Power supply system and power supply management system applied to airplane passenger cabin

Abstract

The utility model discloses a power supply system and a power supply management system applied to an airplane passenger cabin. Relates to the technical field of airborne power supply. A power supply structure is improved on the basis of a traditional 115V alternating-current power supply system, an independent power supply conversion module is added to convert a 115V alternating-current power supply into a double-circuit isolation + / -48V direct-current power supply, power is supplied to load equipment such as a seat power supply in a passenger cabin, and on one hand, periodic voltage fluctuation and current transient or high-frequency electromagnetic interference caused by alternating current are avoided; on the other hand, the power supply conversion module converts an alternating current power supply into a direct current power supply, alternating current-direct current conversion equipment does not need to be independently assembled in load equipment, the power supply structure is simplified, conversion times, equipment internal heating and energy loss are reduced, energy efficiency is improved, service life is prolonged, and stability of a power supply system is guaranteed; by arranging the priority command generation module, the dynamic priority management function is realized, and the power supply priority can be flexibly set according to the power demands of different shipping spaces.

Description

TECHNICAL FIELD

[0001] The utility model relates to airborne power supply technology field, concretely relates to a power supply system and power supply management system for application in aircraft passenger cabin. BACKGROUND

[0002] In the modern civil aviation aircraft passenger cabin, the seat display screen and the seat power supply and other equipment are important facilities for providing passenger entertainment, information service and equipment power supply. Traditionally, these devices directly take power from the 115V AC power supply bus of the aircraft power supply system. With the continuous increase in the number of cabin equipment and the complication of cabin power supply management requirements, the traditional 115V AC power supply system faces many challenges.

[0003] Firstly, the 115V AC power supply system directly takes power from the aircraft power supply bus, which puts high requirements on the electrical load characteristics of the equipment. When the power dynamic range of the equipment is large, the system design will reserve a lot of margin, which will lead to the deterioration of important indicators such as efficiency, cost and weight. In addition, the 115V AC bus itself has no flexible dynamic power management function and cannot adjust the power supply strategy in real time according to the priority requirements of different cabins. The existing system has insufficient cascading equipment redundancy, and once the power supply of a certain equipment fails, it may cause the power supply system of the entire equipment group (such as 3 to 4 seats) to fail, affecting the passenger experience. In addition, with the continuous change of the electrical requirements of the aircraft cabin equipment, reducing the operating voltage of the equipment and optimizing the power management system to improve efficiency and flexibility become a direction worth exploring. SUMMARY

[0004] The technical problem to be solved by the utility model is that the traditional 115V AC power supply system in the civil aviation aircraft passenger cabin directly takes power from the aircraft power supply bus, which has high requirements on the electrical load characteristics of the load equipment, has potential safety and stability hazards, and the power supply failure of part of the load equipment will affect the power supply system of the entire equipment group. The purpose of the present scheme is to provide a power supply system and power supply management system for application in aircraft passenger cabin, which improves the power supply structure on the basis of the traditional 115V AC power supply system, converts the 115V AC power supply into dual-path isolated ±48V DC power supply through the addition of an independent power supply conversion module, and supplies power to the load equipment such as seat power supply in the passenger cabin. On the one hand, it avoids periodic voltage fluctuations and current transients or high-frequency electromagnetic interference caused by AC power; on the other hand, it converts AC power into DC power through the power supply conversion module, and each load equipment does not need to be separately equipped with an AC-DC conversion device, which simplifies the power supply structure, reduces the conversion frequency, reduces energy loss, reduces internal heating of the equipment, improves energy efficiency and service life, and makes the entire power supply system more stable.

[0005] The utility model is realized by the following technical scheme:

[0006] The scheme provides a power supply system applied to an aircraft passenger cabin, comprising:

[0007] An onboard AC power supply is configured to provide AC power.

[0008] A power conversion module is configured to convert the AC power into single or multiple DC power supplies; the power conversion module is connected with the onboard AC power supply; and the single or multiple DC power supplies output by the power conversion module are connected to respective load devices.

[0009] The onboard AC power supply can be understood as an inherent 115VAC / 400Hz AC power supply on the aircraft.

[0010] The working principle of the scheme is as follows: the traditional 115V AC power supply system in the passenger cabin of a civil aviation aircraft directly supplies power to load devices from the 115V AC power supply system, and the load devices directly use a 115VAC power bus, which has high requirements for the electrical load characteristics of the load devices, and has hidden dangers of safety and stability, and power failure of part of the load devices will affect the power system failure of the entire device group; the purpose of the scheme is to provide a power supply system and a power supply management system applied to an aircraft passenger cabin, and to improve the power supply structure on the basis of the traditional 115V AC power supply system, and to convert the 115V AC power supply into a dual-isolated ±48V DC power supply through an independent power conversion module, thereby supplying power to the load devices such as seat power supplies in the passenger cabin; on the one hand, periodic voltage fluctuations and current transients or high-frequency electromagnetic interference caused by AC power are avoided; on the other hand, the AC power supply is converted into a DC power supply by the power conversion module, and no separate AC-DC conversion device needs to be installed in each load device, thereby simplifying the power supply structure, reducing the number of conversions, reducing energy loss, reducing internal heating of the device, improving energy efficiency and service life, and making the entire power supply system more stable.

[0011] Further optimization scheme is that the onboard AC power supply is a 115V AC power supply, and the power conversion module generates two isolated ±48V DC power supplies.

[0012] Further optimization scheme further comprises a transmission bus configured to transmit a load device control command.

[0013] The transmission bus is connected between the power conversion unit and the load device.

[0014] Further optimization scheme is that the transmission bus comprises an SPE bus and an RS485 bus.

[0015] Further optimization scheme is that the power conversion unit comprises a filter unit, a PFC unit and an isolated DC-DC conversion unit connected in sequence.

[0016] Further, the two isolated DC power supplies of ±48V are parallelly powered to realize 96V voltage difference, or separately powered to realize 48V voltage difference.

[0017] Further, the load devices include: seat power supply, display, seat display screen, USB charging port, emergency lighting, wireless overhead display and video control terminal.

[0018] The application also provides a power supply management system comprising the power supply system applied to the aircraft cabin.

[0019] Further, the management system further comprises a priority command generation module for generating load device control commands according to priorities; the load device control commands are sent to the load devices through the transmission bus; and the priority command generation module is arranged in the power supply conversion module.

[0020] Further, the management system further comprises an action mechanism for turning off the load devices according to the load device control commands; and the action mechanism is connected with switches of the load devices.

[0021] Compared with the prior art, the application has the following advantages and beneficial effects:

[0022] 1. The application provides a power supply system and a power supply management system applied to an aircraft cabin, which are improved in power supply structure on the basis of a traditional 115V AC power supply system, and the 115V AC power supply is converted into two isolated DC power supplies of ±48V through an independent power supply conversion module to supply power to load devices such as seat power supplies in the cabin.

[0023] 2, The scheme provides a power supply system and a power supply management system applied to an aircraft passenger cabin, which provides stable power support for multiple load devices in the passenger cabin through a unified ±48V direct current power supply architecture, reduces the number of PFC modules inside the load devices from multiple to one power supply conversion module, significantly reduces the device cost, simplifies the power supply management structure, and improves the overall efficiency and reliability of the power supply system. In addition, the unified direct current power supply method greatly reduces electrical faults and maintenance costs.

[0024] 3, The scheme provides a power supply system and a power supply management system applied to an aircraft passenger cabin, the power supply conversion module generates two isolated direct current power supplies of ±48V; when any side of the ±48V power supply system fails, the system can automatically switch to a single-side 48V power supply mode to continue to provide power for the load device; this backup function significantly improves the redundancy and fault recovery capability of the system, ensuring the continuous operation of the load device.

[0025] 4, The scheme provides a power supply system and a power supply management system applied to an aircraft passenger cabin, by setting a priority command generation module, generating load device control commands according to priority, realizing a dynamic priority management function, and flexibly setting the power supply priority according to the power demand of different cabins. BRIEF DESCRIPTION OF DRAWINGS

[0026] The drawings described herein are used to provide further understanding of the embodiments of the utility model, constitute a part of this application, and do not constitute the limitation to the embodiments of the utility model. In the drawings:

[0027] Figure 1 It is a schematic diagram of the power supply system applied to the aircraft passenger cabin;

[0028] Figure 2 It is a schematic diagram of the power supply system applied to the traditional aircraft passenger cabin;

[0029] Figure 3 It is a schematic diagram of the power supply conversion module. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical scheme and advantages of the utility model more clear and obvious, the utility model is further explained in detail below in combination with embodiments and drawings, and the illustrative embodiments of the utility model and the explanation thereof are only used to explain the utility model, and do not constitute the limitation to the utility model.

[0031] The traditional aircraft passenger cabin 115V alternating current power supply system is as follows: Figure 2As shown, the load device directly takes power from the aircraft power bus, which puts high requirements on the electrical load characteristics of the load device. When the power dynamic range of the load device is large, the system design will reserve a lot of margin, which will cause the degradation of important indicators such as efficiency, cost, weight, etc. In addition, the 115V AC bus itself has no flexible dynamic power management function and cannot adjust the power supply strategy in real time according to the priority requirements of different cabins. The existing system has insufficient cascading device redundancy, and once the power supply of a load device fails, it may cause the power supply system of the entire device group (such as 3 to 4 seats) to fail, affecting the passenger experience. In addition, as the electrical demand of the aircraft cabin device continues to change, reducing the operating voltage of the load device and optimizing the power management system to improve efficiency and flexibility become a direction worth exploring. In view of this, the present scheme provides the following embodiments to solve the above technical problems:

[0032] Embodiment 1

[0033] The present embodiment provides a power supply system applied to an aircraft cabin, as shown in Figure 1 , comprising:

[0034] An onboard AC power supply for providing AC power;

[0035] A power conversion module (Dual DC in Figure 1 ) for converting AC power into single or multiple DC power supplies; the power conversion module is connected with the onboard AC power supply; the single or multiple DC power supplies output by the power conversion module are respectively connected to each load device.

[0036] The onboard AC power supply is a 115V AC power supply (115VAC L and 115VAC N in Figure 1 ), and the power conversion module generates two isolated ±48V DC power supplies.

[0037] Further comprising a transmission bus for transmitting load device control commands;

[0038] The transmission bus is connected between the power conversion unit and the load device.

[0039] The transmission bus includes an SPE bus and an RS485 bus.

[0040] The two isolated ±48V DC power supplies are parallelly powered to achieve a 96V voltage difference, or are separately powered to achieve a 48V voltage difference.

[0041] As shown in Figure 3 , the power conversion unit includes a filter unit, a PFC unit, and an isolated DC-DC conversion unit connected in sequence.

[0042] The load device includes: seat power supply, display, seat display screen, USB charging port, emergency lighting, wireless overhead display and video control terminal.

[0043] After the power supply structure is improved in the scheme, the load devices in the passenger cabin, such as overhead displays and seat power supplies, are powered from 115V AC; and the control panel WiFi device needs 28V DC. After the load devices are uniformly integrated and powered in the scheme, all the load devices can be directly powered from ±48V DC, and the load devices previously directly powered from 115V AC do not need to be modified.

[0044] The power supply system applied to the passenger cabin of an aircraft integrates a power supply conversion module at the rear end of the existing 115V AC power supply. The power supply conversion module is responsible for converting the 115V AC power supply into a dual-path isolated 48V power supply combined into ±48V DC power supply, and then powers the load devices such as seat power supplies in the passenger cabin, replacing the traditional 115V AC direct power supply mode. Not only can it provide more secure and stable low-voltage power supply for load devices such as seat power supplies, seat display screens and video control centers, but also the dual-path isolated DC power supply of ±48V generated by the power supply conversion module supports a single-sided 48V backup power supply mode, ensuring that the load devices can still operate continuously and stably even in the case of system failure.

[0045] In terms of safety: first, 48V DC is a safe extra low voltage (SELV, Safety Extra Low Voltage) with no risk of electric shock. Second, 115V AC power supply is prone to electromagnetic interference (EMI), which can affect sensitive devices around it. Compared with AC power, DC power does not have periodic voltage fluctuations during power supply, and does not produce current transients or high-frequency electromagnetic interference (EMI) caused by AC power. It can significantly improve the electrical safety of the power supply system, reduce interference to sensitive electronic circuits, and improve the overall electromagnetic compatibility (EMC) of the system.

[0046] In terms of stability: 115V AC power supply is replaced by ±48V DC power supply, which can greatly simplify the power supply structure and enhance system stability. All devices powered by 115V AC power supply need to be AC-DC converted, i.e. 115V AC power is rectified and then boosted to 380V by PFC power factor correction module before being converted to the required voltage by DC / DC converter. Therefore, all power supply devices need to be equipped with PFC modules, and the number of PFC modules is large and must be boosted to high voltage for power factor correction. After being replaced by 48V DC power supply, only one PFC unit in the power supply conversion module is needed, which greatly reduces the cost. The downstream load devices of the power supply conversion module do not need to be boosted to 380V for power factor correction process. Simplifying the power supply structure, reducing the number of conversions, reducing energy loss, and reducing internal heating of the device can improve energy efficiency and service life, making the entire power supply system more stable.

[0047] In addition, the power supply system applied to the aircraft passenger cabin has a ±48V dual-channel redundant power supply function, which provides bipolar DC power supply of +48V and -48V relative to the center ground point. The power supply conversion module can use two power supply rails to provide a higher voltage difference (96V) or only use one rail (48V). In the event of a failure of any one of the power supply rails, the power supply system applied to the aircraft passenger cabin can automatically switch to a single-sided 48V mode due to the presence of the center ground point, and the device can still operate normally, which is an automatic and seamless switching mode that maintains continuous power supply. Ensuring that the device can continue to operate in the event of a power failure can greatly enhance the reliability of power distribution. The input range of the isolated DC-DC conversion unit of the power supply conversion module is wide, and the device can operate normally for input of 96V or 48V without changing the power supply structure.

[0048] The power supply conversion module completely integrates the power of the passenger cabin devices, and passengers will not directly contact 115V AC power supply, eliminating the risk of AC leakage current. Unifying various devices in the passenger cabin for DC power supply can greatly reduce the cost of device power components. For example, the power supply of the seat, iRM hanging display, SVDU seat display screen, VCC video control terminal, etc. After integration, the number of PFC modules can be reduced from dozens to one. This can simplify the power bus standard of the passenger cabin electronic devices and improve the efficiency and reliability of the overall power supply system.

[0049] Embodiment 2

[0050] The embodiment provides a power supply management system, which comprises the power supply system applied to the aircraft passenger cabin according to the embodiment 1.

[0051] The management system further comprises a priority command generation module configured to generate load device control commands according to priorities; the load device control commands are sent to the load devices through the transmission bus; the priority command generation module is arranged in the power supply conversion module.

[0052] The power supply management system optimizes the power distribution of different load devices through the priority command generation module, ensures the rational scheduling and efficient use of power resources, and meets the power demand of different devices and cabins.

[0053] The priority command generation module in the power supply conversion module can monitor the power demand of cabins and devices in real time, and allocate power supply resources based on preset priority rules, so as to ensure that critical devices can obtain power support in power supply shortage or abnormal conditions, and realize flexible power resource allocation and optimized management.

[0054] The power supply conversion module controls the subordinate DC load devices through the SPE bus and the RS485 bus; in this embodiment, the power supply priorities are dynamically set according to the specific needs of cabins and devices. The business class devices (such as seat power supply, seat display screen, USB charging port, etc.) are allocated as the second priority, and the economy class devices (such as seat power supply, seat display screen, USB charging port, etc.) are allocated as the third priority. The critical devices (such as emergency lighting, wireless overhead display) always enjoy the first priority in the system, so that the load device power consumption can be closed or limited in the case of power resource shortage, and the power resources can be reasonably configured. The system can flexibly adjust the power distribution by monitoring the running state and load demand of each device in real time, balance the devices of different priorities in power distribution, and improve the reliability and efficiency of the power supply system. The power supply resources are dynamically allocated while ensuring the power support of critical devices, and the power supply support capability is improved.

[0055] The above specific embodiments further illustrate the purpose, technical solutions and beneficial effects of the utility model, and it should be understood that the above description is only a specific embodiment of the utility model and does not limit the protection scope of the utility model. Any modification, equivalent replacement, improvement, etc. within the spirit and principles of the utility model should be included in the protection scope of the utility model.

Claims

1. A power supply system for application to a passenger cabin of an aircraft, characterized in that, The application relates to a power supply system for an aircraft passenger cabin. The power supply system comprises: an onboard AC power supply for providing AC power; a power conversion module for converting the AC power into single or multiple DC power supplies; the power conversion module is connected with the onboard AC power supply; and the single or multiple DC power supplies output by the power conversion module are connected with respective load devices. The onboard AC power supply is a 115V AC power supply, and the power conversion module generates two isolated DC power supplies with a voltage of + / -48V.

2. The power supply system for use in a passenger cabin of an aircraft according to claim 1, characterized in that The power supply system further comprises a transmission bus for transmitting load device control commands.

3. A power supply system for use in an aircraft cabin according to claim 2, wherein, The transmission bus is connected between the power conversion module and the load devices. The transmission bus comprises an SPE bus and an RS485 bus.

4. The power supply system for use in a passenger cabin of an aircraft according to claim 3, characterized in that The power conversion module comprises a filter unit, a PFC unit and an isolated DC-DC conversion unit which are electrically connected in sequence.

5. The power supply system for use in a passenger cabin of an aircraft according to claim 2, characterized in that, The load devices comprise seat power supplies, displays, seat display screens, USB charging ports, emergency lighting, wireless overhead displays and video control terminals.

6. The power supply system for use in a passenger cabin of an aircraft according to claim 1, characterized in that, The two isolated DC power supplies with a voltage of + / -48V are used to provide a voltage difference of 96V in parallel or a voltage difference of 48V in series.

7. The power supply system for use in a passenger cabin of an aircraft according to claim 2, characterized in that, The application further relates to a power supply system for an aircraft passenger cabin.

8. A power supply management system, characterized by, The management system further comprises a priority command generation module for generating load device control commands according to priorities; the load device control commands are transmitted to the load devices through the transmission bus; and the priority command generation module is arranged in the power conversion module.

9. A power supply management system according to claim 8, wherein, The management system further comprises an action mechanism for turning off the load devices according to the load device control commands; and the action mechanism is connected with switches of the load devices.

10. The power management system of claim 8, wherein, ​

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