초록 ▼

The present example provides aircraft integrated aircraft utility management and power distribution systems. Included are three exemplary implementations of aircraft power management systems (a DC power distribution system, a utility management system, and a combined system) that may utilize the lik

The present example provides aircraft integrated aircraft utility management and power distribution systems. Included are three exemplary implementations of aircraft power management systems (a DC power distribution system, a utility management system, and a combined system) that may utilize the like architecture, technologies, and components advantageously. A DC power distribution system can include two parts: primary DC power distribution and secondary DC power distribution systems. The utility management system integrates aircraft sub functions and utilities into one fault tolerant system. The systems described makes use of secondary power distribution units of a modularized design, including standard I/O modules, power modules, and aircraft computing modules.

대표청구항 ▼

1. An aircraft utilities and DC power distribution system comprising: a primary power distribution unit coupled between a plurality of sources and two power feeders; anda secondary power distribution unit coupled to the primary power distribution unit through both of the two power feeders, and inclu

1. An aircraft utilities and DC power distribution system comprising: a primary power distribution unit coupled between a plurality of sources and two power feeders; anda secondary power distribution unit coupled to the primary power distribution unit through both of the two power feeders, and including: a power module;an I/O module; anda computing modulewhereby DC power from the plurality of sources may be applied to a plurality of aircraft power loads through the primary power distribution unit and the secondary power distribution unit. 2. The aircraft utilities and DC power distribution system of claim 1, further including current sensors coupled to each one of the two power feeders. 3. The aircraft utilities and DC power distribution system of claim 1, in which the plurality of sources includes a DC power generator. 4. The aircraft utilities and DC power distribution system of claim 1, in which the plurality of sources includes at least two DC power generators. 5. The aircraft utilities and DC power distribution system of claim 1, in which the plurality of sources includes a battery. 6. The aircraft utilities and DC power distribution system of claim 1, further comprising an additional secondary power distribution unit disposed in an aft section of an aircraft, and the secondary power distribution unit is disposed in a forward section of the aircraft. 7. An aircraft DC power management system comprising: at least one primary power distribution unit coupled to a plurality of power sources, and including a plurality of electronically activated contactors for coupling each of the plurality of power sources to an output of the primary power distribution unit, and at least one current sensing element disposed in a terminal lead of a contactor for determining a failure condition; andat least one secondary power distribution unit communicatively coupled to the at least one primary power distribution unit, and coupled to the output of the primary power distribution unit such that power from any one of the plurality of power sources may be coupled to an electrical load through the at least one primary power distribution unit and the at least one secondary power distribution unit under the direction of the at least one secondary power distribution unit. 8. The aircraft DC power management system of claim 7 in which the at least one secondary power distribution unit further includes: a power module;an I/O module; anda computing module communicatively coupled to the power module, the I/O module and the at least one primary power distribution unit so that power from any one of the plurality of power sources may be routed to the load based upon detection of a failure, an operators manual override or other conditions programmed into the computing module. 9. An aircraft DC power management system comprising: a first primary power distribution unit coupled to a first plurality of power sources, and including a first plurality of electronically activated contactors for coupling each of the first plurality of power sources to an output of the first primary power distribution unit, and at least one first current sensing element disposed in a terminal lead of a first contactor for determining a current output condition;a second primary power distribution unit coupled to a second plurality of power sources, and including a second plurality of electronically activated contactors for coupling each of the second plurality of power sources to an output of the second primary power distribution unit, and at least one second current sensing element disposed in a terminal lead of a second contactor for determining a failure condition; andat least one secondary power distribution unit communicatively coupled to the first primary power distribution unit and to the second primary power distribution unit, and coupled to the output of the first and second primary power distribution unit such that power from any one of the first or second plurality of power sources may be coupled to an electrical load through one of the first or second primary power distribution unit and the at least one secondary power distribution unit under the direction of the at least one secondary power distribution unit. 10. The aircraft DC power management system of claim 9 in which the at least one secondary power distribution unit further includes: a power module;an I/O module; anda computing module communicatively coupled to the power module, the I/O module, the first primary power distribution unit and the second primary power distribution unit so that power from any one of the first or second plurality of power sources may be routed to the load based upon detection of a failure, an operating condition, an operators manual override or other conditions programmed into the computing module. 11. The aircraft DC power management system of claim 10 wherein the power module, I/O module and computing module are interconnected via at least one serial digital bus. 12. The aircraft DC power management system of claim 11 wherein the at least one serial digital bus comprises three independent serial digital busses. 13. The aircraft DC power management system of claim 9 wherein the first primary power distribution unit has one output and the second primary power distribution unit has one output. 14. The aircraft DC power management system of claim 13 further comprises a standby battery coupled to both the output from the first primary power distribution unit and the output from the second primary power distribution unit. 15. The aircraft DC power management system of claim 9 wherein the first primary power distribution unit has a first power line output and a second power line output, the second primary power distribution unit has a first power line output and a second power line output. 16. The aircraft DC power management system of claim 15 wherein the at least one secondary power distribution unit comprises a first plurality of secondary power distribution units and a second plurality of secondary power distribution units, the first plurality of secondary power distribution units couples to both the first power line output from the first primary power distribution unit and the second power line output from the second primary power distribution unit, the second plurality of secondary power distribution units couples to both the second power line output from the first primary power distribution unit and the first power line output from the second primary power distribution unit. 17. The aircraft DC power management system of claim 15 further comprises a standby battery coupled to both the first power line output from the first primary power distribution unit and the first power line output from the second primary power distribution unit. 18. The aircraft DC power management system of claim 9 wherein the first primary power distribution unit and the second primary power distribution unit are coupled via a bus tie. 19. The aircraft DC power management system of claim 9 wherein the at least one secondary power distribution unit comprises internal fuses to prevent common mode failures within the secondary power distribution units from causing catastrophic failure of the entire aircraft DC power management system. 20. The aircraft DC power management system of claim 9 wherein the at least one secondary power distribution unit comprises internal filters to suppress interfering signals. 21. The aircraft DC power management system of claim 9 wherein both the first primary power distribution unit and the second primary power distribution unit comprise a manual controller, the manual controller being normally inactive but having ability to control any contactors within the first or the second primary power unit.