Propulsion system for space vehicles
View Patent ↗An electric propulsion module coupled to a spacecraft capable of providing thrust at a level required for multi-burn orbit transfer is disclosed herein. The electric propulsion system includes an electric propulsion thruster, a propellant tank and an energy storage device. In one form the energy storage device is a battery operable to provide sufficient power to maneuver the spacecraft quickly to avoid space debris and/or move to a different orbit through a multi-burn thrust procedure.
1. A spacecraft system comprising:
a spacecraft configured to take off from earth and move in outer space;
a primary electric propulsion module including:
a primary battery connected to the spacecraft;
a primary photovoltaic array (PV Array) operably coupled to the primary battery; and
a primary electric propulsion system operably coupled to the primary PV Array; and
an auxiliary propulsion module coupled to the spacecraft;
wherein the auxiliary propulsion module includes:
an energy storage device;
a propellant tank; and
an auxiliary electric propulsion system with a thruster having a thrust rating higher than the primary electric propulsion system, the auxiliary electric propulsion system configured to maneuver the spacecraft into another orbit via a Hohmann multi-burn transfer.
2. The system of claim 1 , wherein the energy storage device is a battery.
3. The system of claim 2 , wherein the battery is a lithium based battery.
4. The system of claim 1 , wherein the energy storage device is one of a flywheel and a thermal storage medium.
5. The system of claim 1 , wherein the electric propulsion thruster is a Hall thruster with throttling capability.
6. The system of claim 1 , wherein the electric propulsion thruster is an Ion thruster with throttling capability.
7. The system of claim 1 , wherein the auxiliary propulsion module includes an auxiliary photovoltaic array capable of receiving energy and transferring energy to the energy storage device.
8. The system of claim 7 , wherein the power provided by the auxiliary photovoltaic array and the energy storage device is at least five (5) times the power output of the spacecraft PV array.
9. The system of claim 1 , wherein the propellant is ejected at 5 Km/s or greater from the auxiliary electric propulsion thruster.
10. The system of claim 1 , further comprising a coupling configured to releasably lock the auxiliary propulsion module to the spacecraft.
11. The system of claim 10 , wherein the coupling is configured to release the auxiliary propulsion module from the spacecraft and couple to another spacecraft.
12. A space propulsion system for a spacecraft comprising:
a primary electric propulsion system with a primary thruster; and
an auxiliary electric propulsion system including:
an auxiliary energy storage device;
an auxiliary energy collecting device;
an auxiliary propellant tank;
an auxiliary electric propulsion thruster having a thrust rating higher than the primary electric propulsion thruster, the auxiliary electric propulsion thruster being capable of maneuvering the spacecraft into another orbit via multi-burn transfer; and
a coupling mechanism configured to releasably connect the auxiliary space propulsion system to the spacecraft.
13. The space propulsion system of claim 12 , wherein the coupling mechanism permits decoupling the auxiliary electric propulsion system from one spacecraft and couple the auxiliary electric propulsion system to another spacecraft in space.
14. The space propulsion system of claim 12 , wherein the energy storage device is battery.
15. The space propulsion system of claim 12 further comprising xenon gas propellant stored in the propellant tank.
16. The space propulsion system of claim 12 , wherein the coupling mechanism includes a mechanical connection, an electrical connection and/or a data communication connection.
17. The space propulsion system of claim 12 , wherein the combined energy capacity of the energy storage device and the energy collecting device is at least five (5) times the energy collected by the energy collecting device in one (1) hour.
18. A method comprising:
moving a spacecraft from earth to an orbit in outer space;
moving the spacecraft in outer space with a primary electric propulsion system coupled to the spacecraft;
maneuvering the spacecraft from the orbit to avoid space debris or to another orbit via Hohmann transfer with an auxiliary electric propulsion system releasably connected to the spacecraft, the auxiliary electric propulsion system having a higher power output than the primary electric propulsion system; and
wherein the maneuvering includes storing electrical energy in an auxiliary power source and providing at least five (5) times the power of a power output of an energy collection device electrically connected to an auxiliary electric propulsion thruster.
19. The method of claim 18 , wherein the energy collection device is an auxiliary photovoltaic array.
20. The method of claim 18 , wherein the auxiliary power source includes the energy collection device and an auxiliary battery operably coupled to the auxiliary electric propulsion thruster.
21. The method of claim 18 further comprising using all of the stored energy within a selected burn interval.