US 11,750,021 B2
Modular electrical power subsystem architecture
Christopher M. Cosner, Manhattan Beach, CA (US); John F. Stickelmaier, Manhattan Beach, CA (US); and John J. Wootan, Hermosa Beach, CA (US)
Assigned to Raytheon Company, Waltham, MA (US)
Filed by Raytheon Company, Waltham, MA (US)
Filed on Nov. 13, 2020, as Appl. No. 17/97,622.
Prior Publication US 2022/0158477 A1, May 19, 2022
Int. Cl. H02J 7/00 (2006.01); H02J 7/35 (2006.01); H02S 40/38 (2014.01); B64G 1/42 (2006.01); B64G 1/44 (2006.01); B64G 1/58 (2006.01); H01M 10/42 (2006.01); H02S 50/00 (2014.01)
CPC H02J 7/35 (2013.01) [B64G 1/425 (2013.01); B64G 1/428 (2013.01); B64G 1/443 (2013.01); B64G 1/58 (2013.01); H01M 10/425 (2013.01); H02J 7/007 (2013.01); H02J 7/0014 (2013.01); H02J 7/0024 (2013.01); H02J 7/0063 (2013.01); H02S 40/38 (2014.12); H02S 50/00 (2013.01); H01M 2010/4271 (2013.01)] 21 Claims
OG exemplary drawing
 
1. An electrical power system for a spacecraft, the electrical power system comprising:
a bus circuit including a first payload, a solar array, a first battery, and a battery charge management unit coupled between the first battery and the solar array; and
a payload module that is carried by the spacecraft, the payload module including a second payload and a second battery that is electrically coupled to the battery charge management unit of the bus circuit;
wherein the electrical power system has a sunlight power mode in which the solar array is operable to power the first payload and the second payload while the first battery and the second battery are charged; and an eclipse power mode in which the first battery is operable to power the first payload, and in which the second battery is operable to power the second payload independently from the bus circuit; and
wherein, during the sunlight power mode, the battery charge management unit controls charging of the first battery and the second battery by the solar array.