US 12,442,350 B2
Small satellite propulsion system utilizing liquid propellant ullage vapor
Brandie L Rhodes, Redondo Beach, CA (US)
Assigned to THE AEROSPACE CORPORATION, El Segundo, CA (US)
Filed by The Aerospace Corporation, El Segundo, CA (US)
Filed on Jun. 16, 2016, as Appl. No. 15/184,854.
Prior Publication US 2017/0363044 A1, Dec. 21, 2017
Int. Cl. F02K 9/68 (2006.01); F02K 9/42 (2006.01); F02K 9/54 (2006.01); F02K 9/58 (2006.01); F02K 9/60 (2006.01)
CPC F02K 9/58 (2013.01) [F02K 9/425 (2013.01); F02K 9/54 (2013.01); F02K 9/605 (2013.01); F02K 9/68 (2013.01)] 24 Claims
OG exemplary drawing
 
1. An apparatus, comprising:
a propellant tank comprising liquid propellant with a reactive vapor phase,
a catalyst located downstream of the propellant tank along a vapor flow path, wherein
the propellant tank is configured to be selectively exposed to the pressure of space, generating a pressure differential causing a flow of vapor from the propellant tank and through a valve, a membrane, a collection of tubes, or a combination thereof,
to interact with the catalyst to generate thrust while maintaining the liquid propellant in the propellant tank; and
a propellant management device configured to prevent the liquid propellant from escaping the propellant tank and propagating through the apparatus.