Abstract: A liquid propellant supply system (10) according to the invention is electrical in nature and avoids the need for a gas generator and a turbine assembly. In particular, the system (10) includes an electrical power source (12), a controller (14) and a motor (18) for driving the pump (20). The electrical power source (12) provides electrical power sufficient for high power, limited duration applications such as for launch vehicle applications. For launch vehicle applications, the power source (12) is preferably capable of providing very high power for at least 60 seconds. A number of different types of electrical power sources may be employed in this regard. For example, the power source (12) may include high energy density batteries, supercapacitors, or counter rotating flywheels. Multiple counter rotating motors may be employed in order to minimize precessional forces.

Abstract: The invention is a thermal battery system. In detail, the battery system includes housing. A plurality of battery cells containing an electrolyte that is in a non-operating condition at ambient temperatures and in an operating at condition at elevated temperatures is mounted within the housing. A wire heating assembly is mounted within the housing for heating the electrolyte to operating temperatures, upon the application of electric power thereto. Preferably, the heating assembly comprises a plurality of heating coils wound about the battery cells.