Embedded electrospray thruster
View Patent ↗An electrospray thruster with integrated propellant storage directly embedded into small satellite structural elements integrates the volume of the thruster into the volume of the rail.
1. A satellite, comprising:
an electrospray thruster embedded in an opening of a flat face of a structure of the satellite; and
the electrospray thruster comprising:
an insulated casing flush with the flat face;
an emitter array seated within the insulated casing;
an extractor grid spaced from the emitter array within the insulated casing, the extractor grid flush with the flat face; and
a ground plate seated within the insulated casing and surrounding the extractor grid, the ground plate flush with the flat face.
2. The satellite of claim 1 , wherein the satellite is a CubeSat and the structure is a CubeSat rail.
3. The satellite of claim 1 , wherein the electrospray thruster is embedded in a propellant reservoir formed in the structure of the satellite.
4. The satellite of claim 1 , wherein the insulated casing comprises a stepped shape configured to provide spacing between the emitter array and the extractor grid.
5. The satellite of claim 1 , wherein the insulated casing is embedded within a propellant reservoir formed in the structure of the satellite.
6. The satellite of claim 1 , wherein multiple electrospray thrusters are embedded in multiple faces of the structure at orthogonal placement for 3-axis attitude control.
7. The satellite of claim 1 , wherein multiple electrospray thrusters are embedded in a single face of the structure for linear thrust.
8. The satellite of claim 1 , wherein the electrospray thruster embedded in the structure of the satellite does not increase a volume of the structure.
9. The satellite of claim 1 , wherein the electrospray thruster is embedded in a propellant reservoir formed in the structure of the satellite and wherein the insulated casing seals the opening to seal in propellent contained within the propellant reservoir.
10. The satellite of claim 1 , wherein the extractor grid and the ground plate are electrically neutral with the structure of the satellite.
11. The satellite of claim 1 , wherein the insulated casing provides electrical isolation for the emitter array relative to the structure of the satellite.
12. The satellite of claim 1 , wherein the insulated casing comprises a first shoulder for supporting the emitter array and a second shoulder for supporting the extractor grid and the ground plate, the first shoulder spaced from the second shoulder.
13. A method of propelling a satellite, comprising:
embedding an electrospray thruster in an opening of a flat face of a structure of the satellite, wherein the electrospray thruster comprises an insulated casing flush with the flat face, an emitter array seated within the insulated casing, an extractor grid spaced from the emitter array within the insulated casing, the extractor grid flush with the flat face, and a ground plate seated within the insulated casing and surrounding the extractor grid, the ground plate flush with the flat face; and
operating the electrospray thruster.
14. The method of claim 13 , wherein the electrospray thruster is embedded in a propellant reservoir formed in the structure of the satellite.
15. The method of claim 13 , further comprising spacing the emitter array from the extractor grid with a stepped shape of the insulated casing.
16. The method of claim 13 , wherein the embedding an electrospray thruster comprises embedding the insulated casing within a propellant reservoir formed in the structure of the satellite and further comprising sealing the opening with the insulated casing to seal in propellant contained within the propellant reservoir.
17. The method of claim 13 , wherein the insulated casing is embedded within a propellant reservoir formed in the structure of the satellite.
18. The method of claim 13 , further comprising arranging multiple electrospray thrusters embedded in multiple faces of the structure to provide 3-axis attitude control.
19. The method of claim 13 , further comprising arranging multiple electrospray thrusters embedded in a single face of the structure to provide linear thrust.
20. The method of claim 13 , further comprising electrically isolating the electrospray thruster relative to the structure of the satellite with the insulated casing.