening of the fuel engines and balancing the output power of the power supply devices.
2. The grid-connected system for power supply equipment for aircraft according to claim 1, wherein specifications of identical components of the plurality of power supply equipment are identical.
3. The aircraft power supply equipment grid-connection system according to claim 1, wherein a charge-discharge battery is connected in parallel to an output end of the power supply equipment.
4. The aircraft power supply equipment grid-connection system according to claim 3, wherein a generator driving circuit for assisting starting of a generator is provided in the power supply equipment, and the generator driving circuit is electrically connected to the charge-discharge battery and the generator respectively.
5. The power supply equipment grid-connected system for the aircraft according to any one of claims 1 to 4, wherein the grid-connected regulation and control controller comprises:
the data collection module is used for collecting the current, voltage and power data output by the generator and fed back by each power supply device;
the data comparison module is connected with the data collection module and is used for comparing the output power of each power supply device;
and the regulation and control instruction output module is connected with the data comparison module, and outputs regulation and control instructions to the main controller of each power supply device according to the comparison result of the output power, and the main controller controls the accelerator opening of each fuel engine to balance the output power of each power supply device.
6. The aircraft power supply equipment grid-connection system as claimed in claim 5, wherein the grid-connection regulation and control controller is provided with a communication interface for connecting external equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221862971.3U CN218276089U (en) | 2022-07-19 | 2022-07-19 | Power supply equipment grid-connected system for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221862971.3U CN218276089U (en) | 2022-07-19 | 2022-07-19 | Power supply equipment grid-connected system for aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN218276089U true CN218276089U (en) | 2023-01-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221862971.3U Active CN218276089U (en) | 2022-07-19 | 2022-07-19 | Power supply equipment grid-connected system for aircraft |
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| CN (1) | CN218276089U (en) |
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- 2022-07-19 CN CN202221862971.3U patent/CN218276089U/en active Active
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