US 11,945,606 B1
Electric propulsion based spacecraft propulsion systems and methods utilizing multiple propellants
Gordon C. Wu, Melbourne, FL (US); Derek Chan, Boulder, CO (US); and William D. Deininger, Lafayette, CO (US)
Assigned to Ball Aerospace & Technologies Corp., Boulder, CO (US)
Filed by Ball Aerospace & Technologies Corp., Boulder, CO (US)
Filed on Oct. 18, 2022, as Appl. No. 17/967,941.
Claims priority of provisional application 63/257,255, filed on Oct. 19, 2021.
Int. Cl. B64G 1/40 (2006.01); B64G 1/26 (2006.01)
CPC B64G 1/402 (2013.01) [B64G 1/26 (2013.01); B64G 1/405 (2013.01); B64G 1/411 (2023.08); B64G 1/413 (2023.08); B64G 1/415 (2023.08)] 20 Claims
OG exemplary drawing
 
1. A propulsion system, comprising:
an electric propulsion thruster;
a first storage tank, the first storage tank containing a metallic propellant;
a second storage tank, the second storage tank containing a non-metallic propellant;
a first metallic propellant supply valve, wherein the first metallic propellant supply valve can be operated to selectively provide metallic propellant from the first storage tank to the electric propulsion thruster and thereby generate thrust;
a first non-metallic propellant supply valve, wherein the first non-metallic propellant supply valve can be operated to selectively provide non-metallic propellant from the second storage tank to the electric propulsion thruster and thereby generate thrust; and
a control system, wherein the first metallic propellant supply valve is operated by the control system to supply metallic propellant to the electric propulsion thruster during an operational phase in which an instrument that is sensitive to the metallic propellant is not in a vulnerable state, and wherein the first non-metallic propellant supply valve is operated by the control system to supply non-metallic propellant to the electric propulsion thruster during an operational phase in which an instrument that is sensitive to the metallic propellant is in a vulnerable state.