WO2023024371A1 - 一种飞机起动发电系统线缆分时复用电路及方法 - Google Patents

一种飞机起动发电系统线缆分时复用电路及方法 Download PDF

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WO2023024371A1
WO2023024371A1 PCT/CN2021/141883 CN2021141883W WO2023024371A1 WO 2023024371 A1 WO2023024371 A1 WO 2023024371A1 CN 2021141883 W CN2021141883 W CN 2021141883W WO 2023024371 A1 WO2023024371 A1 WO 2023024371A1
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cables
rdp
sgcu
starting
asg
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PCT/CN2021/141883
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English (en)
French (fr)
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浦程楠
程方舜
周绚
郦江
吕小娴
袁海宵
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中国商用飞机有限责任公司
中国商用飞机有限责任公司上海飞机设计研究院
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Publication of WO2023024371A1 publication Critical patent/WO2023024371A1/zh

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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
    • 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
    • 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

Definitions

  • the invention relates to an aircraft starting and generating system, and more particularly relates to a time-division multiplexing circuit and method for cables of the aircraft starting and generating system.
  • aircrafts are generally equipped with a starter power generation system, and the auxiliary power unit (APU) has two functions of starting and power generation.
  • the starter power generation system is divided into a starter power generation split structure and a start power generation integrated structure. Since adopting an integrated architecture can effectively reduce the weight of the aircraft, the integrated starter and power generation architecture has been widely used in relatively new models.
  • the aircraft APU provides starting torque through the starter generator.
  • the starter generator needs the excitation power provided by the starter generator control unit (SGCU) to drive the rotor to rotate. After the APU reaches the specified speed, it drives the auxiliary starter generator (ASG) to supply power to the aircraft. Therefore, it is necessary to design the excitation power cable, generator output feeder and generator voltage regulation point detection line to realize the function of the starter generator system.
  • the three cable designs for different functions of the traditional starter generator system are independent of each other.
  • the existing power supply and detection circuit design of the aircraft starting and generating system needs to arrange long cables along the fuselage, which increases the weight of the aircraft and reduces the economy of aircraft operation.
  • the purpose of the present invention is to reduce the quantity and length of the cables of the aircraft starting and generating system, thereby reducing the total weight of the cables of the starting and generating system, realizing the reduction of operating costs, and improving the economical efficiency of the aircraft. sex.
  • a cable time-division multiplexing circuit for an aircraft starting and generating system.
  • the aircraft starting and generating system may include a starter generator control unit SGCU, an auxiliary starter generator ASG, and a switchboard box RDP
  • the cable time-division multiplexing circuit may include: 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
  • the cable function and use stage of the starter generator system is used to time-division multiplex the first group of cables and the second group of cables, where in the startup stage of the aircraft starter generator system, the SGCU excitation wire includes the first group from SGCU to RDP Cables and the second set of cables from RDP to ASG; in the power generation stage of the aircraft starting and generating system, the generator output feeder includes the second set of cables from ASG to RDP, and the voltage detection line includes the first set of lines from SGCU to RDP cable.
  • the cables of the first group and the second group of cables may be connected via a binding post at the input end of the RDP.
  • the SGCU may include an excitation power supply module and a voltage detection module.
  • control unit in the starting phase, can be configured to connect the output end of the SGCU to the excitation power supply module, wherein in the power generation phase, the control unit can be configured to connect the output end of the SGCU to the The voltage detection module is connected.
  • the RDP may include a power supply module, wherein during the power generation phase, the control unit may be configured to connect the input terminal of the RDP to the power supply module.
  • a method for time-division multiplexing of cables for an aircraft starting and generating system which may include a starter-generator control unit SGCU, an auxiliary starter-generator ASG, and a switchboard box RDP
  • the method may include: using a first set of cables to connect the SGCU to the RDP; using a second set of cables to connect the RDP to the ASG;
  • the first group of cables and the second group of cables are time-division multiplexed;
  • the SGCU excitation wire includes the first group of cables from SGCU to RDP and the second group of cables from RDP to ASG ;
  • the generator output feeder includes the second set of cables from ASG to RDP, and the voltage detection line includes the first set of cables from SGCU to RDP.
  • the first group of cables and the second group of cables may be connected via a binding post at the input end of the RDP.
  • the SGCU may include an excitation power supply module and a voltage detection module.
  • the output terminal of the SGCU can be connected to the excitation power supply module during the start-up phase, and the output terminal of the SGCU can be connected to the voltage detection module during the power generation phase.
  • the RDP may include a power supply module, wherein in the power generation stage, the input end of the RDP may be connected to the power supply module.
  • the complexity of the system can be reduced and the reliability can be improved.
  • the weight reduction of cables for narrow-body passenger aircraft is about 7-10kg, and the weight of cables for wide-body passenger aircraft is 15-20kg, which reduces the operating costs of airlines and improves operational efficiency.
  • FIG. 1 illustrates a schematic diagram of a conventional aircraft starter generator system circuit design.
  • FIG. 2 illustrates a schematic diagram of a cable time-division multiplexing circuit for an aircraft starting and generating system according to an embodiment of the present invention.
  • FIG. 3 illustrates a simplified schematic diagram of an SGCU time-division multiplexing circuit design architecture according to an embodiment of the present invention.
  • FIG. 4 illustrates a simplified schematic diagram of an RDP time-division multiplexing circuit design architecture according to an embodiment of the present invention.
  • FIG. 5 illustrates a flowchart of a method for time-division multiplexing of cables for an aircraft starting and generating system according to an embodiment of the present invention.
  • Fig. 6 illustrates a block diagram of a hardware implementation of a control unit according to one embodiment of the invention.
  • cables with different functions are usually independent from each other and arranged along the fuselage respectively.
  • FIG. 1 illustrates a schematic diagram of a circuit design of a conventional aircraft starter generator system 100 .
  • the aircraft starter generator system 100 may include a starter generator control unit SGCU 110 , an auxiliary starter generator ASG 120 , and a switchboard box RDP 130 .
  • three starting power cables can be used to connect the SGCU 110 and the ASG 120, so as to provide excitation power to drive the rotor to rotate during the starting phase of the aircraft starting and generating system 100.
  • the RDP 130 is connected with the ASG 120 using six cables as generator output feeders to provide electric power generated by the ASG 120 during the generating phase of the aircraft start-up generating system 100.
  • the invention discloses a design of a cable time-division multiplexing circuit for an aircraft starting and generating system, in which cables with different functions are time-division multiplexed according to the functions and use stages of the cables.
  • the present invention adopts following circuit design scheme for realizing above-mentioned purpose of the invention:
  • the wires from the SGCU to the RDP and from the RDP to the ASG are time-division multiplexed. Use the binding posts on the RDP input terminal to connect the cables.
  • the SGCU excitation line includes the SGCU-RDP section and the RDP-ASG section; in the power generation phase, the feeder line is the ASG-RDP section, and the voltage detection line is the SGCU-RDP section, realizing the time-division multiplexing of cables.
  • FIG. 2 illustrates a schematic diagram of a cable time-division multiplexing circuit for an aircraft starting and generating system 200 according to an embodiment of the present 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 box RDP 230 .
  • the cable time division multiplexing circuit shown in FIG. 2 may include a first set of cables 240 connecting the SGCU 210 with the RDP 230.
  • first set of cables 240 may include a first cable connecting a first port of SGCU 210 to A2 port of RDP 230, a second cable connecting a second port of SGCU 210 to B2 port of RDP 230, and a third cable connecting the third port of the SGCU 210 to the C2 port of the RDP 230.
  • the cable time-division multiplexing circuit may also include a second set of cables 250 connecting the RDP 230 and the ASG 220.
  • the second set of cables 250 may include a fourth cable connecting the A2 port of the RDP 230 to phase A of the generator line of the ASG 220, and a fifth cable connecting the B2 port of the RDP 230 to phase B of the generator line of the ASG 220 Connect the C2 port of the RDP 230 to the sixth cable of the C phase of the generator line of the ASG 220, connect the A1 port of the RDP 230 to the seventh cable of the A phase of the ASG 220 generator line, and connect the B1 port of the RDP 230
  • the first group of cables 240 and the second group of cables 250 can be connected to each other through the binding post at the input end of the RDP 230 .
  • the cable time-division multiplexing circuit may include a control unit not shown in FIG.
  • a group of cables 250 is used for time-division multiplexing, wherein in the starting phase of the aircraft starting and generating system, the SGCU excitation wires include the first group of cables 240 from the SGCU 210 to the RDP 230 and the second group of cables 250 from the RDP 230 to the ASG 220,
  • the generator output feeder includes the second set of cables 250 from the ASG 220 to the RDP 230
  • the voltage detection line includes the first set of cables 240 from the SGCU 210 to the RDP 230.
  • FIG. 3 illustrates a simplified schematic diagram of an SGCU time-division multiplexing circuit design architecture according to an 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 supply module 310 may be configured to provide field power during a start-up phase of the aircraft start-up generation system.
  • the voltage detection module 320 may be configured to provide voltage detection during the power generation phase of the aircraft start-up power generation system. Switching of the switch 330 may be controlled by the control unit.
  • the control unit may switch the switch 330 to connect with the excitation power module 310 so that the SGCU output terminal is connected with the excitation power module 310 to transmit the excitation power.
  • the control unit can switch the switch 330 to be connected to the voltage detection module 320 so that the SGCU output terminal is connected to the voltage detection module 320 so as to detect the distribution terminal voltage.
  • FIG. 4 illustrates a simplified schematic diagram of an RDP time-division multiplexing circuit design architecture according to an embodiment of the present invention.
  • the RDP shown in FIG. 4 may include a power supply module 410 and a switch 420 .
  • the power supply module 410 may be configured to receive the output power of the generator and distribute it to various electrical devices (eg, loads) during the power generation phase of the aircraft start-up power generation system.
  • the RDP input end In the starting phase, the RDP input end is in a high-impedance state, and the excitation cable is not connected to the power supply module 410; in the power generation phase, the RDP input end is in a low-impedance state, receiving the output power of the generator, and at the same time, the detection circuit is at the same potential as it.
  • Switching of the switch 420 may be controlled by the control unit. For example, in the power generation phase of the aircraft starting power generation system, the control unit can switch the switch 420 to connect with the power supply module 410, so as to
  • FIG. 5 illustrates a flow chart of a method 500 for time-division multiplexing of cables for an aircraft starting and generating system according to an embodiment of the present invention.
  • the method 500 may include using a first set of cables to connect the SGCU with the RDP.
  • the SGCU 210 is connected to the RDP 230 using a first set of cables 240.
  • the method 500 may include using a second set of cables to connect the RDP to the ASG.
  • the RDP 230 is connected to the ASG 220 using a second set of cables 250.
  • the method 500 may include: time-division multiplexing the first set of cables and the second set of cables according to the cable function and use phase of the aircraft start-up generation system, wherein during the start-up phase of the aircraft start-up generation system,
  • the SGCU excitation line includes the first set of cables from SGCU to RDP and the second set of cables from RDP to ASG; where in the power generation stage of the aircraft starting and generating system, the generator output feeder includes the second set of cables from ASG to RDP, the voltage
  • the detection cables include the first set of cables from the SGCU to the RDP.
  • the SGCU excitation wires include the first group of cables 240 from the SGCU 210 to the RDP 230 and the second group of cables 250 from the RDP 230 to the ASG 220;
  • the generator output feeder includes the second set of cables 250 from the ASG 220 to the RDP 230, and the voltage detection line includes the first set of cables 240 from the SGCU 210 to the RDP 230.
  • the cables of the first group and the second group of cables may be connected via a binding post at an input end of the RDP.
  • the SGCU may include an excitation power supply module and a voltage detection module.
  • the output terminal of the SGCU in the start-up phase, may be connected to the excitation power supply module, wherein in the power generation phase, the output terminal of the SGCU may be connected to the voltage detection module.
  • the RDP may include a power supply module, wherein in the power generation phase, the input end of the RDP may be connected to the power supply module.
  • Fig. 6 illustrates a block diagram of a hardware implementation of a control unit according to one embodiment of the invention.
  • a control device 600 will now be described, which is 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, which may be, but is not limited to, a workstation, server, desktop computer, laptop computer, tablet computer, personal digital assistant, smart phone, or any combination.
  • control device 600 may comprise elements connected to or in communication with the bus 602 , possibly via one or more interfaces.
  • control device 600 may include a bus 602 , as well as 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 are not limited to, one or more general purpose processors and/or one or more special purpose processors (such as dedicated processing chips).
  • Input device 606 can be any type of device that can enter information into a computing device, and can include, but is not limited to, a mouse, keyboard, touch screen, microphone, and/or remote control.
  • Output devices 608 may be any type of device that can present information, and may include, but are not limited to, displays, 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 capable of storing data, and may include But not limited to disk drives, optical storage devices, solid state storage, floppy disks, floppy disks, hard disks, tapes or any other magnetic media, optical disks or any other optical media, ROM (Read Only Memory), RAM (Random Access Memory), cache memory and/or any other memory chip or cartridge, and/or any other medium from which a computer can read data, instructions and/or code.
  • the non-transitory storage device 610 may be separate from the interface.
  • the non-transitory storage device 610 may have data/instructions/codes for implementing the above methods and steps.
  • the control device 600 may also include a communication device 612 .
  • Communication device 612 may be any type of device or system that enables communication with external devices and/or networks, and may include, but is not limited to, modems, network cards, infrared communication devices, devices such as Bluetooth TM devices, 1302.11 devices, WiFi devices, WiMax devices, wireless communication devices such as cellular communication facilities and/or chipsets, etc.
  • the bus 602 may include, but is not limited to, an Industry Standard Architecture (ISA) bus, a Micro Channel Architecture (MCA) bus, an Enhanced ISA (EISA) bus, a Video Electronics Standards Association (VESA) local bus, and a Peripheral Component Interconnect (PCI) bus .
  • ISA Industry Standard Architecture
  • MCA Micro Channel Architecture
  • EISA Enhanced ISA
  • VESA Video Electronics Standards Association
  • PCI Peripheral Component Interconnect
  • Control device 600 may also include working memory 614, which may be any type of working memory that may store instructions and/or data useful for the operation of processor 604, and may include, but is not limited to, random access memory and and/or read-only memory devices.
  • working memory 614 may be any type of working memory that may store instructions and/or data useful for the operation of processor 604, and may include, but is not limited to, random access memory and and/or read-only memory devices.
  • Software elements may be located in working memory 614 including, but not limited to, operating system 616, one or more application programs 618, drivers, and/or other data and code. Instructions for performing the methods and steps described above may be included in one or more application programs 618 .
  • the executable code or source code of the 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 compiling and/or installing middle. Executable or source code for instructions of a software element may also be downloaded from a remote location.
  • the present disclosure can be realized by software with necessary hardware, or by hardware, firmware and the like. Based on such an understanding, the embodiments of the present disclosure may be partially implemented in the form of software.
  • the computer software can be stored on a readable storage medium such as a computer's floppy disk, hard disk, optical disk or flash memory.
  • the computer software includes a series of instructions to make a computer (for example, a personal computer, a service station or a network terminal) execute the method or a part thereof according to the corresponding embodiment of the present disclosure.

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Abstract

本发明提供了一种用于飞机起动发电系统的线缆分时复用电路，飞机起动发电系统包括起动发电机控制单元SGCU、辅助起动发电机ASG、配电盘箱RDP，该分时复用电路包括：将SGCU与RDP相连接的第一组线缆；将RDP与ASG相连接的第二组线缆；其中在起动阶段，SGCU励磁线包括SGCU至RDP的第一组线缆和RDP至ASG的第二组线缆；其中在发电阶段，发电机输出馈线包括ASG至RDP的第二组线缆，电压检测线包括SGCU至RDP的第一组线缆。此外，本发明还提供了一种用于飞机起动发电系统的线缆分时复用的方法。通过本发明，能够显著减少飞机起动发电系统线缆的数量和长度，从而减轻起动发电系统线缆的总重量。

Description

一种飞机起动发电系统线缆分时复用电路及方法
本申请要求中国专利申请CN 202110973396.8的优先权。
技术领域
本发明涉及飞机起动发电系统，更具体地，涉及飞机起动发电系统线缆分时复用电路及方法。
背景技术
当前飞机普遍安装了起动发电系统，辅助动力单元(APU)具备起动和发电两项功能。通常情况下，起动发电系统分为起动发电分体式架构和起动发电一体化架构。由于采用一体式架构可以有效地降低飞机重量，因此，起动发电一体化架构在比较新的机型中获得了广泛应用。
飞机APU通过起动发电机提供起动扭矩，起动发电机需要起动发电机控制单元(SGCU)提供励磁功率以驱动转子转动，在APU达到指定转速后，驱动辅助起动发电机(ASG)向飞机供电。因此实现起动发电系统功能需要设计励磁功率线缆、发电机输出馈线和发电机调压点检测线。传统的起动发电系统的这三个实现不同功能的线缆设计是相互独立的。现有的飞机起动发电系统供电、检测线路设计需要沿机身布置较长的线缆，增加飞机重量，降低飞机运营的经济性。
因此，本领域中存在对于有效减少飞机上需要的电缆、缩短电缆的总长度、降低飞机重量、降低运营成本的技术的需要。
发明内容
提供本发明内容以便以简化形式介绍将在以下具体实施方式中进一步的描述一些概念。本发明内容并非旨在标识所要求保护的主题的关键特征或必要特征，也不旨在用于帮助确定所要求保护的主题的范围。
鉴于以上描述的现有技术中的缺陷，本发明的目的在于，减少飞机起动发电 系统线缆的数量和长度，从而减轻起动发电系统线缆的总重量，实现运营成本的降低，提高飞机的经济性。
根据本发明的第一方面，提供了一种用于飞机起动发电系统的线缆分时复用电路，该飞机起动发电系统可以包括起动发电机控制单元SGCU、辅助起动发电机ASG、配电盘箱RDP，该线缆分时复用电路可以包括：将SGCU与RDP相连接的第一组线缆；将RDP与ASG相连接的第二组线缆；以及控制单元，该控制单元被配置成根据飞机起动发电系统的线缆功能和使用阶段来对第一组线缆和第二组线缆进行分时复用，其中在飞机起动发电系统的起动阶段，SGCU励磁线包括SGCU至RDP的第一组线缆和RDP至ASG的第二组线缆；其中在飞机起动发电系统的发电阶段，发电机输出馈线包括ASG至RDP的第二组线缆，电压检测线包括SGCU至RDP的第一组线缆。
在第一方面的一个实施例中，第一组线缆和第二组线缆可以经由RDP的输入端的接线柱来实现线缆的连接。
在第一方面的一个实施例中，SGCU可以包括励磁供电模块和电压检测模块。
在第一方面的一个实施例中，在起动阶段，控制单元可以被配置成将SGCU的输出端可以与励磁供电模块相连接，其中在发电阶段，控制单元可以被配置成将SGCU的输出端与电压检测模块相连接。
在第一方面的一个实施例中，RDP可以包括供电模块，其中在发电阶段，控制单元可以被配置成将RDP的输入端与供电模块相连接。
根据本发明的第二方面，提供了一种用于飞机起动发电系统的线缆分时复用的方法，该飞机起动发电系统可以包括起动发电机控制单元SGCU、辅助起动发电机ASG、配电盘箱RDP，该方法可以包括：使用第一组线缆来将SGCU与RDP相连接；使用第二组线缆来将RDP与ASG相连接；以及根据飞机起动发电系统的线缆功能和使用阶段来对第一组线缆和第二组线缆进行分时复用；其中在飞机起动发电系统的起动阶段，SGCU励磁线包括SGCU至RDP的第一组线缆和RDP至ASG的第二组线缆；其中在飞机起动发电系统的发电阶段，发电机输出馈线包括ASG至RDP的第二组线缆，电压检测线包括SGCU至RDP的第一组线缆。
在第二方面的一个实施例中，第一组线缆和第二组线缆可以经由RDP的输入端的接线柱来实现线缆的连接。
在第二方面的一个实施例中，SGCU可以包括励磁供电模块和电压检测模块。
在第二方面的一个实施例中，在起动阶段，SGCU的输出端可以与励磁供电模块相连接，其中在发电阶段，SGCU的输出端可以与电压检测模块相连接。
在第二方面的一个实施例中，RDP可以包括供电模块，其中在发电阶段，RDP的输入端可以与供电模块相连接。
通过采用本发明提供的技术方案，可以降低系统复杂度、提高可靠性。此外，窄体客机线缆减重约7-10kg，宽体客机线缆减重15-20kg，降低了航空公司运营成本，提高运营效益。
通过阅读下面的详细描述并参考相关联的附图，这些及其他特点和优点将变得显而易见。应该理解，前面的概括说明和下面的详细描述只是说明性的，不会对所要求保护的各方面形成限制。
附图说明
为了能详细地理解本发明的上述特征所用的方式，可以参照各实施例来对以上简要概述的内容进行更具体的描述，其中一些方面在附图中示出。然而应该注意，附图仅示出了本发明的某些典型方面，故不应被认为限定其范围，因为该描述可以允许有其它等同有效的方面。
图1解说了传统的飞机起动发电系统电路设计的示意图。
图2解说了根据本发明的一个实施例的用于飞机起动发电系统的线缆分时复用电路的示意图。
图3解说了根据本发明的一个实施例的SGCU分时复用电路设计架构简化示意图。
图4解说了根据本发明的一个实施例的RDP分时复用电路设计架构简化示意图。
图5解说了根据本发明的一个实施例的用于飞机起动发电系统的线缆分时复用的方法的流程图。
图6解说了根据本发明的一个实施例的控制单元的硬件实现的框图。
具体实施方式
下面结合附图详细描述本发明，本发明的特点将在以下的具体描述中得到进一步的显现。
如以上提及的，在传统的飞机起动发电系统布线设计中，不同功能的线缆通常相互独立，分别沿机身布置。
图1解说了传统的飞机起动发电系统100的电路设计的示意图。飞机起动发电系统100可以包括起动发电机控制单元SGCU 110、辅助起动发电机ASG 120、配电盘箱RDP 130。通常，可以使用三根起动电源线缆来将SGCU 110与ASG 120相连接，以在飞机起动发电系统100的起动阶段提供励磁功率以便驱动转子转动。此外，使用作为发电机输出馈线的六根线缆来将RDP 130与ASG 120相连接，以在飞机起动发电系统100的发电阶段提供由ASG 120生成的电功率。为了检测电压，还需要提供图1中未示出的电压检测线。如此，需要沿机身布置很多根具有不同功能且相互独立的线缆，从而带来了较多的重量，不利于飞机的经济性。
本发明公开了一种飞机起动发电系统线缆分时复用电路设计，根据线缆的功能、使用阶段对不同功能的线缆进行了分时复用。通过减少线缆的数量和长度，减轻了起动发电系统线缆的总重量，实现运营成本的降低，提高飞机的经济性。
本发明为实现上述发明目的采用如下的电路设计方案：
由于起动状态下，ASG不需要向RDP提供交流电；同时，发电状态下，SGCU不需要向ASG提供起动电源，因此，将SGCU至RDP及RDP至ASG段导线分时复用。利用RDP输入端的接线柱实现线缆的连接。在起动阶段，SGCU励磁线包括SGCU至RDP段和RDP至ASG段；在发电阶段，馈线为ASG至RDP段，电压检测线为SGCU至RDP段，实现了线缆的分时复用。
图2解说了根据本发明的一个实施例的用于飞机起动发电系统200的线缆分时复用电路的示意图。飞机起动发电系统200可以包括起动发电机控制单元SGCU 210、辅助起动发电机ASG 220、配电盘箱RDP 230。图2中所示的线缆分时复用电路可以包括将SGCU 210与RDP 230相连接的第一组线缆240。例如，第一组线缆240可以包括将SGCU 210的第一端口连接至RDP 230的A2端口的第一线缆、将SGCU 210的第二端口连接至RDP 230的B2端口的第二线缆、以及将SGCU 210的第三端口连接至RDP 230的C2端口的第三线缆。线缆分时复用电路还可以包括将RDP 230与ASG 220相连接的第二组线缆250。例如，第二组线缆250可以包 括将RDP 230的A2端口连接至ASG 220的发电线A相的第四线缆，将RDP 230的B2端口连接至ASG 220的发电线B相的第五线缆，将RDP 230的C2端口连接至ASG 220的发电线C相的第六线缆，将RDP 230的A1端口连接至ASG 220的发电线A相的第七线缆，将RDP 230的B1端口连接至ASG 220的发电线B相的第八线缆，以及将RDP 230的C1端口连接至ASG 220的发电线C相的第九线缆。第一组线缆240和第二组线缆250可以通过RDP 230输入端的接线柱来实现相互连接。
线缆分时复用电路可以包括图2中未示出的控制单元，该控制单元可以被配置成根据飞机起动发电系统200的线缆功能和使用阶段来对第一组线缆240和第二组线缆250进行分时复用，其中在飞机起动发电系统的起动阶段，SGCU励磁线包括SGCU 210至RDP 230的第一组线缆240和RDP 230至ASG 220的第二组线缆250，而在飞机起动发电系统的发电阶段，发电机输出馈线包括ASG 220至RDP 230的第二组线缆250，电压检测线包括SGCU 210至RDP 230的第一组线缆240。由此，实现了线缆的分时复用。
图3解说了根据本发明的一个实施例的SGCU分时复用电路设计架构简化示意图。图3中所示的SGCU可以包括励磁供电模块310、电压检测模块320和开关330。励磁供电模块310可以被配置成用于在飞机起动发电系统的起动阶段提供励磁功率。电压检测模块320可以被配置成用于在飞机起动发电系统的发电阶段提供电压检测。开关330的切换可以由控制单元来控制。例如，在飞机起动发电系统的起动阶段，控制单元可以将开关330切换至与励磁功率模块310相连接以使得SGCU输出端与励磁功率模块310相连接，以便传输励磁功率。在飞机起动发电系统的发电阶段，控制单元可以将开关330切换至与电压检测模块320相连接以使得SGCU输出端与电压检测模块320相连接，以便检测配电端电压。
图4解说了根据本发明的一个实施例的RDP分时复用电路设计架构简化示意图。图4中所示的RDP可以包括供电模块410和开关420。供电模块410可以被配置成用于在飞机起动发电系统的发电阶段接收发电机输出功率并将其分配给各个用电设备(例如，负载)。在起动阶段，RDP输入端高阻态，励磁线缆与供电模块410无连接；在发电阶段，RDP输入端低阻态，接收发电机输出功率，同时，检测电路与其等电势。开关420的切换可以由控制单元来控制。例如，在飞机起动 发电系统的发电阶段，控制单元可以将开关420切换至与供电模块410相连接，以接收发电机输出功率。
图5解说了根据本发明的一个实施例的用于飞机起动发电系统的线缆分时复用的方法500的流程图。
在框510，方法500可以包括：使用第一组线缆来将SGCU与RDP相连接。例如，参照图2，使用第一组线缆240来将SGCU 210与RDP 230相连接。
在框520，方法500可以包括：使用第二组线缆来将RDP与ASG相连接。例如，参照图2，使用第二组线缆250来将RDP 230与ASG 220相连接。
在框530，方法500可以包括：根据飞机起动发电系统的线缆功能和使用阶段来对第一组线缆和第二组线缆进行分时复用，其中在飞机起动发电系统的起动阶段，SGCU励磁线包括SGCU至RDP的第一组线缆和RDP至ASG的第二组线缆；其中在飞机起动发电系统的发电阶段，发电机输出馈线包括ASG至RDP的第二组线缆，电压检测线包括SGCU至RDP的第一组线缆。例如，参照图2，在飞机起动发电系统的起动阶段，SGCU励磁线包括SGCU 210至RDP 230的第一组线缆240和RDP 230至ASG 220的第二组线缆250；其中在飞机起动发电系统的发电阶段，发电机输出馈线包括ASG 220至RDP 230的第二组线缆250，电压检测线包括SGCU 210至RDP 230的第一组线缆240。
在方法500的一个实施例中，第一组线缆和第二组线缆可以经由RDP的输入端的接线柱来实现线缆的连接。
在方法500的一个实施例中，SGCU可以包括励磁供电模块和电压检测模块。
在方法500的一个实施例中，在起动阶段，SGCU的输出端可以与励磁供电模块相连接，其中在发电阶段，SGCU的输出端可以与电压检测模块相连接。
在方法500的一个实施例中，RDP可以包括供电模块，其中在发电阶段，RDP的输入端可以与供电模块相连接。
应当理解，本发明涉及的设计也可以应用于其他需要起动发电的电路。
图6解说了根据本发明的一个实施例的控制单元的硬件实现的框图。参照图6，现在将描述控制设备600，控制设备600是可应用于本公开的各方面的控制单元的示例。控制设备600可以是配置成执行处理和/或控制的任何机器或设备，可以是但不限于工作站、服务器、桌面型计算机、膝上型计算机、平板计算机、个人 数字助理、智能电话、或其任何组合。
控制设备600可以包括可能地经由一个或多个接口来与总线602连接或者与总线602处于通信的元件。例如，控制设备600可以包括总线602、以及一个或多个处理器604、一个或多个输入设备606和一个或多个输出设备608。该一个或多个处理器604可以是任何类型的处理器，并且可以包括但不限于一个或多个通用处理器和/或一个或多个专用处理器(诸如专门的处理芯片)。输入设备606可以是可将信息输入计算设备的任何类型的设备，并且可以包括但不限于鼠标、键盘、触摸屏、话筒、和/或遥控器。输出设备608可以是可呈现信息的任何类型的设备，并且可以包括但不限于显示器、扬声器、视频/音频输出终端、振动器和/或打印机。控制设备600还可以包括非瞬态存储设备610或者与非瞬态存储设备610相连接，该非瞬态存储设备610可以是为非瞬态的且可实现数据存储的任何存储设备，并且可以包括但不限于盘驱动器、光存储设备、固态存储、软盘、软磁盘、硬盘、磁带或任何其他磁性介质、光盘或任何其他光介质、ROM(只读存储器)、RAM(随机存取存储器)、高速缓存存储器和/或任何其他存储器芯片或存储器盒、和/或计算机可从其读取数据、指令和/或代码的任何其他介质。非瞬态存储设备610可以能与接口分开。非瞬态存储设备610可以具有用于实现上述方法和步骤的数据/指令/代码。控制设备600还可以包括通信设备612。通信设备612可以是能实现与外部装置和/或网络的通信的任何类型的设备或系统，并且可以包括但不限于调制解调器、网卡、红外通信设备、诸如蓝牙 TM设备、1302.11设备、WiFi设备、WiMax设备、蜂窝通信设施之类的无线通信设备和/或芯片组、等等。
总线602可以包括但不限于工业标准架构(ISA)总线、微通道架构(MCA)总线、增强型ISA(EISA)总线、视频电子标准协会(VESA)本地总线、以及外围组件互连(PCI)总线。
控制设备600还可以包括工作存储器614，工作存储器614可以是可存储对于处理器604的工作而言有用的指令和/或数据的任何类型的工作存储器，并且可以包括但不限于随机存取存储器和/或只读存储器设备。
软件元素可以位于工作存储器614中，包括但不限于操作系统616、一个或多个应用程序618、驱动程序和/或其他数据和代码。用于执行上述方法和步骤的指令可以包括在一个或多个应用程序618中。软件元素的指令的可执行代码或源代码可 以被存储在非瞬态计算机可读存储介质(诸如上述存储设备610)中，并且可以可能地通过编译和/或安装而被读取到工作存储器614中。软件元素的指令的可执行代码或源代码也可以从远程位置下载。
从上面的实施例中，本领域技术人员可以清楚地知道，本公开可以由具有必要硬件的软件来实现，或者由硬件、固件等来实现。基于这样的理解，本公开的实施例可以部分地以软件形式来实施。可以将计算机软件存储在诸如计算机的软盘、硬盘、光盘或闪存之类的可读存储介质中。该计算机软件包括一系列指令，以使计算机(例如，个人计算机、服务站或网络终端)执行根据本公开的相应实施例的方法或其一部分。
在整个说明书中，已经对“一个示例”或“一示例”进行了参考，这意味着在至少一个示例中包括具体描述的特征、结构或特性。因此，此类短语的使用可能涉及不止一个示例。此外，所描述的特征、结构或特性可以在一个或多个示例中以任何合适的方式组合。
然而，相关领域的技术人员可以认识到，可以在没有一个或多个特定细节的情况下，或者在其他方法、资源、材料等的情况下实践这些示例。在其他实例中，没有详细示出或描述众所周知的结构、资源或操作以避免使这些示例的各方面模糊。
尽管已经解说和描述了诸样例和应用，但是应当理解，这些示例不限于上述精确的配置和资源。可以对本文公开的方法和系统的布置、操作和细节作出对于本领域技术人员而言显而易见的各种修改、改变和变化，而不会脱离所要求保护的示例的范围。

Claims (10)

  1. 一种用于飞机起动发电系统的线缆分时复用电路，所述飞机起动发电系统包括起动发电机控制单元SGCU、辅助起动发电机ASG、配电盘箱RDP，所述线缆分时复用电路包括：
    将所述SGCU与所述RDP相连接的第一组线缆；
    将所述RDP与所述ASG相连接的第二组线缆；以及
    控制单元，配置成根据所述飞机起动发电系统的线缆功能和使用阶段来对所述第一组线缆和所述第二组线缆进行分时复用；
    其中在所述飞机起动发电系统的起动阶段，SGCU励磁线包括所述SGCU至所述RDP的所述第一组线缆和所述RDP至所述ASG的所述第二组线缆；
    其中在所述飞机起动发电系统的发电阶段，发电机输出馈线包括所述ASG至所述RDP的所述第二组线缆，电压检测线包括所述SGCU至所述RDP的所述第一组线缆。
  2. 如权利要求1所述的线缆分时复用电路，其特征在于，所述第一组线缆和所述第二组线缆经由所述RDP的输入端的接线柱来实现线缆的连接。
  3. 如权利要求1所述的线缆分时复用电路，其特征在于，所述SGCU包括励磁供电模块和电压检测模块。
  4. 如权利要求3所述的线缆分时复用电路，其特征在于，在所述起动阶段，所述控制单元被配置成将所述SGCU的输出端与所述励磁供电模块相连接，其中在所述发电阶段，所述控制单元被配置成将所述SGCU的输出端与所述电压检测模块相连接。
  5. 如权利要求1所述的线缆分时复用电路，其特征在于，所述RDP包括供电模块，其中在所述发电阶段，所述控制单元被配置成将所述RDP的输入端与所述供电模块相连接。
  6. 一种用于飞机起动发电系统的线缆分时复用的方法，所述飞机起动发电系统包括起动发电机控制单元SGCU、辅助起动发电机ASG、配电盘箱RDP，所述方法包括：
    使用第一组线缆来将所述SGCU与所述RDP相连接；
    使用第二组线缆来将所述RDP与所述ASG相连接；以及
    根据所述飞机起动发电系统的线缆功能和使用阶段来对所述第一组线缆和所述第二组线缆进行分时复用；
    其中在所述飞机起动发电系统的起动阶段，SGCU励磁线包括所述SGCU至所述RDP的所述第一组线缆和所述RDP至所述ASG的所述第二组线缆；
    其中在所述飞机起动发电系统的发电阶段，发电机输出馈线包括所述ASG至所述RDP的所述第二组线缆，电压检测线包括所述SGCU至所述RDP的所述第一组线缆。
  7. 如权利要求6所述的方法，其特征在于，所述第一组线缆和所述第二组线缆经由所述RDP的输入端的接线柱来实现线缆的连接。
  8. 如权利要求6所述的方法，其特征在于，所述SGCU包括励磁供电模块和电压检测模块。
  9. 如权利要求8所述的方法，其特征在于，在所述起动阶段，所述SGCU的输出端与所述励磁供电模块相连接，其中在所述发电阶段，所述SGCU的输出端与所述电压检测模块相连接。
  10. 如权利要求6所述的方法，其特征在于，所述RDP包括供电模块，其中在所述发电阶段，所述RDP的输入端与所述供电模块相连接。
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