Reconfigurable power processing unit for spacecraft operations
A reconfigurable power processing unit for a spacecraft including a plurality of power modules. Each of the power modules includes a first power source and a second power source. The first power source and the second power source are configured to be in series in a first state and in parallel in a second state. A plurality of contactors connect each power module to at least one of another power module in the plurality of power modules and a power processing output and are configured to control the state of the power modules.
1. A reconfigurable power processing unit for a spacecraft comprising:
a plurality of power modules, each power module of the plurality of power modules including a first direct current power source and a second direct current power source that are configured to be connected in series with each other in a first state and are configured to be connected in parallel with each other in a second state;
a plurality of contactors connecting each power module to at least one of another power module in the plurality of power modules; and
a controller configured to provide a control signal to each contactor of the plurality of contactors to control the state of the power modules;
wherein, in the first state, first and second power modules of the plurality of power modules are arranged in series between first and second output lines of the reconfigurable power processing unit, and third and fourth power modules of the plurality of power modules are arranged in series between the first and second output lines;
wherein, in the second state, the first and second direct current power sources of each said power module are (i) connected in parallel with each other and (ii) connected in parallel with the first and second direct current power sources of all other power modules across the first and second input lines;
wherein the reconfigurable power processing unit provides direct current only at a first voltage level when the plurality of power modules are in the first state, and the reconfigurable power processing unit provides direct current only at a lower second voltage level when the plurality of power modules are in the second state; and
wherein the controller is configured to transition the plurality of contactors from the first state to the second state by depowering the reconfigurable power processing unit, transitioning a state of each contactor of the plurality of contactors, and repowering the reconfigurable power processing unit.
2. The reconfigurable power processing unit of claim 1 , wherein the plurality of contactors are configured to place a first module of the plurality of power modules in series with a second power module in the plurality of power modules in the first state.
3. The reconfigurable power processing unit of claim 1 , wherein the plurality of contactors are configured to place each first direct current power source in parallel with each other first direct current power source and each second direct current power source in parallel with each other second direct current power source in the second state.
4. The reconfigurable power processing unit of claim 1 , wherein each of the contactors in the plurality of contactors is one of a mechanical relay, a semiconductor switch, or an electronic logic circuit.
5. The reconfigurable power processing unit of claim 1 , wherein each of the contactors in the plurality of contactors is a mechanical relay.
6. The reconfigurable power processing unit of claim 1 , wherein the second state is a low voltage supply state.
7. The reconfigurable power processing unit of claim 1 , wherein the first direct current power source in each power module in the plurality of power modules is a 150 volt 11 amp power source.
8. The reconfigurable power processing unit of claim 7 , wherein the first state is 600V, 22 A high voltage power supply.
9. The reconfigurable power processing unit of claim 7 , wherein the second state is 150V, 88 A low voltage power supply.
10. The reconfigurable power processing unit of claim 1 , wherein each power module in the plurality of power modules is identical.
11. The reconfigurable power processing unit of claim 1 , wherein the plurality of power modules includes at least four power modules.
12. The reconfigurable power processing unit of claim 11 , wherein the plurality of power modules includes exactly four power modules.
13. A method for operating a power processing unit comprising:
placing the power processing unit in a first state in which the power processing unit provides high voltage direct current to a switched power bus for a duration dictated by a first load;
powering down the power processing unit;
transitioning the power processing unit from the first state to a second state by switching a state of each contactor in a plurality of contactors, where the power processing unit provides low voltage direct current to the switched power bus when in the second state;
powering up the power processing unit; and
providing low voltage direct current to the switched power bus;
wherein in the first state, first and second power modules of a plurality of power modules are arrange in series between first and second output lines of the power processing unit, and third and fourth power modules of the plurality of power modules are arranged in series between the first and second output lines; and
wherein, in the second state, first and second direct current power sources of each said power module are (i) connected in parallel with each other and (ii) connected in parallel with first and second direct current power sources of all other power modules across the first and second input lines.
14. The method of claim 13 , wherein the first load is an electric thruster, and the duration is a duration of thruster operations.
15. The method of claim 13 , wherein providing low voltage power to the switched power bus comprises providing low voltage power to at least one on board electric system of a spacecraft through the switched power bus.
16. A spacecraft power distribution system comprising:
a power processing unit configured to provide high voltage direct current power to a switched power bus in a first state and low voltage direct current power to the switched power bus in a second state;
at least one electronic thruster connected to the switched power bus and configured to receive power during the first state;
at least one on-board electrical system connected to the switched power bus and configured to receive power during the second state; and
a controller configured to control the state of the power processing unit;
wherein the power processing unit comprises a plurality of power modules, each power module of the plurality of power modules including a first direct current power source and a second direct current power source that are configured to be connected in series with each other in the first state and are configured to be connected in parallel with each other in the second state;
wherein, in the first state, first and second power modules of the plurality of power modules are arranged in series between first and second output lines of the power processing unit, and third and fourth power modules of the plurality of power modules are arranged in series between the first and second output lines;
wherein, in the second state, the first and second power sources of each said power module are (i) connected in parallel with each other and (ii) connected in parallel with the first and second power sources of all other power modules across the first and second input lines; and
wherein the controller is configured to transition the power processing unit from the first state to the second state by depowering the power processing unit, transitioning the power processing unit from the first state to the second state, and repowering the power processing unit.
17. The spacecraft power distribution system of claim 16 , wherein the power processing unit includes:
a plurality of contactors connecting each power module to at least one of another power module in the plurality of power modules and a power processing output and configured to control the state of the power modules.
18. The spacecraft power distribution system of claim 17 , wherein each power module in the plurality of power modules is identical.