MODULAR ELECTRICAL POWER SUBSYSTEM ARCHITECTURE

An electrical power system has a dual battery configuration that enables sufficient power supply for a spacecraft bus and a payload module being carried by the spacecraft. During a sunlight power mode, power is drawn from a solar array of the bus to power a low-discharge payload of the spacecraft an...

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Bibliographische Detailangaben
Hauptverfasser:	Cosner, Christopher M, Wootan, John J, Stickelmaier, John F
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT AVIATION BASIC ELECTRIC ELEMENTS CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER CONVERSION OR DISTRIBUTION OF ELECTRIC POWER COSMONAUTICS ELECTRICITY GENERATION GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRA-REDRADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, E.G. USINGPHOTOVOLTAIC [PV] MODULES PERFORMING OPERATIONS PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSIONOF CHEMICAL INTO ELECTRICAL ENERGY SYSTEMS FOR STORING ELECTRIC ENERGY TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR
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Beschreibung
Zusammenfassung:	An electrical power system has a dual battery configuration that enables sufficient power supply for a spacecraft bus and a payload module being carried by the spacecraft. During a sunlight power mode, power is drawn from a solar array of the bus to power a low-discharge payload of the spacecraft and a high-discharge payload of a payload module. During the sunlight power mode, a low rate discharge battery and a high rate discharge battery are charged by a battery charge management unit of the spacecraft bus. During an eclipse power mode, the low rate discharge battery powers the low-discharge payload of the spacecraft and the high rate discharge battery powers the high-discharge payload of the payload module. The high-rate discharge battery may also be used to power the high-rate discharge payload in the sunlight power mode to meet its high current demands to meet a flexible mission operations.