Aircraft ground service bus architecture, power supply system and operation method

Abstract

Disclosed are an aircraft ground service bus architecture, a power supply system, and an operating method. The aircraft ground service bus architecture includes: a first AC bus; an autotransformer connected to the first AC bus via a first contactor; a second AC bus connected to the autotransformer via a second contactor and to an external power source via a third contactor; a second AC ground service bus connected to the autotransformer via a fourth contactor and to the external power source via a fifth contactor; an external power ground service switch, a normally closed auxiliary contact of which is connected to a drive circuit of the second contactor and the third contactor, and the drive circuits of the second contactor and the third contactor are disconnected when external power ground service is enabled; and a controller that closes the first contactor, the fourth contactor, and the fifth contactor to energize the second AC ground service bus when the external power ground service is enabled.

Description

Technical Field

[0001] Various aspects of the present disclosure relate to the technical field of aircraft power system architecture, and more particularly to an aircraft power system ground service bus architecture, a power system, and an operating method. Background Art

[0002] The aircraft power system's ground service bus typically consists of a 115V three-phase AC ground service bus and a 28V DC ground service bus. These buses primarily power 115V three-phase AC and 28V DC loads required to perform ground service functions in various aircraft power system modes. Typical loads include cabin lighting, cockpit lighting, lavatory lighting, and cargo door actuators. Aircraft currently operating on airlines use 230V three-phase AC as their primary power supply. Autotransformers (ATUs) convert 230V to 115V, and transformer-rectifier units (TRUs) convert 230V to 28V DC.

[0003] In the existing technology, in order to realize the ground service mode, some models use the load management function. In the ground service mode, power is supplied to the relevant electrical loads by controlling the electronic circuit breaker, thereby achieving the effect of a virtual ground service bus; some models combine the two implementation methods of busbar physical design and load management function, and supply power to the relevant electrical loads by controlling the contactor and electronic circuit breaker.

[0004] The first method mentioned above powers both the 115V three-phase AC busbar and the 28V DC busbar, while the second method powers only the 115V three-phase AC busbar. Consequently, when 115V three-phase AC loads and 28V DC loads are powered using a thermal circuit breaker, power may be supplied to devices that do not require ground service functions. This prevents the goal of only powering loads that require ground service functions. Summary of the Invention

[0005] The present invention is directed to providing an aircraft ground service bus architecture, comprising: a first AC bus; an autotransformer connected to the first AC bus via a first contactor; a second AC bus connected to the autotransformer via a second contactor and to an external power source via a third contactor; a second AC ground service bus connected to the autotransformer via a fourth contactor and to the external power source via a fifth contactor; an external power ground service switch, a normally closed auxiliary contact of which is connected to a drive circuit of the second contactor and the third contactor, and the drive circuits of the second contactor and the third contactor are disconnected when external power ground service is enabled; and a controller that closes the first contactor, the fourth contactor, and the fifth contactor to energize the second AC ground service bus when the external power ground service is enabled. The aircraft ground service bus architecture may further include: a transformer-rectifier connected to the first AC bus via a sixth contactor; a third DC ground service bus connected to the transformer-rectifier via a seventh contactor; and a third DC bus connected to the transformer-rectifier via an eighth contactor; wherein the normally closed auxiliary contact of the external power service switch is also connected to a drive circuit of the eighth contactor, and the eighth contactor is opened when the external power ground service is enabled, and wherein the controller also closes the sixth contactor and the seventh contactor to energize the third DC ground service bus when the external power ground service is enabled.

[0006] The present invention also provides an operating method for the aircraft ground service bus architecture as described above, comprising: using the controller to disconnect the electrical load control contactor connected to the first AC bus; and using the external power ground service switch to disconnect the second contactor, the third contactor and the eighth contactor; and using the controller to close the first contactor, the fourth contactor, the fifth contactor, the sixth contactor and the seventh contactor to power on the second AC ground service bus and the third DC ground service bus.

[0007] The present invention also provides an aircraft power supply system including the aircraft ground service busbar architecture described above.

[0008] The present invention realizes that when entering the ground service mode, power is only supplied to the power loads that need to perform the ground service function. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 is a block diagram illustrating an aircraft ground services bus architecture according to an aspect of the present invention.

[0010] Figure 2 is a block diagram illustrating an aircraft ground services bus architecture according to an aspect of the present invention.

[0011] Figure 3 is a diagram illustrating an aircraft ground services bus architecture according to an aspect of the present invention.

[0012] Figure 4 It shows that according to the present invention Figure 3 Illustration of the external power ground service mode of the aircraft ground service bus architecture.

[0013] Figure 5 It shows that according to the present invention Figure 3 Illustration of the normal power supply mode of the external power supply of the aircraft ground service bus architecture.

[0014] Figure 6 is a flowchart of the operation of an aircraft ground service bus architecture according to an aspect of the present invention. DETAILED DESCRIPTION

[0015] In order to understand in detail the features of the present disclosure set forth above, a more particular description of the content briefly summarized above may be obtained with reference to various aspects, some of which are illustrated in the accompanying drawings. It should be noted, however, that the accompanying drawings illustrate only certain typical aspects of the present disclosure and are not to be considered limiting of its scope, as the description may admit to other equally effective aspects. The same reference numerals in different drawings may identify the same or similar elements.

[0016] One aspect of the present invention provides a ground service bus architecture for an aircraft power system. In ground service mode (e.g., by pressing an external power ground service switch), the architecture controls corresponding contactors to ensure that only the AC ground service bus (e.g., a 115V three-phase AC ground service bus) is powered when the external power source is on, thereby powering only the AC loads required to perform ground service functions.

[0017] Figure 1A block diagram of an aircraft power system ground service bus architecture 100 according to one aspect of the present invention is illustrated. The aircraft power system ground service bus architecture 100 may include: a first AC bus 105; an autotransformer (ATU) 115 connected to the first AC bus 105 via a first contactor 110; a second AC bus 130 connected to the autotransformer 115 via a second contactor 120 and connected to an external power source via a third contactor 140; a second AC ground service bus 135 connected to the autotransformer 115 via a fourth contactor 125 and connected to an external power source via a fifth contactor. 145 is connected to the external power source; an external power ground service switch 150, the normally closed auxiliary contacts of the external power service switch 150 are connected to the drive circuits of the second contactor 120 and the third contactor 140, wherein when the external power ground service switch 150 is pressed, the drive circuits of the second contactor 120 and the third contactor 140 are disconnected due to loss of grounding; and a controller 155, which can close the first contactor 110, the fourth contactor 125 and the fifth contactor 145 when the external power ground service is enabled to power on the second AC ground service bus 135.

[0018] In one embodiment, the first AC bus 105 may be a 230V three-phase AC bus, the second AC bus 130 may be a 115V three-phase AC bus, and the second AC ground service bus 135 may be a 115V three-phase AC ground service bus.

[0019] In one embodiment, the first AC bus 105 may also be connected to N first AC electrical loads via N electrical load control contactors (ELCCs) to supply power to the first AC electrical loads, and the controller 155 may disconnect the electrical load control contactors before the external power service is enabled.

[0020] In one embodiment, after the external power ground service is enabled, the external power source supplies power to the second AC ground service bus 135 through the fifth contactor 145, and then the autotransformer 115 converts the second AC power (e.g., 115V three-phase AC power) into the first AC power (e.g., 230V three-phase AC power) and supplies power to the first AC bus 105 through the first contactor 110.

[0021] The ground service busbar 100 described in the present invention can realize that in the ground service mode, the power system only supplies power to the three-phase AC loads that need to perform ground service functions.

[0022] Figure 2A diagram illustrating an aircraft power system ground service bus architecture 200 according to one aspect of the present invention is shown. The aircraft power system ground service bus architecture 200 may include: a first AC bus 205; an autotransformer 215 connected to the first AC bus 205 via a first contactor 210; a second AC bus 230 connected to the autotransformer 215 via a second contactor 220 and connected to an external power source via a third contactor 240; and a second AC ground service bus 235 connected to the autotransformer 215 via a fourth contactor 225 and connected to an external power source via a fifth contactor 245. connected to the external power source; an external power ground service switch 250, the normally closed auxiliary contacts of the external power service switch 250 being connected to the drive circuits of the second contactor 220 and the third contactor 240, wherein when the external power ground service switch 250 is pressed, the drive circuits of the second contactor 220 and the third contactor 240 are disconnected due to loss of grounding; and a controller 255, the controller 255 can close the first contactor 210, the fourth contactor 225 and the fifth contactor 245 to energize the second AC ground service bus 235 when the external power ground service is enabled. The above components of the aircraft power system ground service bus architecture 200 may correspond to Figure 1 1 and 2. Corresponding components of the aircraft power system ground service bus architecture 100 in FIG.

[0023] The aircraft power system ground service bus architecture 200 may further include: a transformer-rectifier (TRU) 265, which is connected to the first AC bus 205 via a sixth contactor 260; a third DC ground service bus 280, which is connected to the transformer-rectifier 265 via a seventh contactor 270; and a third DC bus 285, which is connected to the transformer-rectifier 265 via an eighth contactor 275; wherein the normally closed auxiliary contact of the external power ground service switch 250 is also connected to the drive circuit of the eighth contactor 275, and when the external power ground service switch 250 is pressed, the drive circuit of the eighth contactor 275 is disconnected due to loss of ground, and wherein the controller 255 also closes the sixth contactor 260 and the seventh contactor 270 to energize the third DC ground service bus 280 when the external power ground service is enabled.

[0024] In one embodiment, the first AC bus 205 can be a 230V three-phase AC bus, the second AC bus 230 can be a 115V three-phase AC bus, the second AC ground service bus 235 can be a 115V three-phase AC ground service bus, the third DC ground service bus 280 can be a 28V DC ground service bus, and the third DC bus 285 can be a 28V DC bus.

[0025] In one embodiment, the first AC bus 205 can also be connected to N first AC electrical loads through N electrical load control contactors (ELCCs) to power the first AC electrical loads, and the controller 255 can disconnect these electrical load control contactors before the external power service is enabled.

[0026] In one embodiment, the external power source supplies power to the second AC ground service bus 235 through the fifth contactor 245 after the external power ground service is enabled, and then the autotransformer 215 converts the second AC power (e.g., 115V three-phase AC power) into the first AC power (e.g., 230V three-phase AC power) and supplies power to the first AC bus 205 through the first contactor 210.

[0027] In one embodiment, the transformer-rectifier 265 converts the first AC power (e.g., 230V three-phase AC power) into a third DC power (e.g., 28V DC power) after the external power ground service is enabled, and supplies power to the third DC bus 285 through the seventh contactor 270.

[0028] The ground service busbar 200 described in the present invention can realize that in the ground service mode, the power system only supplies power to the three-phase AC power loads and DC power loads that need to perform ground service functions.

[0029] The present invention provides a ground service bus architecture for an aircraft power system. In ground service mode (e.g., pressing an external power ground service switch), the architecture controls corresponding contactors to ensure that, when the external power source is powered on, only the AC ground service bus (e.g., a 115V three-phase AC ground service bus) and the DC ground service bus (e.g., a 28V DC ground service bus) are powered on, thereby supplying power only to electrical loads required to perform ground service functions.

[0030] Figure 3 A diagram illustrating an aircraft electrical power system ground service busbar architecture 300 is shown in accordance with an aspect of the present disclosure. Figure 3 The aircraft power system ground service bus architecture 300 may be Figure 2 An example of an aircraft power system ground service bus architecture 200 is shown in FIG. Figure 2The first AC bus can be a 230V three-phase AC bus, the second AC bus can be a 115V three-phase AC bus, the second AC ground service bus can be a 115V three-phase AC ground service bus, the third DC ground service bus can be a 28V DC ground service bus, and the third DC bus can be a 28V DC bus, where the first to eighth contactors can respectively correspond to the corresponding contactors in contactors 1 to 8 (for example, the first contactor 210 corresponds to contactor 2, the second contactor 220 corresponds to contactor 5, and so on).

[0031] like Figure 3 As shown, in models using 230V three-phase AC as the primary power supply, a 115V three-phase AC ground service bus and a 28V DC ground service bus are physically provided. When the external power ground service switch is pressed, entering ground service mode, only the 115V three-phase AC loads and 28V DC loads required to perform ground service functions are powered. Contactors 4, 5, and 7 are interconnected with the normally closed auxiliary contacts of the external power service switch, ensuring that the drive circuits of contactors 4, 5, and 7 are disconnected due to loss of ground when the external power ground service switch is pressed.

[0032] In one embodiment, the 230V three-phase AC busbar is further connected to N 230V loads through N electrical load control contactors (ELCCs), and the controller disconnects the electrical load control contactors before the external power service is enabled.

[0033] In one embodiment, the external power source supplies power to the 115V three-phase AC ground service busbar through the contactor 8 after the external power ground service is enabled.

[0034] In one embodiment, the 115V three-phase AC ground service busbar supplies power to the autotransformer through the contactor 6 after the external power ground service is enabled.

[0035] In one embodiment, the autotransformer converts 115V three-phase power to 230V three-phase power after the external power ground service is enabled, and supplies power to the 230V three-phase AC busbar through the contactor 2 .

[0036] In one embodiment, the 230V three-phase AC busbar supplies power to the transformer rectifier through contactor 1 after the external power ground service is enabled.

[0037] In one embodiment, the transformer rectifier converts 230V three-phase AC power into 28V DC power after the external power ground service is enabled, and supplies power to the 28V DC ground service busbar through the contactor 3 .

[0038] Figure 4and Figure 5 They are respectively Figure 3 Schematic diagram of the external power ground service mode and the external power normal power supply mode of the aircraft ground service bus architecture.

[0039] Figure 6 A flowchart illustrates a method 600 for operating an aircraft ground service bus architecture (e.g., aircraft power system ground service bus architecture 200 or 300) according to one aspect of the present invention. Before entering ground service mode, a controller first disconnects the electrical load control contactor (ELCC) used for load distribution on the 230V three-phase AC bus, thereby eliminating the need to power the loads connected to the 230V three-phase AC bus. The external power ground service switch is then pressed, and the controller automatically closes contactors 1, 2, 3, 6, and 8, while the drive coils of contactors 4, 5, and 7 are disconnected due to loss of ground. The grid status at this point is as follows:

[0040] 1. The external power supply supplies power to the 115V three-phase AC ground service busbar through contactor 8;

[0041] 2. The 115V three-phase AC ground service bus supplies power to the ATU through contactor 6;

[0042] 3. The ATU converts the 115V three-phase power supply to a 230V three-phase power supply, and then supplies power to the 230V three-phase AC busbar through contactor 2;

[0043] 4. The 230V three-phase AC busbar supplies power to the TRU through contactor 1;

[0044] 5. The TRU converts 230V three-phase AC power to 28V DC power, and then supplies power to the 28V DC ground service bus through contactor 3.

[0045] Because contactors 4, 5, and 7 are in the disconnected state, the 115V three-phase AC bus and the 28V DC bus are not powered. Although the 230V three-phase AC bus is powered, the ELCCs connected to the bus are all disconnected, so the corresponding 230V three-phase AC loads cannot be powered. At this time, only the 115V three-phase AC loads and 28V DC loads that need to perform ground service functions are powered on in the entire power grid.

[0046] The operations of the aircraft ground service bus architecture operating method 600 may be implemented by an aircraft power system or its components. In some embodiments, the aircraft power system may execute a code set for controlling functional elements of the system to perform the functions described below. Additionally or alternatively, the aircraft power system may use dedicated hardware to perform various aspects of the functions described below.

[0047] At block 605 , an electrical load control contactor connected to a first AC bus bar is opened using a controller.

[0048] At block 610 , the second contactor, the third contactor, and the eighth contactor are opened using an external power ground service switch.

[0049] At block 615 , the first contactor, the fourth contactor, the fifth contactor, the sixth contactor, and the seventh contactor are closed using the controller to energize the second AC ground service bus and the third DC ground service bus.

[0050] The present invention also provides an aircraft power supply system comprising any aircraft power supply system ground service busbar architecture as described above.

[0051] The various steps and modules of the methods and devices described above can be implemented in hardware, software, or a combination thereof. If implemented in hardware, the various illustrative steps, modules, and circuits described in conjunction with the present disclosure can be implemented or executed using a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other programmable logic components, hardware components, or any combination thereof. The general-purpose processor can be a processor, a microprocessor, a controller, a microcontroller, or a state machine, etc. If implemented in software, the various illustrative steps and modules described in conjunction with the present disclosure can be stored or transmitted as one or more instructions or codes on a computer-readable medium. The software modules that implement the various operations of the present disclosure can reside in a storage medium, such as RAM, flash memory, ROM, EPROM, EEPROM, registers, hard disk, removable disk, CD-ROM, cloud storage, etc. The storage medium can be coupled to a processor so that the processor can read and write information from / to the storage medium and execute the corresponding program modules to implement the various steps of the present disclosure. Moreover, software-based embodiments can be uploaded, downloaded, or remotely accessed via appropriate communication means. Such appropriate communication means include, for example, the Internet, the World Wide Web, an intranet, software applications, cables (including fiber optic cables), magnetic communications, electromagnetic communications (including RF, microwave and infrared communications), electronic communications, or other such communication means.

[0052] The numerical values given in the various embodiments are for illustrative purposes only and are not intended to limit the scope of the present invention. Furthermore, as a whole, the technical solution may include other components or steps not listed in the claims or the specification. Furthermore, a single name for a component does not preclude the use of other names for that component.

[0053] It should also be noted that these embodiments may be described as processes depicted as flow charts, flow diagrams, structure diagrams, or block diagrams. Although a flow chart may describe the operations as sequential processes, many of these operations can be performed in parallel or concurrently. In addition, the order of these operations can be rearranged.

[0054] The disclosed methods, devices, and systems should not be limited in any way. On the contrary, the present disclosure covers all novel and non-obvious features and aspects of the various disclosed embodiments (alone and in various combinations and subcombinations with each other). The disclosed methods, devices, and systems are not limited to any specific aspect or feature or combination thereof, nor do any disclosed embodiments require any one or more specific advantages or solutions to specific or all technical problems.

[0055] The present invention is not limited to the above-mentioned specific embodiments. The above-mentioned specific embodiments are merely illustrative and not restrictive. Under the guidance of the present invention, ordinary technicians in this field can make many forms without departing from the scope of protection of the present invention and the claims. These all fall within the scope of protection of the present invention.

Claims

1. An aircraft ground service busbar structure, characterized in that: include: first AC busbar; an autotransformer connected to the first AC busbar via a first contactor; a second AC bus bar connected to the autotransformer via a second contactor and to an external power source via a third contactor; a second AC ground service bus connected to the autotransformer via a fourth contactor and to the external power source via a fifth contactor; an external power ground service switch, wherein a normally closed auxiliary contact of the external power service switch is connected to a drive circuit of the second contactor and the third contactor, and the drive circuit of the second contactor and the third contactor is disconnected when the external power ground service is enabled; as well as A controller is configured to close the first contactor, the fourth contactor, and the fifth contactor to energize the second AC ground service busbar when the external power ground service is enabled.

2. The aircraft ground service busbar structure according to claim 1, wherein: Further including: a transformer rectifier, the transformer rectifier being connected to the first AC bus bar through a sixth contactor; a third DC ground service bus, the third DC ground service bus connected to the transformer rectifier via a seventh contactor; as well as a third DC bus bar, the third DC bus bar being connected to the transformer rectifier via an eighth contactor; The normally closed auxiliary contact of the external power service switch is also connected to the drive circuit of the eighth contactor, and the eighth contactor is opened when the external power ground service is enabled, and the controller also closes the sixth contactor and the seventh contactor to energize the third DC ground service bus when the external power ground service is enabled.

3. The aircraft ground service busbar structure according to claim 2, wherein: The first AC busbar is connected to a first AC electrical load through an electrical load control contactor, and the controller opens the electrical load control contactor before the external power service is enabled.

4. The aircraft ground service busbar structure according to claim 2, wherein: The first AC bus is a 230V three-phase AC bus, the second AC bus is a 115V three-phase AC bus, the second AC ground service bus is a 115V three-phase AC ground service bus, the third DC ground service bus is a 28V DC ground service bus, and the third DC bus is a 28V DC bus.

5. The aircraft ground service busbar structure according to claim 1, wherein: The external power source supplies power to the second AC ground service busbar through the fifth contactor after the external power ground service is enabled.

6. The aircraft ground service busbar structure according to claim 1, wherein: The autotransformer converts the second alternating current into the first alternating current after the external power ground service is enabled, and supplies power to the first AC busbar through the first contactor.

7. The aircraft ground service busbar structure according to claim 2, wherein: The transformer rectifier converts the first alternating current into a third direct current after the external power ground service is enabled, and supplies power to the third direct current ground service busbar through the seventh contactor.

8. An aircraft power supply system comprising the aircraft ground service busbar architecture according to any one of claims 1 to 7.

9. A method for operating the aircraft ground service bus architecture according to claim 3, comprising: disconnecting the electrical load control contactor connected to the first AC bus bar using the controller; as well as Disconnecting the second contactor, the third contactor, and the eighth contactor by using the external power ground service switch; as well as The first contactor, the fourth contactor, the fifth contactor, the sixth contactor, and the seventh contactor are closed using the controller to energize the second AC ground service bus and the third DC ground service bus.

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