POWER SYSTEM ARCHITECTURE FOR AIRCRAFT WITH ELECTRICAL ACTUATION

POWER SYSTEM ARCHITECTURE FOR AIRCRAFT WITH ELECTRICAL ACTUATION

An electrical power system (100) for regenerative loads may include a DC bus (110,160) and an electrical actuator load (112,162), where back-driving the electrical actuator load (112,162) generates regenerative electrical energy, and where the electrical actuator load (112,162) is configured to tran...

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Bibliographische Detailangaben
Hauptverfasser: KARIMI, Kamiar J, LIFFRING, Mark E, CURRIER, Thomas F, SOLODOVNIK, Eugene V
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER
CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
COSMONAUTICS
ELECTRICITY
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
GENERATION
PARACHUTES
PERFORMING OPERATIONS
SYSTEMS FOR STORING ELECTRIC ENERGY
TRANSPORTING
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Beschreibung
Zusammenfassung:An electrical power system (100) for regenerative loads may include a DC bus (110,160) and an electrical actuator load (112,162), where back-driving the electrical actuator load (112,162) generates regenerative electrical energy, and where the electrical actuator load (112,162) is configured to transmit the regenerative electrical energy to the DC bus (110,160). The system may also include at least one additional load (114,164), where at least a portion of the regenerative electrical energy is transmitted to the at least one additional load (114,164).