# US 8,148,842 B2 · Electrical power generation system having multiple secondary power distribution assemblies with integral power conversion

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- Number: US 8,148,842 B2
- Document ID: US8148842B2
- Status: Granted
- Kind: B2
- Application number: 11/358,870
- Filed: 2006-02-20
- Published: 2007-08-23
- Granted: 2012-04-03
- Earliest claimed: 2006-02-20
- Assignees: Hamilton Sundstrand Corporation
- Inventors: Josef Maier
- Web page: https://patentgrep.com/patent/US8148842B2

## CPC

- H02J 4/00: Circuit arrangements for mains or distribution networks not specified as AC or DC; Circuit arrangements for mains or distribution networks combining AC and DC sections or sub-networks (arrangements using intermediate DC-AC-DC conversion H02J1/002; arrangements using high-voltage DC [HVDC] links H02J3/36)
- H02J 2105/32: {for aircrafts}
- H02J: ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY

## Abstract

An improved EPGS with an integrated electrical system architecture uses SPDAs with localised power converters to provide the necessary types of power to their respective electrical loads so that a single type of primary power bus may be used to connect its PDAs to respective SPDAs.

## Claims

### Claim 1

An electrical power generating system (EPGS) for an aircraft with an integrated electrical system architecture that has at least one electrical power source aboard the aircraft, comprising:
a primary power distribution assembly (PDA) aboard the aircraft for each electrical power source that distributes power of one type to a single corresponding primary bus; and
at least one secondary power distribution assembly (SPDA) aboard the aircraft for each PDA that receives only the power of one type on the single corresponding primary bus, converts power of the one type to converted power of multiple other types, wherein at least one type of converted power is a type of AC power and distributes the converted power of the multiple other types to at least some respective electrical loads for each SPDA.

### Claim 2 (depends on 1)

The EPGS of claim 1, wherein the type of power that each PDA distributes to its single corresponding primary bus is AC.

### Claim 3 (depends on 2)

The EPGS of claim 2, wherein one other type of power that each SPDA distributes to at least some of its respective electrical loads is DC.

### Claim 4 (depends on 3)

The EPGS of claim 3, wherein each SPDA comprises a power converter for converting AC power that it receives from its corresponding single primary power bus to DC for at least some of its respective electrical loads.

### Claim 5 (depends on 4)

The EPGS of claim 4, wherein each power converter comprises a transformer rectifier unit (TRU).

### Claim 6 (depends on 1)

The EPGS of claim 1, wherein the type of converted power that each PDA distributes to its single corresponding primary bus is DC of high electrical potential.

### Claim 7 (depends on 6)

The EPGS of claim 6, wherein one other type of converted power that each SPDA distributes to at least some of its respective electrical loads is AC.

### Claim 8 (depends on 7)

The EPGS of claim 7, wherein each SPDA comprises a power converter for converting DC power of high electrical potential that it receives from its corresponding single primary power bus to AC for at least some of its respective electrical loads.

### Claim 9 (depends on 8)

The EPGS of claim 8, wherein each power converter comprises a DC/AC converter.

### Claim 10 (depends on 6)

The EPGS of claim 6, wherein one other type of converted power that each SPDA distributes to at least some of its respective electrical loads is DC of lower electrical potential.

### Claim 11 (depends on 10)

The EPGS of claim 10, wherein each power converter comprises a DC/DC converter.

### Claim 12 (depends on 7)

The EPGS of claim 7, wherein one other type of converted power that each SPDA distributes to at least some of its respective electrical loads is AC, and another type of converted power that each SPDA distributes to at least some of its respective electrical loads is DC of lower electrical potential.

### Claim 13 (depends on 12)

The EPGS of claim 12, wherein each SPDA comprises a power converter for converting DC power of high electrical potential that it receives from its corresponding single primary power bus to AC and DC of lower electrical potential for at least some of its respective electrical loads.

### Claim 14 (depends on 13)

The EPGS of claim 13, wherein each power converter comprises a DC/AC and DC/DC converter.

### Claim 15

An electrical power generating system (EPGS) for an aircraft with an integrated electrical system architecture that has at least one electrical power source aboard the aircraft, comprising:
a primary power distribution assembly (PDA) aboard the aircraft for each electrical power source that distributes AC power to a single corresponding primary bus; and
at least one secondary power distribution assembly (SPDA) aboard the aircraft for each PDA that comprises a power converter that receives only the AC power on the single corresponding primary bus, simultaneously converts it to multiple types of converted power, wherein at least one type of converted power is a type of DC power and distributes the converted DC power to at least some respective electrical loads for each SPDA.

### Claim 16 (depends on 15)

The EPGS of claim 15, The EPGS of claim 15, wherein each power converter comprises a transformer rectifier unit (TRU).

### Claim 17

An electrical power generating system (EPGS) for an aircraft with an integrated electrical system architecture that has at least one electrical power source aboard the aircraft, comprising:
a primary power distribution assembly (PDA) aboard the aircraft for each electrical power source that distributes DC power of high electrical potential to a single corresponding primary bus; and
at least one secondary power distribution assembly (SPDA) aboard the aircraft for each PDA that comprises a power converter that receives only DC power of high electrical potential on the single corresponding primary bus, simultaneously converts it to multiple types of power, wherein at least one type of converted power is a type of AC power and distributes the converted AC power to at least some respective electrical loads for each SPDA.

### Claim 18 (depends on 17)

The EPGS of claim 17, wherein each power converter comprises a DC/AC converter.

### Claim 19

An electrical power generating system (EPGS) for an aircraft with an integrated electrical system architecture that has at least one electrical power source aboard the aircraft, comprising:
a primary power distribution assembly (PDA) aboard the aircraft for each electrical power source that distributes DC power of high electrical potential to a single corresponding primary bus; and
at least one secondary power distribution assembly (SPDA) aboard the aircraft for each PDA that comprises a power converter that receives only DC power of high electrical potential on the single corresponding primary bus, simultaneously converts it to multiple types of power, wherein two types of converted power comprise AC and DC power of lower electrical potential and distributes the converted AC and DC power of lower electrical potential to at least some respective electrical loads for each SPDA.

### Claim 20 (depends on 19)

The EPGS of claim 19, wherein each power converter comprises a DC/AC and DC/DC converter.