阅读说明：本技术 一种飞机起动发电系统线缆分时复用电路及方法 (Cable time-sharing multiplexing circuit and method for aircraft starting power generation system ) 是由 浦程楠 程方舜 周绚 郦江 吕小娴 袁海宵 于 2021-08-24 设计创作，主要内容包括：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。(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 generator control unit SGCU, an auxiliary starting generator ASG and a distribution panel box RDP, and the time-sharing multiplexing circuit comprises: a first set of cables connecting the SGCU with the RDP; a second set of cables connecting the RDP with the ASG; wherein during a start-up phase, the SGCU excitation line 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 feed line comprises a second set of cables from ASG to RDP and the voltage detection line comprises a first set of cables from SGCU to RDP. In addition, the invention also provides a method for time-sharing multiplexing of cables of the aircraft starting power generation system. By the invention, the number and the length of the aircraft starting power generation system cables can be obviously reduced, so that the total weight of the starting power generation system cables is reduced.)

1. A cable time-sharing multiplexing circuit for an aircraft starting power generation system including a Starter Generator Control Unit (SGCU), an Auxiliary Starter Generator (ASG), a distribution switchboard cabinet (RDP), the cable time-sharing 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-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 startup phase of the aircraft starting power generation system, an SGCU field line includes the first set of cables from the SGCU to the RDP and the second set of cables from the RDP to the ASG;

wherein during a power generation phase of the aircraft starting power generation system, a generator output feed line comprises the ASG to the second set of cables of the RDP and a voltage detection line comprises the SGCU to the first set of cables of the RDP.

2. The cable time-sharing multiplexing circuit of claim 1 wherein the first set of cables and the second set of cables are connected via a lug at an input of the RDP.

3. The cable time-sharing multiplexing circuit of claim 1 wherein the SGCU includes an excitation power supply module and a voltage detection module.

4. The cable time-sharing multiplexing circuit of claim 3, wherein during the startup phase, the control unit is configured to connect the output of the SGCU with the excitation power supply module, wherein during 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-sharing multiplexing circuit of claim 1, wherein the RDP includes 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 time-sharing multiplexing of cables for an aircraft starting power generation system including a starter generator control unit SGCU, an auxiliary starter generator ASG, a distribution switchboard cabinet 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 startup phase of the aircraft starting power generation system, an SGCU field line includes the first set of cables from the SGCU to the RDP and the second set of cables from the RDP to the ASG;

wherein during a power generation phase of the aircraft starting power generation system, a generator output feed line comprises the ASG to the second set of cables of the RDP and a voltage detection line comprises the SGCU to the first set of cables of the RDP.

7. The method of claim 6, wherein the first set of wires and the second set of wires are connected via a lug at an input end of the RDP.

8. The method of claim 6, wherein the SGCU includes an excitation power supply module and a voltage detection module.

9. The method of claim 8, wherein the output of the SGCU is coupled to the field supply module during the startup phase, and wherein the output of the SGCU is coupled to the voltage detection module during the power generation phase.

10. The method of claim 6, wherein the RDP includes a power module, wherein an input of the RDP is connected to the power module during the power generation phase.

Technical Field

The invention relates to an aircraft starting power generation system, in particular to a cable time-sharing multiplexing circuit and a cable time-sharing multiplexing method for the aircraft starting power generation system.

Background

At present, a starting power generation system is generally installed on an airplane, and an Auxiliary Power Unit (APU) has two functions of starting and generating power. Generally, a starting and power generating system is divided into a starting and power generating split type architecture and a starting and power generating integrated architecture. Because the integrated framework can effectively reduce the weight of the airplane, the starting and power generation integrated framework is widely applied to a newer model.

The aircraft APU provides starting torque through a starter generator that requires a Starter Generator Control Unit (SGCU) to provide excitation power to drive the rotor to rotate, and drives an Auxiliary Starter Generator (ASG) to power the aircraft after the APU reaches a specified speed. Therefore, the excitation power cable, the generator output feeder line and the generator voltage regulation point detection line are required to be designed for realizing the function of starting the power generation system. The three cable designs of the conventional starter-generator system that perform different functions are independent of each other. The existing power supply and detection circuit design of the airplane starting power generation system needs to arrange longer cables along the airplane body, so that the weight of the airplane is increased, and the economical efficiency of airplane operation is reduced.

Accordingly, there is a need in the art for techniques that effectively reduce the amount of cabling required on an aircraft, shorten the overall length of the cabling, reduce the weight of the aircraft, and reduce operational costs.

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, the present invention aims to reduce the number and length of aircraft starting power system cables, thereby reducing the overall weight of the starting power system cables, achieving a reduction in operating costs, and improving the economy of the aircraft.

According to a first aspect of the present invention, there is provided a cable time-sharing multiplexing circuit for an aircraft starting power generation system, which may include a starter generator control unit SGCU, an auxiliary starter generator ASG, a distribution switchboard box RDP, which 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 time-division multiplex the first and second sets of cables according to a cable function and a usage phase of the aircraft starting power generation system, wherein during a start phase of the aircraft starting power 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; wherein during a power generation phase of the aircraft starting power generation system, the generator output feed line comprises a second set of cables from ASG to RDP, and the voltage detection line comprises a first set of cables from SGCU to RDP.

In one embodiment of the first aspect, the first set of wires and the second set of wires may be connected via posts at the input end of the RDP.

In one embodiment of the first aspect, the SGCU may comprise 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 to the excitation supply module during a start-up phase, wherein the control unit may be configured to connect the output of the SGCU to 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 the input of the RDP with the power supply module.

According to a second aspect of the invention, there is provided a method for time-sharing multiplexing of cables for an aircraft starting power system, which may comprise a starter generator control unit SGCU, an auxiliary starter generator ASG, a distribution switchboard box RDP, which may comprise: connecting the SGCU with the RDP using a first set of cables; connecting the RDP with the ASG using a second set of cables; the first group of cables and the second group of cables are subjected to time-sharing multiplexing according to the cable functions and the use phases of the aircraft starting power generation system; wherein during a start-up phase of the aircraft starting power generation system, the SGCU field line comprises 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 a power generation phase of the aircraft starting power generation system, the generator output feed line comprises a second set of cables from ASG to RDP, and the voltage detection line comprises a first set of cables from SGCU to RDP.

In one embodiment of the second aspect, the first set of wires and the second set of wires may be connected via lugs at the input end of the RDP.

In one embodiment of the second aspect, the SGCU may comprise an excitation power supply module and a voltage detection module.

In one embodiment of the second aspect, the output of the SGCU may be coupled to the excitation supply module during a startup phase, wherein the output of the SGCU may be coupled to the voltage detection module during a power generation phase.

In one embodiment of the second aspect, the RDP may comprise a power supply module, wherein the input of the RDP may be connected to the power supply module during the power generation phase.

By adopting the technical scheme provided by the invention, the system complexity can be reduced and the reliability can be improved. In addition, the weight of the cable of the narrow-body passenger plane is reduced by about 7-10kg, and the weight of the cable of the wide-body 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 accompanying 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 some 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-sharing multiplexing circuit for an aircraft starting power generation system, according to one embodiment of the invention.

Fig. 3 illustrates a simplified schematic diagram of an SGCU time-sharing multiplexing circuit design architecture according to one embodiment of the invention.

Fig. 4 illustrates a simplified schematic diagram of an RDP time-division multiplexing circuit design architecture according to one embodiment of the invention.

FIG. 5 illustrates a flow diagram of a method for time-sharing multiplexing of cables for 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 present invention will be described in detail below with reference to the attached drawings, and the features of the present invention will be further apparent from the following detailed description.

As mentioned above, in conventional aircraft starting power generation system cabling designs, cables for different functions are typically independent of each other, each disposed 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 panel RDP 130. Typically, three starting power cables may be used to connect the SGCU 110 to the ASG120 to provide excitation power to drive the rotor to rotate during the start-up phase of the aircraft starting power generation system 100. Furthermore, the RDP 130 is connected to the ASG120 using six cables as generator output feeders to provide the electrical power generated by the ASG120 during the power generation phase of the aircraft starting power generation system 100. In order to detect the voltage, a voltage detection line not shown in fig. 1 needs to be provided. Thus, a plurality of cables having different functions and being independent of each other need to be arranged along the fuselage, thereby bringing more weight and being not beneficial to the economy of the aircraft.

The invention discloses a design of a time-sharing multiplexing circuit for cables of an airplane starting power generation system, which carries out time-sharing multiplexing on cables with different functions according to the functions and the use stages of the cables. By reducing the number and length of cables, the total weight of the starting power generation system cable is reduced, the reduction of operation cost is realized, and the economy of the airplane is improved.

The invention adopts the following circuit design scheme for realizing the aim of the invention:

because in the start-up state, the ASG does not need to provide AC power to the RDP; meanwhile, in the power generation state, the SGCU does not need to provide starting power for the ASG, so that the SGCU-RDP and RDP-ASG section conductors are time-division multiplexed. And the connection of the cable is realized by using a binding post at the input end of the RDP. During a start-up phase, the SGCU excitation line includes an SGCU to RDP section and an RDP to ASG section; in the power generation stage, the feeder line is from ASG to RDP, and the voltage detection line is from SGCU to RDP, so that time-sharing multiplexing of the cable is realized.

Fig. 2 illustrates a schematic diagram of a cable time-sharing multiplexing circuit for an aircraft starting power generation system 200, according to one embodiment of the invention. Aircraft starting power generation system 200 may include a starter generator control unit SGCU 210, an auxiliary starter generator ASG 220, and a distribution panel 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. For example, the first set of cables 240 may include a first cable connecting the first port of the SGCU 210 to the a2 port of the RDP 230, a second cable connecting the second port of the SGCU 210 to the B2 port of the 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 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 line a phase of ASG 220, a fifth cable connecting the B2 port of RDP 230 to the power line B phase of ASG 220, a sixth cable connecting the C2 port of RDP 230 to the power line C phase of ASG 220, a seventh cable connecting the a1 port of RDP 230 to the power line a phase of ASG 220, an eighth cable connecting the B1 port of RDP 230 to the power line B phase of ASG 220, and a ninth cable connecting the C1 port of RDP 230 to the power line C phase of ASG 220. First set of cables 240 and second set of cables 250 may be interconnected by posts at the input of RDP 230.

The cable time-sharing multiplexing circuit may include a control unit, not shown in fig. 2, that may be configured to time-share the first set of cables 240 and the second set of cables 250 according to a cable function and a usage phase of the aircraft starting power generation system 200, wherein during a start phase of the aircraft starting power generation system, the SGCU excitation line includes the first set of cables 240 of the SGCU 210 to RDP 230 and the second set of cables 250 of the RDP 230 to ASG 220, and during a power generation phase of the aircraft starting power generation system, the generator output feed line includes the second set of cables 250 of the ASG 220 to RDP 230, and the voltage detection line includes the first set of cables 240 of the SGCU 210 to RDP 230. Thus, time-sharing multiplexing of cables is realized.

Fig. 3 illustrates a simplified schematic diagram of an SGCU time-sharing multiplexing circuit design architecture according to one embodiment of the 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 the aircraft starting power generation system. The switching of the switch 330 may be controlled by a control unit. For example, during a startup phase of the aircraft starting power generation system, the control unit may switch 330 to connect with the excitation power module 310 such that the SGCU output connects with the excitation power module 310 to deliver excitation power. During the power 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 to connect the SGCU output 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 according to one embodiment of the invention. The RDP shown in fig. 4 may include a power module 410 and a switch 420. The power module 410 may be configured to receive and distribute the generator output power to various electrical devices (e.g., loads) during a power generation phase of the aircraft starting power generation system. In the starting stage, the RDP input end is in a high-resistance state, and the excitation 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 is equal to the detection circuit in potential. The switching of the switch 420 may be controlled by a control unit. For example, during the power generation phase of an aircraft starting the 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 diagram of a method 500 for time-sharing multiplexing of cables for an aircraft starting power generation system, according to 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 RDP. For example, referring to fig. 2, a first set of cables 240 is used to connect the SGCU 210 with the 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-division 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 in a starting phase of the aircraft starting power generation system, the SGCU excitation line comprises the first set of cables from the SGCU to the RDP and the second set of cables from the RDP to the ASG; wherein during a power generation phase of the aircraft starting power generation system, the generator output feed line comprises a second set of cables from ASG to RDP, and the voltage detection line comprises a first set of cables from SGCU to RDP. For example, referring to fig. 2, during a start-up phase of an aircraft starting power generation system, the SGCU field line includes a first set of cables 240 from SGCU 210 to RDP 230 and a second set of cables 250 from RDP 230 to ASG 220; wherein during the power generation phase of the aircraft starting power generation system, the generator output feed line comprises a second set of cables 250 from ASG 220 to RDP 230 and the voltage detection line comprises a first set of cables 240 from SGCU 210 to RDP 230.

In one embodiment of method 500, the first set of wires and the second set of wires may be connected via lugs at the input end of the RDP.

In one embodiment of method 500, the SGCU may include an excitation power supply module and a voltage detection module.

In one embodiment of method 500, the output of the SGCU may be coupled to the excitation power supply module during a startup phase, wherein the output of the SGCU may be coupled to the voltage detection module during a power generation phase.

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 understood that the design of the present invention may be applied to other circuits requiring power generation to be initiated.

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 comprise elements 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, 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 deviceDevice 606 can be any type of device that can input information into a computing device and can 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 can present information and may include, but is not limited to, a display, speakers, a video/audio output terminal, a vibrator, and/or a printer. The control device 600 may also include, or be connected with, a non-transitory storage device 610, which 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 storage, floppy disks, hard disks, magnetic tape, or any other magnetic medium, optical disks or any other optical medium, ROMs (read only memories), RAMs (random access memories), cache memories, 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 above-described methods and steps. 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 devices and/or networks, and may include, but is not limited to, a modem, a network card, an infrared communication device, such as bluetooth^TMDevices, 1302.11 devices, WiFi devices, WiMax devices, wireless communication devices such as cellular communication facilities and/or chipsets, and so forth.

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.

The control device 600 may also include a working memory 614, which working memory 614 may be any type of working memory that can store instructions and/or data useful to 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 be located in 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 methods and steps described above may be included in one or more application programs 618. Executable code or source code for the instructions of the software elements may be stored in a non-transitory computer-readable storage medium (such as storage device 610 described above) and may be read into 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 is apparent to those skilled in the art that the present disclosure can be implemented by software having necessary hardware, or by hardware, firmware, and the like. Based on such understanding, embodiments of the present disclosure may be implemented partially 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 the 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 or a portion thereof according to a respective embodiment of the present disclosure.

Throughout the specification, reference has been made to "one example" or "an example" meaning that a particular described feature, structure or characteristic is included in at least one example. Thus, use of such phrases may refer to 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 can be practiced without one or more of the specific details, or with other methods, resources, materials, and so forth. In other instances, well-known structures, resources, or operations are not shown or described in detail to avoid obscuring aspects of the examples.

While examples and applications have been illustrated and described, it is to be understood that these examples are not limited to the precise configuration 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.