CN116317084A

CN116317084A - Power supply system and power supply control method for aircraft

Info

Publication number: CN116317084A
Application number: CN202310202746.XA
Authority: CN
Inventors: 张苗欢; 徐健龙; 杨殿亮
Original assignee: Commercial Aircraft Corp of China Ltd
Current assignee: Commercial Aircraft Corp of China Ltd
Priority date: 2023-03-03
Filing date: 2023-03-03
Publication date: 2023-06-23

Abstract

A power supply system and a power supply control method for an aircraft are disclosed. The bus bar controller may determine whether a battery of the power system is placed in an emergency power mode. When the battery is not placed in the emergency power mode, the bus bar controller detects a control signal that causes the power supply system to enter the electrical maintenance mode. In the electrical maintenance mode, the conversion bus is connected to the battery such that the battery supplies power to the circuit breaker controller and the first avionics display via the conversion bus, wherein the circuit breaker controller and the first avionics display are operable for circuit breaker maintenance operations. In the electrical maintenance mode, other dc emergency bus bars coupled to the battery may be disconnected from the battery, eliminating the need to power devices connected to the dc emergency bus bars, reducing power load and power usage.

Description

Power supply system and power supply control method for aircraft

Technical Field

The invention relates to the field of aircrafts, in particular to a power supply system and a power supply control method for an aircraft.

Background

For an aircraft employing electronic circuit breakers, the thermal circuit breaker cannot be pulled out or pushed in on the breaker panel after the aircraft is powered down, as in conventional thermal circuit breakers, but rather manual setting (closing or opening) of the electronic circuit breaker is required on the cockpit display.

At present, the inspection and setting of the electronic circuit breaker are realized on a circuit breaker state and a control page, each circuit breaker state and a circuit breaker state file displayed on an interface of a display system are manually inspected through a machine service/unit, and if inconsistent circuit breakers exist, the circuit breakers need to be manually set to a correct state.

The electronic circuit breaker is typically set in a battery power mode or an off-ground power mode. If there is no external ground power source, the battery mode is used. Since all the battery bus bars and the emergency bus bar equipment can be supplied with power in the battery mode, a large amount of battery electric quantity is used, and the availability and the working efficiency of the battery in subsequent test flight and air line operation are greatly affected.

Accordingly, there is a need in the art for an improved power supply system and power control method for an aircraft.

Disclosure of Invention

The present invention thus proposes an improved power supply system and power supply control method for an aircraft. The invention can be applied to the design of an aircraft power supply system architecture, in particular to a power supply control architecture and a method for maintaining an electronic circuit breaker. In one implementation, the invention may be used in the design of a power system electronic circuit breaker floor maintenance mode.

In one embodiment according to the present invention, there is provided a power supply system for an aircraft, comprising: a battery and a dc emergency bus bar; a switching bus bar connected to the circuit breaker controller and the first avionics display; and a bus bar controller configured to determine whether the battery is placed in an emergency power mode in which the battery supplies power to the direct current emergency bus bar; when the battery is not placed in the emergency power mode, the bus bar controller detects a control signal that causes the power system to enter an electrical maintenance mode, and in response to detecting the control signal, the bus bar controller connects the transition bus bar to the battery to cause the power system to enter an electrical maintenance mode, wherein the battery supplies power to the circuit breaker controller and the first avionics display via the transition bus bar, the circuit breaker controller and the first avionics display being operable in the electrical maintenance mode for a circuit breaker maintenance operation.

In an aspect, when the battery is placed in an emergency power mode, the dc emergency bus bar is connected to the battery, the transition bus bar is disconnected from the battery, and the transition bus bar is connected to the dc emergency bus bar such that the battery powers the circuit breaker controller and the second avionics display via the dc emergency bus bar, and the dc emergency bus bar powers the transition bus bar, the transition bus bar powers the circuit breaker controller and the first avionics display, wherein the circuit breaker controller and the first avionics display are operable in the emergency power mode for circuit breaker maintenance operations.

In an aspect, the circuit breaker maintenance operation includes one or more of: the circuit breaker controller is configured to receive status information associated with a circuit breaker in a power system; the first avionics display is configured to display status information of the circuit breaker; the first avionics display is configured to receive setting information associated with the circuit breaker; or the circuit breaker controller configures the circuit breaker according to the setting information.

In one aspect, the power supply system further comprises: an electrical maintenance mode switch, wherein the bus bar controller detects a control signal that causes the power supply system to enter an electrical maintenance mode by detecting a state of the electrical maintenance mode switch.

In one aspect, the power supply system further comprises: an avionics processing system connected to the direct current emergency bus and the conversion bus, wherein the avionics processing system is communicatively coupled to the circuit breaker controller and the first avionics display and performs processing associated with the circuit breaker maintenance operation.

In an aspect, the bus bar controller causes the power supply system to enter an electrical maintenance mode in response to detecting the control signal when one or more of the following conditions are met: the aircraft is on the ground; the aircraft is not powered by a generator or an external power source.

In one aspect, the power supply system further comprises: a second battery and a second dc emergency bus bar, wherein when the second battery is in an emergency power mode, the second battery is connected to the second dc emergency bus bar and powers a second circuit breaker controller and a third avionics display via the second dc emergency bus bar, wherein when the battery and the second battery are not placed in an emergency power mode, the bus bar controller connects the transition bus bar to the battery and/or the second battery, the battery and/or the second battery powers the circuit breaker controller, the second circuit breaker controller, and the first avionics display via the transition bus bar in response to detecting the control signal that causes the power system to enter an electrical maintenance mode.

In another embodiment according to the invention, an aircraft is provided comprising a power supply system as described in any one of the above.

In another embodiment according to the present invention, there is provided a power supply control method for an aircraft power supply system, including: determining whether a battery of the power system is placed in an emergency power mode in which the battery supplies power to a direct current emergency bus; detecting a control signal that causes the power system to enter an electrical maintenance mode when the battery is not placed in the emergency power mode; in response to detecting the control signal, a transition bus is connected to the battery to cause the power system to enter an electrical maintenance mode, wherein the battery supplies power to a circuit breaker controller and a first avionics display via the transition bus, the circuit breaker controller and the first avionics display being operable in the electrical maintenance mode for a circuit breaker maintenance operation.

In one aspect, the power supply control method further includes: when the battery is placed in an emergency power mode, the direct current emergency bus bar is connected to the battery, the transition bus bar is disconnected from the battery, and the transition bus bar is connected to the direct current emergency bus bar such that the battery powers the circuit breaker controller and the second avionics display via the direct current emergency bus bar, and the direct current emergency bus bar powers the transition bus bar, which powers the circuit breaker controller and the first avionics display, wherein the circuit breaker controller and the first avionics display are operable for circuit breaker maintenance operations in the emergency power mode.

In one aspect, the power supply control method further includes: a control signal to cause the power supply system to enter an electrical maintenance mode is detected by detecting a state of an electrical maintenance mode switch.

In one aspect, the power supply control method further includes: processing associated with the circuit breaker maintenance operation is performed with an avionics processing system connected to the direct current emergency bus and the conversion bus.

In an aspect, the power supply control method further comprises entering an electrical maintenance mode in response to detecting the control signal when one or more of the following conditions are met: the aircraft is on the ground; the aircraft is not powered by a generator or an external power source.

In one aspect, the power supply control method further includes: when a second storage battery of the power supply system is in an emergency power supply mode, the second storage battery supplies power to a second breaker controller and a third avionics display through a second direct-current emergency bus bar; and when the battery and the second battery are not placed in an emergency power mode, in response to detecting the control signal that causes the power system to enter an electrical maintenance mode, connecting the transition bus to the battery and/or the second battery, the battery and/or the second battery powering the circuit breaker controller, the second circuit breaker controller, and the first avionics display via the transition bus.

Drawings

FIG. 1 is a schematic block diagram of a power supply system for an aircraft in accordance with one embodiment of the invention.

FIG. 2 is a schematic diagram of one implementation of a power supply system for an aircraft in accordance with one embodiment of the invention.

Fig. 3 is a state diagram of a power supply system for an aircraft according to one embodiment of the invention.

Fig. 4 is a state diagram of a power supply system for an aircraft according to another embodiment of the invention.

Fig. 5 is a flow chart of a power control method for an aircraft power system according to one embodiment of the invention.

Detailed Description

The invention will be further described with reference to specific examples and figures, which should not be construed as limiting the scope of the invention.

The present invention proposes an improved power supply system and method for an aircraft. The bus bar controller may determine whether a battery of the power system is placed in an emergency power mode. When the battery is not placed in the emergency power mode, the bus bar controller detects a control signal that causes the power supply system to enter the electrical maintenance mode. In the electrical maintenance mode, the conversion bus is connected to the battery such that the battery supplies power to the circuit breaker controller and the first avionics display via the conversion bus, wherein the circuit breaker controller and the first avionics display are operable for circuit breaker maintenance operations. In the electrical maintenance mode, other dc emergency bus bars coupled to the battery may be disconnected from the battery, eliminating the need to power devices connected to the dc emergency bus bars, reducing power load and power usage.

The ground maintenance power supply mode can realize the function of maintaining the electronic circuit breaker by supplying power to bus bars/equipment required by the maintenance of the electronic circuit breaker under the condition of reducing power supply load and power consumption as much as possible and ensuring that a storage battery is used for supplying power on the ground.

Fig. 1 is a schematic block diagram of a power supply system 100 for an aircraft in accordance with one embodiment of the invention. Power system 100 is used to power various on-board powered devices. The aircraft cockpit may include a plurality of avionics displays, such as first avionics display 123 and second avionics display 116, each for displaying a variety of information, such as flight information, equipment information, communications information, and the like. The first avionics display 123 and the second avionics display 116 may be separate displays. The data, signals for each avionics display may be provided by avionics processing system 130 and the avionics display software may reside in the central processor of the avionics processing system.

The aircraft power system may be over-current protected using one or more electronic circuit breakers (not shown). One or more circuit breaker controllers 122 may receive status information associated with circuit breakers in the power system and/or may set the operational mode of each circuit breaker. The first avionics display 123 may be configured to provide an operating system interface that may display individual breaker status and may set operating buttons, and the crew/crew may set each breaker status and breaker status file displayed on the interface. By way of example and not limitation, display and control of electronic circuit breakers may be provided in a circuit breaker indication and control interface (CBIC) in an avionics display. When referring herein to powering an avionics display and the avionics display is operating, it is meant that the avionics processing system (or processor) associated with the avionics display is also powered and operating properly.

During flight, the onboard equipment can be powered by an onboard generator, wherein the ac power provided by the generator can be converted to dc power by a transformer rectifier. For example, the generator may power the first and second avionics displays 123 and 116, the avionics processing system 130, the circuit breaker controller 122, and other electronic devices via direct current bus bars (not shown) and optional conversion bus bars (not shown). In case no generator is available, emergency power will be supplied by means of the battery 110 via the dc emergency bus 115 and the conversion bus 121. In the air, if the engine/generator is lost, an emergency mode is entered, and emergency power is supplied by the battery. In one example, the direct current bus bar and the conversion bus bar used by the generator and the direct current emergency bus bar 115 and the conversion bus bar 121 used by the battery 110 may be separate bus bars. In another example, the direct current bus bar and conversion bus bar used by the generator and the direct current emergency bus bar 115 and conversion bus bar 121 used by the battery 110 may be common or partially common bus bars.

When the aircraft is on the ground, the on-board generator, if not operating, may employ an off-ground power supply to power on-board equipment via the dc bus and associated conversion bus. The off-ground power supply and the on-board engine may share the same dc bus and conversion bus, or different buses may be employed. If the electronic circuit breaker is arranged in the ground external power supply mode, the ground external power supply can supply power to various electric equipment through the direct current bus bar and the conversion bus bar, so that the electric equipment can work normally.

If there is no off-ground power source, a battery mode is required to supply power to various consumers through the dc emergency bus 115 and the switching bus 121, which will use a large amount of battery power, greatly affecting the availability and operating efficiency of the battery in subsequent test flights and on-line operations. For example, in the case of full power in battery mode, the onboard dc emergency bus and single-phase ac bus will be powered by the battery, which typically has a power load of around 200. In this mode, the battery will be depleted for about 20-30 minutes due to the large load and the large power consumption.

The invention provides a power supply system architecture and a power supply control method for an aircraft, which can be used for efficiently maintaining an electronic circuit breaker of a power supply system.

Referring to fig. 1, a battery 110 of a power supply system 100 is coupled to a dc emergency bus 115 via a first contactor 111 and to a conversion bus 121 via a second contactor 112. The circuit breaker controller 122 and avionics processing system 130 may each be connected to both the dc emergency bus 115 and the transition bus 121. The first avionics display 123 may be connected to the switching bus 121 and the second avionics display 116 may be connected to the dc emergency bus 115. Further, the conversion bus 121 may be coupled to the dc emergency bus 115 via the third contactor 113. The first, second and

third contactors

111, 112 and 113 may be controlled by the bus bar controller 120 to be turned on or off accordingly. While contactors are described herein for switching on and off various components, it should be understood that other types of switching devices may be employed to perform the switching on and off operations, such as mechanical switches, transistors, circuit breakers, relays, and the like.

In the case of inspection before take-off, equipment maintenance, and the like, it is necessary to enter electrical maintenance for the power supply system 100, for example, to detect whether or not there is a failure in the power supply system 100, to make various settings for the power supply system 100, and the like. In the case where the power supply system 100 has sufficient power, for example, an external power supply, electrical maintenance may be performed with the power supply system 100 fully powered. According to an embodiment of the present invention, in order to perform electrical maintenance using the storage battery 110 without an external power source, an electrical maintenance mode is provided in order to efficiently perform maintenance of the power system electronic circuit breaker.

In one embodiment, if battery 110 is used for emergency power, such as an associated battery emergency power switch is on, battery 110 will be used to power dc emergency bus 115 and all powered devices connected thereto. Thus, when the battery 110 is in the emergency power mode, the bus bar controller 120 opens the second contactor 112 and closes the first and

third contactors

111 and 113, such that the battery 110 supplies power to the avionics processing system 130, the circuit breaker controller 122, and the second avionics display 116 via the dc emergency bus bar 115, and the dc emergency bus bar 115 supplies power to the transition bus bar 121 via the third contactor 113, the transition bus bar 121 supplying power to the avionics processing system 130, the circuit breaker controller 122, and the first avionics display 123. Thus, in the battery emergency power mode, all of the electrical devices connected to the dc emergency bus 115 and the switching bus 121 will be in operation. The avionics processing system 130, the circuit breaker controller 122, and the first avionics display 123 may each receive multiple power supplies and may automatically select one power supply to ensure proper operation with only one power supply. For example, if the dc emergency bus 115 and the transition bus 121 together supply power to the circuit breaker controller 122, the circuit breaker controller 122 may receive power from one of them.

In accordance with one embodiment of the present invention, if the battery 110 is not used for emergency power without an external power source, the bus bar controller 120 may detect whether a control signal for causing the power system 100 to enter an electrical maintenance mode is present. The bus bar controller 120 may be in continuous operation, such as powered by the battery 110 or by other batteries. By detecting the state of the emergency power switch of the battery 110 or detecting whether power is supplied to the dc emergency bus 115, it is possible to determine whether the battery 110 is used for emergency power. The bus bar controller 120 may detect whether a control signal for causing the power supply system 100 to enter an electrical maintenance mode exists when the battery 110 is not used for emergency power supply.

For example, the electrical maintenance mode switch 101 may be employed to provide the control signal. The electrical maintenance mode switch 101 may be located in the cockpit, or other suitable location. By way of example and not limitation, the electrical maintenance mode switch 101 may be a rotary switch, a toggle switch, a push switch, or the like. When an electrical maintenance mode is to be entered, the electrical maintenance mode switch 101 may be operated, for example, to dial it into an "electrical maintenance" gear. The bus bar controller 120 may be configured to detect a state of the electrical maintenance mode switch 101. In response to the electrical service mode switch 101 being in the electrical service gear, the bus bar controller 120 may cause the power system 100 to enter an electrical service mode. In another example, control signals may be provided in other ways to cause power system 100 to enter an electrical maintenance mode. For example, the bus bar controller 120 may receive a control signal (or an input signal) to put the power supply system 100 into an electrical maintenance mode from an operation panel or an electronic device. In response to receiving the control signal, the bus bar controller 120 may cause the power system 100 to enter an electrical maintenance mode.

In another aspect, the bus bar controller 120 may not have to separately detect whether the battery 110 is used for emergency power, wherein the control signal that causes the power system 100 to enter the electrical maintenance mode may be configured to be turned on only if the battery 110 is not used for emergency power, as described with reference to fig. 2. In this case, the bus bar controller 120 may directly put the power supply system 100 into the electric maintenance mode in response to receiving the control signal.

According to a further embodiment of the present invention, if a control signal for causing the power supply system 100 to enter the electric maintenance mode is received when the storage battery 110 is not used for emergency power supply, the bus bar controller 120 may also determine whether additional conditions for causing the power supply system 100 to enter the electric maintenance mode are satisfied. The determination of these additional conditions may be determined before, after, or concurrently with receiving a control signal that causes power system 100 to enter an electrical maintenance mode.

In an aspect, the bus bar controller 120 may detect whether the aircraft is on the ground or receive an indication from other electronic devices as to whether the aircraft is on the ground and allow entry into an electrical maintenance mode when the aircraft is on the ground. By way of example and not limitation, by detecting the state of the landing gear, it may be determined whether the aircraft is on the ground. In another aspect, the bus bar controller 120 may detect whether a generator or external power source is powered or receive an indication from other electronic devices as to whether a generator or external power source is powered. For example, by detecting whether there is power on the aircraft's direct current bus (which is connected to the generator or external power source), it can be determined whether there is power from the generator or external power source. The bus bar controller 120 may allow entry into an electrical maintenance mode when the aircraft is not powered by a generator or an external power source.

It is to be understood that the various additional conditions described above are by way of example only and are not limiting. In specific practice, more, fewer, or different conditions may be set to allow access to the electrical maintenance mode as desired and in particular, as required by aircraft safety requirements.

For example, in one embodiment, if the aircraft is on the ground and no external power source or generator power is being supplied, and the battery 110 is not being used for emergency power, the bus bar controller 120 may turn on/off the corresponding contactors in response to detecting a control signal that causes the power system 100 to enter the electrical maintenance mode, such that the power system 100 enters the electrical maintenance mode. Specifically, the bus bar controller 120 may turn on the second contactor 112 to cause the battery 110 to power the avionics processing system 130, the circuit breaker controller 122, and the first avionics display 123 via the transition bus bar 121. Meanwhile, the first contactor 111 and the third contactor 113 may be maintained in an open state, i.e., the battery 110 does not supply power to the direct current emergency bus bar 115. In some implementations, the first avionics display 123 may be connected to multiple avionics processing systems (e.g., flight control computers), while only one (or a small number of few) avionics processing systems 130 may be connected to the conversion bus 121 to provide the required electrical maintenance operation processing in the electrical maintenance mode.

Thus, in the electrical maintenance mode, the avionics processing system 130, the circuit breaker controller 122, and the first avionics display 123 may be in an operational state, while the second avionics display 116, and other devices connected to the dc emergency bus 115, may be inactive. The circuit breaker controller 122 and the first avionics display 123 may communicate through an avionics network (and/or avionics processing system 130). By way of example and not limitation, in the electrical maintenance mode, the circuit breaker controller 122 may receive status information associated with a circuit breaker in the power system and provide the status information to the first avionics display 123 for display. Further alternatively, the first avionics display 123 may display operational options and receive setup information associated with the circuit breaker. The first avionics display 123 may provide the setting information to the circuit breaker controller 122, and the circuit breaker controller 122 configures a corresponding circuit breaker according to the setting information.

As above, by providing power for the electrical service mode at the transition bus, rather than all dc emergency bus, a minimum configuration of the circuit breaker display interface (such as the circuit breaker controller 122 and the first avionics display 123) may be supported for power up, thereby reducing the amount of load and battery power in the ground service power mode.

FIG. 2 is a schematic diagram of one implementation of a power supply system for an aircraft in accordance with one embodiment of the invention. By way of example and not limitation, fig. 2 shows that the power system includes two batteries and a dc emergency bus bar connected to each battery separately. It should be appreciated that fewer or more batteries and corresponding direct current emergency bus bars may be included in a particular implementation.

As shown in fig. 2, battery 1 may be coupled via contactor K1 to a first dc emergency bus (e.g., a left dc important bus) that is connected to circuit breaker controller a and avionics display 2, among other devices. The battery 2 may be coupled via a contactor K2 to a second dc emergency bus (e.g., a right dc important bus) that is connected to the circuit breaker controller B and avionics display 3, among other devices.

The transition bus bar (e.g., transition bus bar 121,DC ESS TRANSFER BUS as described with reference to fig. 1) is coupled to the first dc emergency bus bar by contactor K3 and/or to the second dc emergency bus bar by contactor K4. In addition, the conversion bus bar is coupled to battery 1 via a contactor K5 and/or to battery 2 via a contactor K6. K5 and K6 may be examples of the second contactor 112 described with reference to fig. 1, respectively. The avionics display 1, the circuit breaker controller a and the circuit breaker controller B may be connected to the conversion bus bar.

By way of example and not limitation, avionics displays 1, 2, 3 may display some similar information, but may also display different information as desired. The various information displayed may have corresponding menu pages, such as pages for hydraulic, fuel, environmental, flight control, engine, etc. systems. The power information may be provided with 2 pages: jian Tuye (display of power supply information of a generator, a battery, a bus bar, etc.), and breaker pages (on-off control and status display of a breaker). The avionics displays 1, 2, 3 differ in the power bus bars, resulting in different displays that can operate in different power supply scenarios. For example, in the electrical maintenance mode, only avionics display 1 is required to operate, and avionics displays 2 and 3 are not required to operate.

When the battery 1 switch is ON, the battery 1 is placed in the emergency power mode, the bus bar controller causes K1, K3, and K4 to be closed, and 3 bus bars (i.e., first dc emergency bus bar, switching bus bar, second dc emergency bus bar,) are all powered by the battery 1.

When the battery 2 switch is ON, the battery 2 is placed in an emergency power mode, the bus bar controller causes K2, K3, and K4 to close, and 3 bus bars are all powered by the battery 2.

When both

battery

1 and 2 switches are ON, both

batteries

1 and 2 are placed in emergency power mode, the bus bar controller causes K1, K2, K3 and K4 to close, and 3 bus bars are commonly powered by

batteries

1 and 2.

When entering the ground electrical service mode without an OFF-ground power source, the battery emergency power switch is in an open position (e.g., battery 1 switch is in an OFF position, battery 2 switch is in an OFF position), closing the electrical service mode switch SW1 to a service mode position, at which time the ground return of the drive line of the electrical service mode relay K7 is on, the relay K7 will be closed, and a bus bar controller (e.g., bus bar controller 120 as described with reference to fig. 1) may detect a status signal of the electrical service mode switch SW1 confirming that the power system is to enter the electrical service mode. The bus bar controller will send a control command to close contactors K5 and K6 (or at least one of K5 and K6). Alternatively, the bus bar controller may transmit the electrical maintenance mode information to the circuit breaker controller a and the circuit breaker controller B, so that the circuit breaker controller a and the circuit breaker controller B operate in the electrical maintenance mode accordingly. With the battery emergency power supply switch in the open position, contactors K1, K2, K3 and K4 are open.

Thus, the power system enters an electrical maintenance mode and the switching bus is powered on (by battery 1 and/or battery 2), and the circuit breaker controller a, circuit breaker controller B and avionics display 1 (and avionics processing system, not shown) are powered by the switching bus and can operate normally, supporting checking and setting of electronic circuit breakers.

Although fig. 2 shows that the battery 1 switch, the battery 2 switch and the electrical maintenance mode switch SW1 cooperate such that the control signal to enter the electrical maintenance mode is only turned on if the

batteries

1 and 2 are not used for emergency power, the bus bar controller may thus simply determine to enter the electrical maintenance mode based on the control signal. It should be appreciated that in other implementations, the electrical maintenance mode or other modes (e.g., battery emergency power mode) may be entered through different schemes. For example, the bus bar controller may determine whether a condition for entering an electrical maintenance mode or a battery emergency power mode is satisfied and operate the contactors (e.g., K1-K6) accordingly in response to receiving a plurality of separate input signals or control signals, thereby causing the power supply system to enter the electrical maintenance mode or the battery emergency power mode.

Fig. 3 is a state diagram of a power supply system for an aircraft according to one embodiment of the invention. More specifically, fig. 3 shows the power supply system in an electrical maintenance mode. When the battery switches 1 and 2 are both in the OFF position, and K1 to K4 are both OFF, the

batteries

1 and 2 do not perform emergency power supply. When the battery switch is in the OFF position, if the electrical maintenance mode switch is in the ON position, the electrical maintenance mode may be entered if other requirements of the electrical maintenance mode are met (e.g., no generator or other power source is operating, ON ground).

As described with reference to fig. 2, in the electrical maintenance mode, at least one of K5 and K6 is closed, battery 1 and/or battery 2 supplies power to breaker controller a, breaker controller B and avionics display 1 via the switching bus bar, supporting checking and setting of the electronic breaker. For example, the circuit breaker controller a and/or the circuit breaker controller B receives status information associated with a circuit breaker in the power system and provides the status information to an avionics processing system (not shown) via the avionics network and is displayed by the avionics display 1. Further alternatively, the avionics display 1 may display operational options and receive setting information associated with the circuit breaker. The avionics display 1 may provide setting information (e.g., via an avionics processing system) to the circuit breaker controller a and/or the circuit breaker controller B, which configure the corresponding circuit breaker according to the setting information.

In the electrical maintenance mode, the contactors K1, K2, K3 and K4 are open, the first and second dc emergency bus bars are powered off, and the devices (e.g., avionic display 2, avionic display 3, etc.) connected to the first and second dc emergency bus bars, respectively, are also in a powered off state, enabling a power mode in which only the switching bus bars are powered, while the other bus bars are not powered, reducing the number of power bus bars, enabling a reduction in battery consumption.

Fig. 4 is a state diagram of a power supply system for an aircraft according to one embodiment of the invention. More specifically, fig. 4 shows the power supply system in a battery emergency power mode. As described with reference to fig. 2, in the battery emergency power mode (e.g., battery 1 switch is in the ON position and/or battery 2 switch is in the ON position), the electrical maintenance mode switch SW1 and relay K7 are in an open state, or even if the electrical maintenance mode switch SW1 is closed to the ON position, the bus bar controller does not put the power supply system into the electrical maintenance mode. Accordingly, the contactors K5 and K6 are in the open state.

As shown in fig. 4, when both the

batteries

1 and 2 are in the emergency power supply mode, the contactors K1, K2, K3, K4 are in the closed state, the contactors K5, K6 are in the open state, the battery 1 supplies power to the connected devices via the first direct current emergency bus bar and the switching bus bar, and the battery 2 supplies power to the connected devices via the second direct current emergency bus bar and the switching bus bar. Specifically, the battery 1 supplies power to a first direct current emergency bus (e.g., a left direct current important bus) that supplies power to the circuit breaker controller a and the avionics display 2, etc., via the closed contactor K1. The battery 2 supplies power to a second dc emergency bus (e.g., a right dc important bus) that supplies power to the circuit breaker controller B and the avionics display 3, etc., via the closed contactor K2. Furthermore, with the contactors K3 and/or K4 closed, the switching bus is supplied by the first and/or second dc emergency bus and supplies power to the avionics display 1, the circuit breaker controller a and the circuit breaker controller B.

When the battery 1 is in the emergency power supply mode and the battery 2 is not in the emergency power supply mode, the contactors K1, K3, K4 are in the closed state, the contactors K2, K5, K6 are in the open state, and the battery 1 supplies power to the connected devices via the first direct current emergency bus bar and the switching bus bar and the second direct current emergency bus bar. When the battery 2 is in the emergency power supply mode and the battery 1 is not in the emergency power supply mode, the contactors K2, K3, K4 are in the closed state, the contactors K1, K5, K6 are in the open state, and the battery 2 supplies power to the connected devices via the second direct current emergency bus bar, the switching bus bar, and the first direct current emergency bus bar.

That is, in the battery emergency power supply mode, all load devices connected to the first direct current emergency bus bar, the second direct current emergency bus bar, and the conversion bus bar are supplied with power, and can normally operate. For example, the associated avionics processing system may perform data processing and

avionics display

1, 2, 3 may display information and/or receive input accordingly.

For example, the breaker controller a and the breaker controller B may each be in communication with the avionic display 1, the avionic display 2, the avionic display 3. By way of example and not limitation, the circuit breaker controller a may receive status information of an associated circuit breaker and provide the status information to the avionics display 1, avionics display 2, and/or avionics display 3 for display. The circuit breaker controller B may receive status information of the associated circuit breaker and provide the status information to the avionics display 1, avionics display 2, and/or avionics display 3 for display.

In addition, avionics display 1, avionics display 2, and/or avionics display 3 may display operational options and receive setup information associated with the circuit breaker. For example, the CBIC of the avionics display may receive operational control commands of the set. The avionics displays 1-3 may provide setting information to the circuit breaker controller a and/or the circuit breaker controller B, which configures the corresponding circuit breaker (e.g., sets an operational mode of the circuit breaker, such as an on/off state) according to the setting information.

Thus, when the batteries 1 and/or 2 are in the emergency power mode, the avionic display 1 and the respective circuit breaker controllers and associated avionic processing systems will be powered and operable for electrical maintenance in the emergency power mode, such as detecting/displaying/setting circuit breaker status, etc.

Fig. 5 is a flow chart of a power control method 500 for an aircraft according to one embodiment of the invention. The power control method 500 may be performed by the power system 100 or components thereof as described with reference to fig. 1, or may be performed by a computer, processor, integrated circuit, or the like. The method 500 may be performed without generator power or without external power.

In step 501, it may be detected whether the power system is in a battery emergency power mode. When the battery is placed in the emergency power mode, a DC emergency bus may be connected to the battery, as described below with reference to steps 510-512.

If the power system is not in the battery emergency power mode, a control signal to place the power system into an electrical maintenance mode may be detected at step 502. For example, the state of an electrical maintenance mode switch may be detected. If a control signal to enter the electrical maintenance mode is not detected, the process may end.

If a control signal to enter an electrical maintenance mode is detected, the conversion bus bar may be connected to the battery at step 503 such that the battery supplies power to the conversion bus bar. For example, the switching bus bar may be connected to the circuit breaker controller and the first avionics display. In one embodiment, the electrical maintenance mode is entered in response to detecting the control signal when the aircraft is on the ground and not powered by the generator or the external power source and the battery is not placed in the emergency power mode. When the power supply system is in the electric maintenance mode, the direct-current emergency bus bar is disconnected from the storage battery.

Accordingly, at step 504, the conversion bus may provide power to the circuit breaker controller and the first avionics display.

Returning to step 501, when the battery is placed in an emergency power mode, the dc emergency bus is connected to the battery at step 510 such that the battery supplies power to the dc emergency bus. In the emergency power mode, the conversion bus bar is disconnected from the battery. In step 511, the dc emergency bus may power the device to which it is connected, such as a battery powering the circuit breaker controller and the second avionics display, etc., via the dc emergency bus. At step 512, the conversion bus may be connected to the dc emergency bus such that the dc emergency bus provides power to the conversion bus, which in turn provides power to the circuit breaker controller and the first avionics display.

In step 505, the circuit breaker controller and the first avionics display may operate, for example, to perform a circuit breaker maintenance operation. For example, the circuit breaker controller may receive status information associated with a circuit breaker in the power system, the first avionics display may be configured to display the status information of the circuit breaker, the first avionics display may be configured to receive setup information associated with the circuit breaker, and/or the circuit breaker controller may configure the circuit breaker based on the setup information, or the like. According to one embodiment, the processing associated with the breaker maintenance operation may be performed using an avionics processing system connected to the direct current emergency bus and the transition bus.

The invention provides a power supply control architecture and a method for maintaining an electronic circuit breaker, which can be specially used for ground maintenance power supply modes of the electronic circuit breaker of a power supply system. By arranging the power supply of the electric maintenance mode on the conversion bus bar, the minimum configuration power-up of the display interface of the circuit breaker and the normal operation of checking and arranging the electronic circuit breaker can be supported, and the direct current emergency bus bar is not needed to supply power, so that equipment connected with the direct current emergency bus bar can be in a power-off state, and the load quantity and the power consumption of a storage battery in the ground maintenance power supply mode are reduced.

The various steps and modules of the methods and apparatus described above may be implemented in hardware, software, or a combination thereof. If implemented in hardware, the various illustrative steps, modules, and circuits described in connection with this disclosure may be implemented or performed with 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 component, a hardware component, or any combination thereof. A general purpose processor may be a processor, microprocessor, controller, microcontroller, state machine, or the like. If implemented in software, the various illustrative steps, modules, described in connection with this disclosure may be stored on a computer readable medium or transmitted as one or more instructions or code. Software modules implementing various operations of the present disclosure may reside in storage media such as RAM, flash memory, ROM, EPROM, EEPROM, registers, hard disk, removable disk, CD-ROM, cloud storage, etc. A storage medium may be coupled to the processor such that the processor can read information from, and write information to, the storage medium, as well as execute corresponding program modules to implement the various steps of the present disclosure. Moreover, software-based embodiments may be uploaded, downloaded, or accessed remotely via suitable communication means. Such suitable communication means include, for example, the internet, world wide web, intranet, software applications, cable (including fiber optic cable), magnetic communications, electromagnetic communications (including RF, microwave and infrared communications), electronic communications, or other such communication means.

The numerical values given in the embodiments are only examples and are not intended to limit the scope of the present invention. The particular parameters of the various components may be suitably set as desired in accordance with specific practices and are not limited to the specific values set forth herein as examples. Furthermore, as an overall solution, there are other components or steps not listed by the claims or the specification of the present invention. Moreover, the singular designation of a component does not exclude the plural designation of such a component.

It is also noted that the embodiments may be described as a process which is depicted as a flowchart, a flow diagram, a structure diagram, or a block diagram. Although a flowchart may describe the operations as a sequential process, many of the operations can be performed in parallel or concurrently. Additionally, the order of the operations may be rearranged.

The disclosed methods, apparatus, and systems should not be limited in any way. Rather, the present disclosure encompasses all novel and non-obvious features and aspects of the various disclosed embodiments (both alone and in various combinations and subcombinations with one another). The disclosed methods, apparatus and systems are not limited to any specific aspect or feature or combination thereof, nor do any of the disclosed embodiments require that any one or more specific advantages be present or that certain or all technical problems be solved.

The present invention is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those of ordinary skill in the art without departing from the spirit of the invention and the scope of the appended claims, which are all within the scope of the invention.

Claims

1. A power supply system for an aircraft, comprising:

a battery and a dc emergency bus bar;

a switching bus bar connected to the circuit breaker controller and the first avionics display; and

a bus bar controller configured to determine whether the battery is placed in an emergency power mode in which the battery supplies power to the direct current emergency bus bar;

when the battery is not placed in the emergency power mode, the bus bar controller detects a control signal that causes the power system to enter an electrical maintenance mode, and in response to detecting the control signal, the bus bar controller connects the transition bus bar to the battery to cause the power system to enter an electrical maintenance mode, wherein the battery supplies power to the circuit breaker controller and the first avionics display via the transition bus bar, the circuit breaker controller and the first avionics display being operable in the electrical maintenance mode for a circuit breaker maintenance operation.

2. The power supply system of claim 1, wherein:

wherein when the battery is placed in an emergency power mode, the direct current emergency bus bar is connected to the battery, the conversion bus bar is disconnected from the battery, and the conversion bus bar is connected to the direct current emergency bus bar such that the battery supplies power to the circuit breaker controller and the second avionics display via the direct current emergency bus bar, and the direct current emergency bus bar supplies power to the conversion bus bar, the conversion bus bar supplies power to the circuit breaker controller and the first avionics display,

wherein the circuit breaker controller and the first avionics display are operable in the emergency power mode for circuit breaker maintenance operations.

3. The power supply system of claim 1 or 2, wherein the circuit breaker maintenance operation comprises one or more of:

the circuit breaker controller is configured to receive status information associated with a circuit breaker in a power system;

the first avionics display is configured to display status information of the circuit breaker;

the first avionics display is configured to receive setting information associated with the circuit breaker; or alternatively

The circuit breaker controller configures the circuit breaker according to the setting information.

4. The power supply system of claim 1, further comprising:

an electrical maintenance mode switch, wherein the bus bar controller detects a control signal that causes the power supply system to enter an electrical maintenance mode by detecting a state of the electrical maintenance mode switch.

5. The power supply system of claim 1, further comprising:

an avionics processing system connected to the direct current emergency bus and the conversion bus, wherein the avionics processing system is communicatively coupled to the circuit breaker controller and the first avionics display and performs processing associated with the circuit breaker maintenance operation.

6. The power system of claim 1, wherein the bus bar controller causes the power system to enter an electrical maintenance mode in response to detecting the control signal when one or more of the following conditions are met:

the aircraft is on the ground;

the aircraft is not powered by a generator or an external power source.

7. The power supply system of claim 1, further comprising:

A second battery and a second direct current emergency bus bar,

wherein when the second battery is in an emergency power mode, the second battery is connected to the second direct current emergency bus and powers a second circuit breaker controller and a third avionics display via the second direct current emergency bus,

wherein when the battery and the second battery are not placed in an emergency power mode, the bus bar controller connects the conversion bus bar to the battery and/or the second battery, which supplies power to the circuit breaker controller, the second circuit breaker controller, and the first avionics display via the conversion bus bar, in response to detecting the control signal that causes the power supply system to enter an electrical maintenance mode.

8. An aircraft comprising the power supply system of any one of claims 1-7.

9. A power supply control method for an aircraft power supply system, comprising:

determining whether a battery of the power system is placed in an emergency power mode in which the battery supplies power to a direct current emergency bus;

Detecting a control signal that causes the power system to enter an electrical maintenance mode when the battery is not placed in the emergency power mode;

in response to detecting the control signal, a transition bus is connected to the battery to cause the power system to enter an electrical maintenance mode, wherein the battery supplies power to a circuit breaker controller and a first avionics display via the transition bus, the circuit breaker controller and the first avionics display being operable in the electrical maintenance mode for a circuit breaker maintenance operation.

10. The power supply control method according to claim 9, characterized by further comprising:

when the battery is placed in an emergency power mode, the direct current emergency bus bar is connected to the battery, the conversion bus bar is disconnected from the battery, and the conversion bus bar is connected to the direct current emergency bus bar such that the battery supplies power to the circuit breaker controller and the second avionics display via the direct current emergency bus bar, and the direct current emergency bus bar supplies power to the conversion bus bar, the conversion bus bar supplies power to the circuit breaker controller and the first avionics display,

11. The power supply control method according to claim 9 or 10, wherein the circuit breaker maintenance operation includes one or more of:

12. The power supply control method according to claim 9, characterized by further comprising:

a control signal to cause the power supply system to enter an electrical maintenance mode is detected by detecting a state of an electrical maintenance mode switch.

13. The power supply control method according to claim 9, characterized by further comprising:

processing associated with the circuit breaker maintenance operation is performed with an avionics processing system connected to the direct current emergency bus and the conversion bus.

14. The power supply control method of claim 9, further comprising entering an electrical maintenance mode in response to detecting the control signal when one or more of the following conditions are met:

the aircraft is on the ground;

the aircraft is not powered by a generator or an external power source.

15. The power supply control method according to claim 9, characterized by further comprising:

when a second storage battery of the power supply system is in an emergency power supply mode, the second storage battery supplies power to a second breaker controller and a third avionics display through a second direct-current emergency bus bar; and

when the battery and the second battery are not placed in an emergency power mode, in response to detecting the control signal to cause the power system to enter an electrical maintenance mode, the conversion bus is connected to the battery and/or the second battery, which supplies power to the circuit breaker controller, the second circuit breaker controller, and the first avionics display via the conversion bus.