SHARED THERMAL CAPACITOR IN A MULTI-THRUSTER SYSTEM
A spacecraft propulsion system comprises an attitude adjustment thruster system with multiple thrusters ( 488 a - d ) receiving heated propellant via a shared thermal capacitance block ( 275 ). The thermal capacitance block ( 275 ) receives energy from a solar concentrator ( 320 ) and stores the heat.
1 . A spacecraft maneuvering system comprising:
a propellant tank;
a shared thermal capacitor including a material configured to store thermal energy, the shared thermal capacitor configured to (i) receive, via a plurality of ingress ports, a propellant for a plurality of respective fluidic channels, (ii) transfer the stored thermal energy to the propellant in the plurality of fluidic channels, and (iii) output the propellant from the plurality of fluidic channels via a plurality of a respective egress ports;
a plurality of valves configured to restrict an amount of propellant directed to the respective ingress ports; and
a controller configured to control the plurality of the valves to change flow rates through the plurality of the fluidic channels in response to signals indicative of intended spacecraft maneuvers.
2 . The spacecraft maneuvering system of claim 1 , further comprising:
a plurality of thrusters fluidicly coupled to respective ones of the plurality of egress ports.
3 . The spacecraft maneuvering system of claim 2 , wherein the shared thermal capacitor further includes a secondary fluidic channel coupled to a non-thruster component.
4 . The spacecraft maneuvering system of claim 3 , wherein the secondary fluidic channel is configured to receive a fluid other than the propellant.
5 . The spacecraft maneuvering system of claim 3 , wherein the secondary fluidic channel is coupled to a turbine for generating electricity.
6 . The spacecraft maneuvering system of claim 2 , wherein the thermal capacitor is configured to transfer, to the propellant, an amount of thermal energy sufficient to operate the corresponding thruster.
7 . The spacecraft maneuvering system of claim 1 , wherein the controller is configured to adjust the flow rates in view of a temperature of the shared thermal capacitor.
8 . The spacecraft maneuvering system of claim 1 , wherein the controller is configured to adjust the flow rates in view of a temperature gradient of the shared thermal capacitor.
9 . The spacecraft maneuvering system of claim 1 , further comprising:
one or more reflectors to configured to reflect energy in an infrared range radiated by the thermal capacitor block back to the thermal capacitor block.
10 . The spacecraft maneuvering system of claim 1 , where the plurality of fluidic channels are integrated into the thermal capacitor.
11 . The spacecraft maneuvering system of claim 1 , wherein each of the one or more fluidic channels has a helical shape.
12 . A method of maneuvering a spacecraft, the method comprising:
directing a propellant from a propellant tank to a plurality of fluidic channels in thermal communication with a shared thermal capacitor, via a plurality of respective valves, including controlling, by a controller, flow rates through the valves in accordance with intended spacecraft maneuvers;
transferring thermal energy stored in a material of the thermal capacitor to the propellant in the plurality of fluidic channels; and
directing the propellant from the plurality of fluidic channels to respective ones of a plurality of thrusters.
13 . The method of claim 12 , further comprising:
transferring, by the thermal capacitor, an amount of thermal energy sufficient to operate the corresponding thruster.
14 . The method of claim 12 , further comprising adjusting the flow rates in view of a temperature of the shared thermal capacitor.
15 . The method of claim 12 , further comprising adjusting the flow rates in view of a temperature gradient of the shared thermal capacitor.
16 . The method of claim 12 , wherein the plurality of fluidic channels are integrated into the thermal capacitor.
17 . The method of claim 12 , further comprising:
directing a working fluid other than the propellant to a secondary fluidic channel in thermal communication with the thermal capacitor.
18 . The method of claim 17 , further comprising:
directing the working fluid from the secondary fluidic channel to a turbine for generating electricity.
19 . The method of claim 12 , further comprising:
using one or more reflectors to reflect energy in an infrared range radiated by the thermal capacitor block back to the thermal capacitor.
20 . The method of claim 12 , further comprising:
operating in the low-pressure environment with a pressure of less than 0.01 Atm, to reduce heat loss through convection.