CN111293864B - Remote power distribution device architecture integrating multiple power conversion functions - Google Patents
Remote power distribution device architecture integrating multiple power conversion functions Download PDFInfo
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- CN111293864B CN111293864B CN201811496908.0A CN201811496908A CN111293864B CN 111293864 B CN111293864 B CN 111293864B CN 201811496908 A CN201811496908 A CN 201811496908A CN 111293864 B CN111293864 B CN 111293864B
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- 238000006243 chemical reaction Methods 0.000 title claims abstract description 47
- 238000004891 communication Methods 0.000 claims abstract description 22
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000005070 sampling Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 6
- 230000017525 heat dissipation Effects 0.000 description 3
- 230000001629 suppression Effects 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 230000009977 dual effect Effects 0.000 description 2
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Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M1/00—Details of apparatus for conversion
- H02M1/10—Arrangements incorporating converting means for enabling loads to be operated at will from different kinds of power supplies, e.g. from ac or dc
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Abstract
The invention discloses a remote power distribution device architecture integrating multiple power conversion functions, comprising a power conversion module for receiving an input power 230VAC and an input power 28VDC from outside and converting the input power 230VAC and the input power 28VDC into an output power 230VAC, an output power 115VAC, an output power +/-270VDC, an output power +/-135VDC and an output power 28VDC according to the input power 230VAC and the input power 28VDC; SSPC 230VAC module; SSPC 115VAC module; an SSPC +/-270VDC module; SSPC +/-135VDC module; SSPC 28VDC module; and a COM communication module. The invention has the beneficial effects that: after the new power architecture is adopted, the number of the input power feeder lines of the RPDU is changed from the previous multiple wires into three, and meanwhile, as the voltage level of the feeder lines is improved, the input current can be reduced, the wire diameter of the wires is reduced, and the weight of the aircraft cable is reduced from two dimensions.
Description
Technical Field
The present invention relates to a remote power distribution device architecture integrating multiple power conversion functions.
Background
The power supply system of the traditional aircraft (including multi-electric aircraft such as B787) comprises four components of power generation, secondary power supply, primary power distribution and secondary power distribution. Where the generator is the primary power source of the aircraft, typically 115VAC or 235VAC ac, which is converted by the secondary power source into 28VDC to the primary power distribution bus, which is then subdivided by the primary power distribution system into secondary power distribution devices which supply the terminal loads.
The system architecture is complex due to the fact that the secondary power supply conversion device and the required primary power distribution intermediate link are introduced, the reliability of a power supply system is reduced, and the weight and cost of the aircraft are increased.
Fig. 1 is an RPDU architecture design of B787.
As can be seen from the figure, the RPDU contains 8 modules, namely two communication modules (COM 1 and COM 2) and 6 SSPCs (3 DC SSPCs and 3 AC SSPCs).
The communication module obtains a 28VDC working power supply from outside to provide working power supply for the communication module and other SSPCs, and simultaneously provides a communication interface between the RPDU and other RPDUs for RPDU communication networking. The communication mode adopts AFDX and TTP.
The power inputs for the AC SSPC and DC SSPC come from external 115VAC power feeders and 28VDC power feeders, providing power supplies for the 115VAC and 28VDC loads, respectively.
From this architectural design, we can see that it has several drawbacks:
a. The product not only needs the working power supply input (28 VDC), but also needs the power feeder input (115 VAC and 28 VDC), the variety of power input voltage is multiple, and the weight of the cable is increased;
b. The SSPC output voltage is too single to output 115VAC and 28VDC voltages, and cannot meet the future multi-aircraft needs for multiple voltage levels (+/-135 VDC, +/-270 VDC);
c. The communication bus adopts TTP, which is expensive, and other mature low-cost communication buses can be adopted.
Disclosure of Invention
The invention aims to solve the technical problem that the aircraft cable is heavy, and provides a novel remote power distribution device architecture integrating multiple power conversion functions.
In order to achieve the purpose, the technical scheme of the invention is as follows: a remote power distribution device architecture integrating multiple power conversion functions, comprising,
A power conversion module for receiving an input power 230VAC and an input power 28VDC from the outside and converting into an output power 230VAC, an output power 115VAC, an output power +/-270VDC, an output power +/-135VDC, and an output power 28VDC according to the input power 230VAC and the input power 28VDC;
An SSPC 230VAC module for receiving the output power 230VAC and the output power 28VDC from the power conversion module;
An SSPC 115VAC module for receiving the output power 115VAC and the output power 28VDC from the power conversion module;
an SSPC +/-270VDC module for receiving output power +/-270VDC and output power 28VDC from the power conversion module;
An SSPC +/-135VDC module for receiving output power +/-135VDC and output power 28VDC from the power conversion module;
An SSPC 28VDC module for receiving output power 28VDC from the power conversion module; and
And the COM communication module is used for receiving the output power 28VDC from the power conversion module.
As a preferable scheme of the remote power distribution device architecture integrating various power conversion functions, the communication mode of the COM communication module is an AFDX/CAN bus.
Compared with the prior art, the invention has the beneficial effects that: the original centralized power supply conversion is changed into a distributed type, the power capacity of a single power supply conversion device is reduced, so that original forced air cooling heat dissipation or liquid cooling heat dissipation is not necessary any more, natural heat dissipation can be adopted, and the heat distribution of an aircraft power supply system is optimized; after a new power architecture is adopted, the number of input power feeder lines of the RPDU is changed from the previous plurality of wires into three, and meanwhile, as the voltage level of the feeder lines is improved, the input current can be reduced, the wire diameter of the wires is reduced, and the weight of the aircraft cable is reduced from two dimensions; the emergency loop is provided with a storage battery for supplying power, so that the safety of the aircraft is ensured; the communication bus supports AFDX/CAN combination, so that the cost of the communication system is reduced.
In addition to the technical problems, features constituting the technical solutions and advantageous effects caused by the technical features of the technical solutions described above, other technical problems that the present invention can solve, other technical features included in the technical solutions and advantageous effects caused by the technical features will be described in further detail with reference to the accompanying drawings.
Drawings
Fig. 1 is a prior art RPDU architecture design of B787.
Fig. 2 is a schematic diagram of an RPDU architecture with integrated multiple power conversion functions according to the present patent.
Fig. 3 is a schematic diagram of the interior of the RPDU proposed in this patent, wherein the conversion module includes various voltage conversion functions.
Fig. 4 is a schematic diagram of the design of the DC SSPC board of the RPDU of this patent.
Fig. 5 is an AC SSPC board design principle for the RPDU of the present patent.
Fig. 6 is a DC SSPC channel design principle for the RPDU of the present patent.
Fig. 7 is an AC SSPC channel design principle for the RPDU of the present patent.
Detailed Description
The invention will be described in further detail below with reference to the drawings by means of specific embodiments. The description of these embodiments is provided to assist understanding of the present invention, but is not to be construed as limiting the present invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
The patent proposes an RPDU architecture design integrating multiple power conversion functions
As shown in fig. 2, to simplify the architecture of the aviation power supply system and improve the safety and economy, it is considered that the original on-board centralized power conversion device is integrated into the RPDU, and therefore, the following improvements are needed based on the original RPDU:
a) The power conversion module is added, the power input is changed from the former 115VAC/28VDC system to the 230VAC/28VDC system, and the input current is reduced by improving the input voltage level, so that the cable diameter is reduced, and the weight of the aircraft is reduced;
b) The added power conversion module supports multiple voltage conversions, 28VDC, +/-135VDC and +/-270VDC may be generated from a 230VAC power input to meet the needs of various voltage class loads in a multi-aircraft;
c) The original 28VDC power input is reserved, the input comes from a storage battery, and when the aircraft is in a multiple failure mode, key electronic equipment on the aircraft can still acquire a standby power supply from the storage battery so as to ensure the flight safety to the greatest extent;
d) The external communication bus is further optimized, the AFDX/TTP combination of B787 is changed into the AFDX/CAN bus combination, namely, the expensive TTP bus is abandoned, and the safety of the aircraft is further improved.
In addition, due to the advent of SSPCs with multiple voltage specifications, corresponding considerations are also made in the design of SSPC boards and channels. This patent presents a schematic block diagram of the design of both DC and AC SSPC boards and channels.
After these improvements, the RPDU integrated with various power conversion modules can support various SSPC specifications of 28VDC, 115VAC, +/-135VDC, +/-270VDC, 230VAC and the like, and can meet the requirements of future multi-electric aircraft on various voltage levels.
The RPDU internal schematic block diagram provided by the patent, the conversion module of which comprises various voltage conversion functions
As shown in fig. 3, to achieve control of the load, power conversion is performed inside the RPDU. First, the conversion from 235VAC to 28VDC is performed, the converted 28VDC is OR-operated with an external 28VDC Batt bus bar to supply power to the 28VDC SSPC, and the power supply control is performed on the 28VDC Load by the latter.
The 235VAC also performs 115VAC voltage conversion to provide power input to the 115VAC SSPC and power control by the latter for the 115VAC load.
The 235VAC Bus can be directly used as a power supply input of the 230VAC SSPC to supply power for the 230VAC load.
Similarly, +/-135VDC and +/-270VDC are also converted from the 230VAC input voltage by the internal voltage conversion module as power inputs to the RPDU +/-135VDC and +/-270VDC SSPC boards.
DC SSPC board card design principle of RPDU
Fig. 4 is a schematic diagram of the design of the DC SSPC board of the RPDU of this patent.
The DC SSPC board has two power inputs, one is a 28VDC power input, which comes from the voltage conversion module of the RPDU, which the DC SSPC uses as its own operating power supply. The 28VDC cannot be directly used as an internal control power supply, and therefore, the 28VDC is reduced to a digital voltage of 5V/3.3V/1.8V and the like through DC-DC voltage conversion and then used as an operating power supply of a master control chip uP.
Another power input to the DC SSPC board is also from the RPDU power conversion module, which may support voltage levels of 28VDC, +/-135VDC and +/-270VDC depending on the SSPC load.
Multiple DC SSPC channels (such as DC SSPC ch1 to chn in the figure) are integrated on each DC SSPC, and the highly integrated channel design improves the power density of the RPDU and reduces the volume and weight.
The SSPC externally employs a dual redundancy serial bus for communication with the communication board COM of the RPDU.
In addition, DC SSPCs integrate discrete control, i.e., control of the load path can receive either instructions to traverse the bus or control of external discrete amounts. The policies that it controls are specified by the configuration file.
EMI filter processing is added to all I/O of the DC SSPC board to improve EMI suppression capability.
AC SSPC board card design principle of RPDU
Fig. 5 is an AC SSPC board design principle for the RPDU of the present patent.
The AC SSPC board has two power inputs, one being a 28VDC power input, which comes from the voltage conversion module of the RPDU, which the AC SSPC uses as its own operating power supply. The 28VDC cannot be directly used as an internal control power supply, and therefore, the 28VDC is reduced to a digital voltage of 5V/3.3V/1.8V and the like through DC-DC voltage conversion and then used as an operating power supply of a master control chip uP.
Another power input to the AC SSPC board is also from the RPDU power conversion module, which can support 115VAC and 230VAC voltage levels depending on the SSPC load.
Multiple AC SSPC channels (AC SSPCs ch1 through chn in the figure) are integrated on each DC SSPC, and the highly integrated channel design increases the power density of the RPDU, reducing volume and weight.
The SSPC externally employs a dual redundancy serial bus for communication with the communication board COM of the RPDU.
In addition, AC SSPCs integrate discrete control, i.e., control of the load path can receive either instructions to traverse the bus or control of external discrete amounts. The policies that it controls are specified by the configuration file.
EMI filter processing is added to all I/O of the AC SSPC board to improve EMI suppression capability.
DC SSPC channel design principle of RPDU
Fig. 6 is a DC SSPC channel design principle for the RPDU of the present patent.
The core device is a power MOS tube, on-off control of the power MOS tube is given by a driver logic, and a sampling resistor (sampling resistor) provides Current signals for Short Circuit protection (Short Circuit) and Current sampling (Current sampling). Status sampling (status sampling) of the channel is achieved by channel voltage sampling.
The channel control command CMD comes from the main control chip uP of the DC SSPC board card, and the collected channel state (including short-circuit protection, current sampling and state sampling) is also fed back to the main control chip uP.
The Isolated DC-DC (Isolated DC-DC) on the channel provides a working power supply for the channel, the EMI module is used for improving electromagnetic immunity of the channel, the fuse is used as failure safety protection, and when the MOS tube control fails, the fuse can also be used as a backup protection measure, so that the safety coefficient of the aircraft is improved.
AC SSPC channel design principle of RPDU
Fig. 7 is an AC SSPC channel design principle for the RPDU of the present patent.
It is similar to DC SSPCs in terms of isolated power supply design, channel drive logic, short circuit protection, current sampling, status acquisition, EMI suppression, etc.
The difference is that the AC SSPC channel uses two back-to-back MOS transistors, rather than just one MOS transistor as in the DC SSPC channel. In addition, zero crossing detection logic (VZero Crossing and IZero Crossing) is specially designed to reduce voltage and current surges generated by the ac SSPC at the moment of switching on and off to realize soft switching.
In order to realize the simultaneous protection of the three-phase alternating current load, the AC SSPC channel also outputs a short-circuit protected Alarm signal to the main uP to realize the protection of the three-phase SSPC channel in one period.
The foregoing has outlined rather broadly the more detailed description of the invention in order that the detailed description thereof that follows may be better understood, and in order that the present invention may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. Accordingly, the scope of protection of the present invention is to be determined by the appended claims.
Claims (2)
1. A remote power distribution device architecture integrating multiple power conversion functions is characterized by comprising,
A power conversion module for receiving an input power 230VAC and an input power 28VDC from the outside and converting into an output power 230VAC, an output power 115VAC, an output power +/-270VDC, an output power +/-135VDC, and an output power 28VDC according to the input power 230VAC and the input power 28VDC;
The SSPC 230VAC module is used for connecting a 230VAC load, and the SSPC 230VAC module receives an output power supply 230VAC and an output power supply 28VDC from the power conversion module, wherein the output power supply 28VDC is used as a working power supply of a master control chip uP of the SSPC 230VAC module, and the output power supply 230VAC is used as a power input of the SSPC 230VAC module;
the SSPC 115VAC module is used for connecting 115VAC loads, and the SSPC 115VAC module receives the output power source 115VAC and the output power source 28VDC from the power conversion module, wherein the output power source 28VDC is used as the working power source of the master control chip uP of the SSPC 115VAC module, and the output power source 115VAC is used as the power input of the SSPC 115VAC module;
an SSPC +/-270VDC module for receiving a +/-270VDC load, the SSPC +/-270VDC module receiving the output power +/-270VDC from the power conversion module and the output power 28VDC, wherein the output power 28VDC is used as the operating power of the SSPC +/-270VDC module master chip uP and the output power +/-270VDC is used as the power input of the SSPC +/-270VDC module;
An SSPC +/-135VDC module for receiving a +/-135VDC load, the SSPC +/-135VDC module receiving the output power +/-135VDC from the power conversion module and the output power 28VDC, wherein the output power 28VDC is used as the operating power of the SSPC +/-135VDC module master chip uP and the output power +/-135VDC is used as the power input of the SSPC +/-135VDC module;
An SSPC 28VDC module for receiving a 28VDC load, the SSPC 28VDC module receiving an output power 28VDC from the power conversion module, wherein the output power 28VDC is used as an operating power and power input for the SSPC 28VDC module master control chip uP; and
And the COM communication module is used for receiving the output power 28VDC from the power conversion module.
2. The architecture of claim 1, wherein the COM communication module has a communication mode of AFDX/CAN bus.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104485704A (en) * | 2014-12-05 | 2015-04-01 | 中国航空工业集团公司第六三一研究所 | Multi-channel dual-redundancy intelligent power supply management system |
| CN108183612A (en) * | 2018-03-13 | 2018-06-19 | 北京比特大陆科技有限公司 | Expansible parallel operation DC-DC power source device |
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| EP2945244B1 (en) * | 2014-05-15 | 2022-07-06 | Airbus Operations GmbH | Power and data distribution module and method for power and data distribution in an airborne vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104485704A (en) * | 2014-12-05 | 2015-04-01 | 中国航空工业集团公司第六三一研究所 | Multi-channel dual-redundancy intelligent power supply management system |
| CN108183612A (en) * | 2018-03-13 | 2018-06-19 | 北京比特大陆科技有限公司 | Expansible parallel operation DC-DC power source device |
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