CN113708679B - Cable time-sharing multiplexing circuit and method for aircraft starting power generation system - Google Patents
Cable time-sharing multiplexing circuit and method for aircraft starting power generation system Download PDFInfo
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- 238000010248 power generation Methods 0.000 title claims abstract description 89
- 238000000034 method Methods 0.000 title claims abstract description 26
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- 230000005284 excitation Effects 0.000 claims abstract description 21
- 239000007858 starting material Substances 0.000 claims description 15
- 230000006870 function Effects 0.000 claims description 13
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- 238000010586 diagram Methods 0.000 description 10
- 238000004891 communication Methods 0.000 description 6
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
- H02P9/14—Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field
- H02P9/26—Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices
- H02P9/30—Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices using semiconductor devices
- H02P9/305—Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices using semiconductor devices controlling voltage
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
- H02P9/02—Details of the control
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P2101/00—Special adaptation of control arrangements for generators
- H02P2101/30—Special adaptation of control arrangements for generators for aircraft
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Abstract
The invention provides a cable time-sharing multiplexing circuit for an aircraft starting power generation system, wherein the aircraft starting power generation system comprises a starting power generator control unit SGCU, an auxiliary starting power generator ASG and a distribution board box RDP, and the time-sharing multiplexing circuit comprises: a first set of cables connecting the SGCUs with the RDPs; a second set of cables connecting the RDP with the ASG; wherein during the start phase, the SGCU excitation wire includes a first set of cables from the SGCU to the RDP and a second set of cables from the RDP to the ASG; wherein during the power generation phase, the generator output feeder comprises a second set of cables of ASG to RDP and the voltage detection line comprises a first set of cables of SGCU to RDP. In addition, the invention also provides a cable time-sharing multiplexing method for the aircraft starting power generation system. According to the invention, the number and the length of the aircraft starting power generation system cables can be remarkably reduced, so that the total weight of the starting power generation system cables is reduced.
Description
Technical Field
The present invention relates to aircraft starting power generation systems, and more particularly to an aircraft starting power generation system cable time division multiplexing circuit and method.
Background
Currently, aircraft are commonly provided with a starting power generation system, and an Auxiliary Power Unit (APU) has two functions of starting and generating power. In general, a starting power generation system is divided into a starting power generation split type architecture and a starting power generation integrated architecture. Because the integrated architecture can effectively reduce the weight of the aircraft, the integrated architecture for starting and generating electricity is widely applied to newer models.
The aircraft APU provides starting torque through a starter generator which requires a Starter Generator Control Unit (SGCU) to provide excitation power to drive the rotor to rotate, and after the APU reaches a specified speed, drives an Auxiliary Starter Generator (ASG) to power the aircraft. Therefore, the excitation power cable, the generator output feeder line and the generator voltage regulation point detection line are required to be designed to realize the function of the starting power generation system. The three cable designs that perform different functions of a conventional start-up power generation system are independent of each other. The existing aircraft starting power generation system is used for supplying power and detecting the design of a line, long cables are required to be arranged along the airframe, the weight of the aircraft is increased, and the economical efficiency of the operation of the aircraft is reduced.
Accordingly, there is a need in the art for techniques that effectively reduce the cables required on board an aircraft, shorten the overall length of the cables, reduce the weight of the aircraft, and reduce the cost of operation.
Disclosure of Invention
This summary is provided to introduce a selection of concepts in a simplified form that are further described below in the detailed description. This summary is not intended to identify key features or essential features of the claimed subject matter, nor is it intended to be used as an aid in determining the scope of the claimed subject matter.
In view of the above-described drawbacks of the prior art, an object of the present invention is to reduce the number and length of the aircraft starting power generation system cables, thereby reducing the total weight of the starting power generation system cables, realizing a reduction in the operating cost, and improving the economy of the aircraft.
According to a first aspect of the present invention, there is provided a cable time division multiplexing circuit for an aircraft starting power generation system, which may include a starter generator control unit SGCU, an auxiliary starter generator ASG, a switchboard RDP, the cable time division multiplexing circuit may include: a first set of cables connecting the SGCUs with the RDPs; a second set of cables connecting the RDP with the ASG; and a control unit configured to time-multiplex the first set of cables and the second set of cables according to a cable function and a usage phase of the aircraft starting power generation system, wherein during a starting phase of the aircraft starting power generation system, the SGCU excitation wire includes a first set of cables of the SGCU to RDP and a second set of cables of the RDP to ASG; wherein during a power generation phase of the aircraft starting power generation system, the generator output feeder includes a second set of cables of ASG through RDP and the voltage detection line includes a first set of cables of SGCU through RDP.
In one embodiment of the first aspect, the first and second sets of cables may be connected via posts at the input of the RDP.
In one embodiment of the first aspect, the SGCU may include an excitation power supply module and a voltage detection module.
In an embodiment of the first aspect, the control unit may be configured to connect the output of the SGCU with the excitation power supply module during a start-up phase, wherein the control unit may be configured to connect the output of the SGCU with the voltage detection module during a power generation phase.
In an embodiment of the first aspect, the RDP may comprise a power supply module, wherein during the power generation phase the control unit may be configured to connect an input of the RDP with the power supply module.
According to a second aspect of the present invention, there is provided a method for cable time division multiplexing of an aircraft starting power generation system, which may comprise a starter generator control unit SGCU, an auxiliary starter generator ASG, a switchboard RDP, which may comprise: using a first set of cables to connect the SGCUs with the RDPs; using a second set of cables to connect the RDP with the ASG; and time-sharing multiplexing the first set of cables and the second set of cables according to the cable function and the use stage of the aircraft starting power generation system; wherein during a start-up phase of the aircraft starting power generation system, the SGCU excitation wire includes a first set of cables of the SGCU to RDP and a second set of cables of the RDP to ASG; wherein during a power generation phase of the aircraft starting power generation system, the generator output feeder includes a second set of cables of ASG through RDP and the voltage detection line includes a first set of cables of SGCU through RDP.
In one embodiment of the second aspect, the first and second sets of cables may be connected via posts at the input of the RDP.
In one embodiment of the second aspect, the SGCU may include an excitation power supply module and a voltage detection module.
In an embodiment of the second aspect, during the start-up phase the output of the SGCU may be connected to the field supply module, wherein during the generation phase the output of the SGCU may be connected to the voltage detection module.
In one embodiment of the second aspect, the RDP may comprise a power supply module, wherein during the power generation phase, an input of the RDP may be connected to the power supply module.
By adopting the technical scheme provided by the invention, the complexity of the system can be reduced, and the reliability can be improved. In addition, the weight of the cables of the narrow passenger plane is reduced by about 7-10kg, and the weight of the cables of the wide passenger plane is reduced by 15-20kg, so that the operation cost of an airline company is reduced, and the operation benefit is improved.
These and other features and advantages will become apparent upon reading the following detailed description and upon reference to the associated drawings. It is to be understood that both the foregoing general description and the following detailed description are explanatory only and are not restrictive of aspects as claimed.
Drawings
So that the manner in which the above recited features of the present invention can be understood in detail, a more particular description of the invention, briefly summarized above, may be had by reference to embodiments, some of which are illustrated in the appended drawings. It is to be noted, however, that the appended drawings illustrate only certain typical aspects of this invention and are therefore not to be considered limiting of its scope, for the description may admit to other equally effective aspects.
Fig. 1 illustrates a schematic diagram of a conventional aircraft starting power generation system circuit design.
Fig. 2 illustrates a schematic diagram of a cable time division multiplexing circuit for an aircraft starting power generation system in accordance with one embodiment of the invention.
Fig. 3 illustrates a simplified schematic diagram of an SGCU time division multiplexing circuit design architecture according to one embodiment of the present invention.
Fig. 4 illustrates a simplified schematic diagram of an RDP time division multiplexing circuit design architecture in accordance with one embodiment of the invention.
Fig. 5 illustrates a flow chart of a method for cable time division multiplexing of an aircraft starting power generation system according to one embodiment of the invention.
Fig. 6 illustrates a block diagram of a hardware implementation of a control unit according to one embodiment of the invention.
Detailed Description
The features of the present invention will become more apparent from the detailed description set forth below when taken in conjunction with the drawings.
As mentioned above, in conventional aircraft starting power generation system wiring designs, the cables for different functions are typically independent of each other and are each routed along the fuselage.
Fig. 1 illustrates a schematic diagram of a circuit design of a conventional aircraft starting power generation system 100. The aircraft starting power generation system 100 may include a starter generator control unit SGCU 110, an auxiliary starter generator ASG120, and a distribution box RDP 130. Typically, three starter power cables may be used to connect the SGCU 110 with the ASG120 to provide excitation power to drive the rotor in rotation during the start-up phase of the aircraft starting power generation system 100. Further, six cables as generator output feeders are used to connect RDP 130 with ASG120 to provide electrical power generated by ASG120 during the power generation phase of aircraft starting power generation system 100. In order to detect the voltage, it is also necessary to provide a voltage detection line not shown in fig. 1. Thus, a plurality of cables with different functions and mutually independent cables are required to be arranged along the fuselage, so that more weight is brought, and the economy of the aircraft is not facilitated.
The invention discloses a design of a cable time-sharing multiplexing circuit of an aircraft starting power generation system, which performs time-sharing multiplexing on cables with different functions according to the functions and the using stages of the cables. By reducing the number and the length of the cables, the total weight of the cables of the starting power generation system is reduced, the operation cost is reduced, and the economy of the aircraft is improved.
The invention adopts the following circuit design scheme for realizing the purpose of the invention:
since the ASG does not need to supply ac power to the RDP in the start-up state; meanwhile, in the power generation state, the SGCU does not need to provide a starting power supply for the ASG, so that the SGCU to RDP and RDP to ASG section conductors are multiplexed in a time-sharing mode. And the connection of the cables is realized by utilizing the binding posts of the RDP input end. During the start phase, the SGCU excitation wire includes a SGCU to RDP section and an RDP to ASG section; in the power generation stage, the feeder line is an ASG to RDP section, the voltage detection line is an SGCU to RDP section, and the time-sharing multiplexing of the cable is realized.
Fig. 2 illustrates a schematic diagram of a cable time division multiplexing circuit for an aircraft starting power generation system 200 in accordance with one embodiment of the invention. The aircraft starter-generator system 200 may include a starter-generator control unit SGCU 210, an auxiliary starter generator ASG 220, and a switchboard RDP 230. The cable time division multiplexing circuit shown in fig. 2 may include a first set of cables 240 that connect SGCUs 210 with RDPs 230. For example, the first set of cables 240 may include a first cable connecting a first port of the SGCU 210 to an A2 port of the RDP 230, a second cable connecting a second port of the SGCU 210 to a B2 port of the RDP 230, and a third cable connecting a third port of the SGCU 210 to a C2 port of the RDP 230. The cable time division multiplexing circuitry may also include a second set of cables 250 that connect RDP 230 with ASG 220. For example, second set of cables 250 may include a fourth cable connecting the A2 port of RDP 230 to the power generation line A phase of ASG 220, a fifth cable connecting the B2 port of RDP 230 to the power generation line B phase of ASG 220, a sixth cable connecting the C2 port of RDP 230 to the power generation line C phase of ASG 220, a seventh cable connecting the A1 port of RDP 230 to the power generation line A phase of ASG 220, an eighth cable connecting the B1 port of RDP 230 to the power generation line B phase of ASG 220, and a ninth cable connecting the C1 port of RDP 230 to the power generation line C phase of ASG 220. The first set of cables 240 and the second set of cables 250 may be interconnected by posts at the input of the RDP 230.
The cable time division multiplexing circuit may include a control unit, not shown in fig. 2, that may be configured to time division multiplex the first set of cables 240 and the second set of cables 250 according to the cable functions and usage phases of the aircraft starting power generation system 200, wherein during a starting phase of the aircraft starting power generation system, the SGCU excitation wires include the first set of cables 240 of the SGCU 210 to the RDP 230 and the second set of cables 250 of the RDP 230 to the ASG 220, and during a power generation phase of the aircraft starting power generation system, the generator output feeder includes the second set of cables 250 of the ASG 220 to the RDP 230, and the voltage detection wires include the first set of cables 240 of the SGCU 210 to the RDP 230. Thereby, time-sharing multiplexing of the cable is achieved.
Fig. 3 illustrates a simplified schematic diagram of an SGCU time division multiplexing circuit design architecture according to one embodiment of the present invention. The SGCU shown in fig. 3 may include an excitation power supply module 310, a voltage detection module 320, and a switch 330. The field power module 310 may be configured to provide field power during a start-up phase of the aircraft starting power generation system. The voltage detection module 320 may be configured to provide voltage detection during a power generation phase of an aircraft starting power generation system. The switching of the switch 330 may be controlled by a control unit. For example, during a start-up phase of the aircraft starting power generation system, the control unit may switch the switch 330 to connect with the excitation power module 310 so that the SGCU output is connected with the excitation power module 310 for transmitting excitation power. During the generation phase of the aircraft starting power generation system, the control unit may switch the switch 330 to connect with the voltage detection module 320 so that the SGCU output is connected with the voltage detection module 320 in order to detect the distribution terminal voltage.
Fig. 4 illustrates a simplified schematic diagram of an RDP time division multiplexing circuit design architecture in accordance with one embodiment of the invention. The RDP shown in fig. 4 may include a power supply module 410 and a switch 420. Power module 410 may be configured to receive generator output power and distribute it to individual powered devices (e.g., loads) during a power generation phase of an aircraft starting power generation system. In the starting stage, the RDP input end is in a high-resistance state, and the exciting cable is not connected with the power supply module 410; in the power generation stage, the RDP input end is in a low-resistance state, the output power of the generator is received, and meanwhile, the detection circuit and the detection circuit are in equipotential. The switching of the switch 420 may be controlled by a control unit. For example, during a power generation phase of the aircraft starting power generation system, the control unit may switch the switch 420 to connect with the power supply module 410 to receive the generator output power.
Fig. 5 illustrates a flow chart of a method 500 for cable time division multiplexing of an aircraft starting power generation system in accordance with one embodiment of the invention.
At block 510, the method 500 may include: a first set of cables is used to connect the SGCUs with the RDPs. For example, referring to FIG. 2, a first set of cables 240 is used to connect SGCU 210 with RDP 230.
At block 520, the method 500 may include: a second set of cables is used to connect the RDP with the ASG. For example, referring to FIG. 2, a second set of cables 250 is used to connect RDP 230 with ASG 220.
At block 530, the method 500 may include: time-multiplexing the first set of cables and the second set of cables according to a cable function and a use phase of the aircraft starting power generation system, wherein during the start phase of the aircraft starting power generation system, the SGCU excitation wire comprises a first set of cables of the SGCU to the RDP and a second set of cables of the RDP to the ASG; wherein during a power generation phase of the aircraft starting power generation system, the generator output feeder includes a second set of cables of ASG through RDP and the voltage detection line includes a first set of cables of SGCU through RDP. For example, referring to fig. 2, during a start-up phase of an aircraft starting power generation system, the SGCU excitation wire includes a first set of cables 240 of SGCU 210 through RDP 230 and a second set of cables 250 of RDP 230 through ASG 220; wherein during a power generation phase of the aircraft starting power generation system, the generator output feeder includes a second set of cables 250 of ASG 220 through RDP 230 and the voltage detection line includes a first set of cables 240 of SGCU 210 through RDP 230.
In one embodiment of the method 500, the first set of cables and the second set of cables may be connected via posts at the input of the RDP.
In one embodiment of the method 500, the SGCU may include an excitation supply module and a voltage detection module.
In one embodiment of the method 500, during the start-up phase, the output of the SGCU may be connected to the field supply module, wherein during the generation phase, the output of the SGCU may be connected to the voltage detection module.
In one embodiment of the method 500, the RDP may include a power module, wherein during the power generation phase, an input of the RDP may be connected to the power module.
It should be appreciated that the design of the present invention is applicable to other circuits requiring start-up of power generation.
Fig. 6 illustrates a block diagram of a hardware implementation of a control unit according to one embodiment of the invention. Referring to fig. 6, a control apparatus 600 will now be described, the control apparatus 600 being an example of a control unit applicable to aspects of the present disclosure. The control device 600 may be any machine or device configured to perform processing and/or control, and may be, but is not limited to, a workstation, a server, a desktop computer, a laptop computer, a tablet computer, a personal digital assistant, a smart phone, or any combination thereof.
The control device 600 may include elements that are connected to the bus 602 or in communication with the bus 602, possibly via one or more interfaces. For example, the control device 600 may include a bus 602, one or more processors 604, one or more input devices 606, and one or more output devices 608. The one or more processors 604 may be any type of processor and may include, but is not limited to, one or more general purpose processors and/or one or more special purpose processors (such as a special purpose processing chip). Input device 606 may be any type of device that can input information into a computing device and may include, but is not limited to, a mouse, a keyboard, a touch screen, a microphone, and/or a remote control. Output device 608 may be any type of device that may present information and may include, but is not limited to, a display, speakers, video/audio output terminals, vibrators, and/or printers. The control device 600 may also include a non-transitory storage device 610 or be connected to the non-transitory storage device 610, the non-transitory storage device 610 may be any storage device that is non-transitory and that enables data storage, and may include, but is not limited to, disk drives, optical storage devices, solid state storageA floppy disk, a flexible disk, hard disk, magnetic tape, or any other magnetic medium, an optical disk or any other optical medium, a ROM (read only memory), a RAM (random access memory), a cache memory, and/or any other memory chip or cartridge, and/or any other medium from which a computer may read data, instructions, and/or code. The non-transitory storage device 610 may be separable from the interface. The non-transitory storage device 610 may have data/instructions/code for implementing the methods and steps described above. The control device 600 may also include a communication device 612. The communication device 612 may be any type of device or system capable of enabling communication with external equipment and/or a network and may include, but is not limited to, a modem, a network card, an infrared communication device, such as bluetooth TM Devices, 1302.11 devices, wiFi devices, wiMax devices, wireless communication devices and/or chipsets such as cellular communication facilities, and the like.
The control device 600 may also include a working memory 614, which working memory 614 may be any type of working memory that may store instructions and/or data useful for the operation of the processor 604, and may include, but is not limited to, random access memory and/or read-only memory devices.
Software elements may reside in the working memory 614 including, but not limited to, an operating system 616, one or more application programs 618, drivers, and/or other data and code. Instructions for performing the above-described methods and steps may be included in one or more application programs 618. Executable code or source code of instructions of the software elements may be stored in a non-transitory computer readable storage medium (such as the storage device 610 described above) and may be read into the working memory 614, possibly by compilation and/or installation. Executable code or source code for the instructions of the software elements may also be downloaded from a remote location.
From the above embodiments, it will be apparent to those skilled in the art that the present disclosure may be implemented by software having necessary hardware, or by hardware, firmware, or the like. Based on such understanding, embodiments of the present disclosure may be implemented in part in software. The computer software may be stored in a readable storage medium such as a floppy disk, hard disk, optical disk, or flash memory of a computer. The computer software includes a series of instructions to cause a computer (e.g., a personal computer, a service station, or a network terminal) to perform a method according to respective embodiments of the present disclosure, or a portion thereof.
Throughout this specification, reference has been made to "one example" or "an example" that means that a particular described feature, structure, or characteristic is included in at least one example. Thus, the use of such phrases may involve more than one example. Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more examples.
One skilled in the relevant art will recognize, however, that the examples may be practiced without one or more of the specific details, or with other methods, resources, materials, etc. In other instances, well-known structures, resources, or operations have not been shown or described in detail to avoid obscuring aspects of these examples.
While examples and applications have been illustrated and described, it should be understood that these examples are not limited to the precise configurations and resources described above. Various modifications, changes, and variations apparent to those skilled in the art may be made in the arrangement, operation, and details of the methods and systems disclosed herein without departing from the scope of the claimed examples.
Claims (10)
1. A cable time division multiplexing circuit for an aircraft starting power generation system including a starter generator control unit SGCU, an auxiliary starter generator ASG, a switchboard RDP, the cable time division multiplexing circuit comprising:
a first set of cables connecting the SGCU with the RDP;
a second set of cables connecting the RDP with the ASG; and
a control unit configured to time-division multiplex the first set of cables and the second set of cables according to cable functions and usage phases of the aircraft starting power generation system;
wherein during a start-up phase of the aircraft start-up power generation system, an SGCU exciter line includes the first set of cables of the SGCU to the RDP and the second set of cables of the RDP to the ASG;
wherein during a power generation phase of the aircraft starting power generation system, a generator output feeder includes the second set of cables of the ASG to the RDP, and a voltage detection line includes the first set of cables of the SGCU to the RDP.
2. The cable time division multiplexing circuit of claim 1, wherein the first set of cables and the second set of cables are connected via posts at an input of the RDP.
3. The cable time division multiplexing circuit of claim 1, wherein the SGCU comprises an excitation power supply module and a voltage detection module.
4. A cable time multiplexing circuit according to claim 3, wherein in the start-up phase the control unit is configured to connect the output of the SGCU with the excitation supply module, and wherein in the power generation phase the control unit is configured to connect the output of the SGCU with the voltage detection module.
5. The cable time division multiplexing circuit of claim 1, wherein the RDP comprises a power module, wherein during the power generation phase the control unit is configured to connect an input of the RDP with the power module.
6. A method for cable time division multiplexing of an aircraft starting power generation system comprising a starter generator control unit SGCU, an auxiliary starter generator ASG, a switchboard RDP, the method comprising:
connecting the SGCU with the RDP using a first set of cables;
connecting the RDP with the ASG using a second set of cables; and
time-division multiplexing the first set of cables and the second set of cables according to cable functions and usage phases of the aircraft starting power generation system;
wherein during a start-up phase of the aircraft start-up power generation system, an SGCU exciter line includes the first set of cables of the SGCU to the RDP and the second set of cables of the RDP to the ASG;
wherein during a power generation phase of the aircraft starting power generation system, a generator output feeder includes the second set of cables of the ASG to the RDP, and a voltage detection line includes the first set of cables of the SGCU to the RDP.
7. The method of claim 6, wherein the first set of cables and the second set of cables are connected via posts at an input of the RDP.
8. The method of claim 6, wherein the SGCU comprises a field supply module and a voltage detection module.
9. The method of claim 8, wherein an output of the SGCU is connected to the excitation power supply module during the start-up phase, and wherein an output of the SGCU is connected to the voltage detection module during the power generation phase.
10. The method of claim 6, wherein the RDP comprises a power module, wherein an input of the RDP is connected to the power module during the generating phase.
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| CN202110973396.8A CN113708679B (en) | 2021-08-24 | 2021-08-24 | Cable time-sharing multiplexing circuit and method for aircraft starting power generation system |
| PCT/CN2021/141883 WO2023024371A1 (en) | 2021-08-24 | 2021-12-28 | Time division multiplexing circuit and method for cables of starting-generation system of aircraft |
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| CN202110973396.8A CN113708679B (en) | 2021-08-24 | 2021-08-24 | Cable time-sharing multiplexing circuit and method for aircraft starting power generation system |
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| CN113708679A (en) | 2021-11-26 |
| WO2023024371A1 (en) | 2023-03-02 |
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