Space Mission Energy Management Architecture

Abstract

A system operating in a spacecraft includes a tank storing a propellant, a thermal receiver configured to change the propellant from a first phase to a second phase by providing heat to the propellant, and an energy conversion device fluidically coupled to the tank and configured to generate electric energy using the propellant in the second phase.

What is claimed: 
     
         1 . A system operating in a spacecraft, the system comprising:
 a tank storing a propellant;   a thermal receiver configured to change the propellant from a first phase to a second phase by providing heat to the propellant; and   an energy conversion device fluidically coupled to the tank and configured to generate electric energy using the propellant in the second phase.   
     
     
         2 . The system of  claim 1 , wherein the thermal receiver converts solar radiation to heat, and wherein the system further comprises a solar collector providing the solar radiation to the thermal receiver. 
     
     
         3 . The system of  claim 1 , wherein the tank includes the thermal receiver, and wherein the tank is insulated to reduce the loss of propellant heat. 
     
     
         4 . The system of  claim 3 , wherein the tank is expandable. 
     
     
         5 . The system of  claim 1 , wherein the energy conversion device is a turbine, and wherein the system further comprises a turbine outlet configured to return the propellant to the tank. 
     
     
         6 . The system of  claim 1 , wherein the energy conversion device is a turbine, and wherein the system further comprises (i) a thruster and (ii) a turbine outlet configured to guide the propellant to the thruster. 
     
     
         7 . The system of  claim 1 , further comprising a thruster, wherein the energy conversion device supplies electricity for powering the thruster. 
     
     
         8 . The system of  claim 7 , wherein the thruster is a microwave electrothermal thruster, and wherein the energy conversion device supplies electricity for powering a microwave source of the microwave electrothermal thruster. 
     
     
         9 . The system of  claim 1 , further comprising an electric energy storage device, wherein the energy conversion device charges the electric energy storage device. 
     
     
         10 . The system of  claim 1 , wherein the propellant is water. 
     
     
         11 . The system of  claim 1 , wherein the first phase is a liquid phase and the second phase is a vapor phase. 
     
     
         12 . The system of  claim 1 , further comprising:
 a thruster fluidically coupled to the tank and configured to generate thrust using the propellant in the second phase; and   a controller configured to selectively direct the propellant in the second phase to either the energy conversion device or the thruster.   
     
     
         13 . A method implemented in a spacecraft, the method comprising:
 storing a propellant in a tank;   changing the propellant from a first phase to a second phase by providing heat to the propellant via a thermal receiver; and   generating, by an energy conversion device fluidically coupled to the tank, electric energy using the propellant in the second phase.   
     
     
         14 . The method of  claim 13 , wherein changing the propellant from the first phase to the second phase includes converting solar radiation to heat, and wherein the method further comprises providing the solar radiation to the thermal receiver via a solar collector. 
     
     
         15 . The method of  claim 13 , wherein the energy conversion device is a turbine, and wherein the method further comprises returning the propellant to the tank via an outlet of the turbine. 
     
     
         16 . The method of  claim 13 , wherein the energy conversion device is a turbine, and wherein the method further comprises guiding the propellant to a thruster via an outlet of the turbine. 
     
     
         17 . The method of  claim 13 , further comprising supplying, via the energy conversion device, electricity for powering a thruster. 
     
     
         18 . The method of  claim 17 , wherein the thruster is a microwave electrothermal thruster, and supplying the electricity for powering the thruster includes supplying the electricity for powering a microwave source of the microwave electrothermal thruster. 
     
     
         19 . The method of  claim 13 , further comprising charging, via the energy conversion device, an electric energy storage device. 
     
     
         20 . The method of  claim 13 , wherein the first phase is a liquid phase and the second phase is a vapor phase. 
     
     
         21 . The method of  claim 13 , further comprising:
 selectively directing the propellant in the second phase to either (i) the energy conversion device or (ii) a thruster fluidically coupled to the tank and configured to generate thrust using the propellant in the second phase.