Granted Patent B2

US 12,523,200 · App. 17/548,446 · Granted Jan 13, 2026

Inventors: Jose Lino Vasconcelos da Costa (Tullahoma, TN); Trevor Michael Moeller (Manchester, TN); Justin Michael Jones (Cleveland, TN); Brian Keith Canfield (Tullahoma, TN); Alexander Yuryevich Terekhov (Hermitage, TN); Joshua Harrison Howell (Franklin, TN)

Assignee: University of Tennessee Research Foundation

F03H1/0037B64G1/413

Abstract

Claims (82)

1 . An electrospray thruster comprising:

a reservoir containing a fluid;

an electrospray emitter comprising:

a dielectric comprising one or more channels formed through a thickness of the dielectric; and

an extraction electrode, wherein the extraction electrode is positioned on an opposite side of the dielectric from the reservoir, in a direction of the thickness of the dielectric;

wherein a first end of each of the one or more channels is in fluidic communication, at an upstream surface of the dielectric, with the fluid contained within the reservoir;

wherein a second end of each of the one or more channels is in fluidic communication, at a downstream surface of the dielectric, with an external atmosphere surrounding the thruster;

wherein the thruster is configured such that, when an electrospray onset voltage difference is applied between the extraction electrode and the fluid, mass from the fluid is ejected from the one or more channels to generate thrust;

wherein the one or more channels are a plurality of channels arranged in an array, each of the channels being formed as a microcapillary with a length-to-width ratio of at least 100:1 and wherein a length of the channels is at least 100 μm;

wherein the extraction electrode comprises an extraction grid;

wherein the dielectric comprises, for each of the plurality of channels, a surface cavity that is formed as a recess extending into the dielectric from the downstream surface, each surface cavity being coaxial with one of the plurality of channels to form a channel-surface cavity pair;

wherein the extraction grid comprises openings that are arranged such that each opening is positioned coaxial with a corresponding channel-surface cavity pair; and

wherein each of the openings of the extraction grid have a diameter that is the same as, or greater than, a diameter of the corresponding surface cavity at the downstream surface of the dielectric.

2 . The electrospray thruster of claim 1 , wherein the fluid comprises an ionic liquid (IL) propellant.

3 . The electrospray thruster of claim 1 , wherein the dielectric comprises a dielectric material with a relative permittivity of less than 12.

4 . The electrospray thruster of claim 1 , wherein the electrospray onset voltage difference is less than 1,000 Volts (V).

5 . The electrospray thruster of claim 1 , wherein a spacing between adjacent channels in the array is from 0.5 to 3 times the length of the channels.

6 . The electrospray thruster of claim 1 , wherein the extraction grid comprises openings that are arranged such that each opening is positioned coaxial with a corresponding one of the plurality of channels.

7 . The electrospray thruster of claim 1 , wherein:

for each channel, an extraction distance (d) is defined as a distance between the floor of the corresponding surface cavity and the extraction grid; and

each corresponding surface cavity has a diameter (m) that is greater than 2 (d) to minimize an electrospray onset voltage and an applied voltage.

8 . The electrospray thruster of claim 7 , wherein the extraction grid is in direct contact with the downstream surface of the dielectric, in a manner of a conformal coating.

9 . The electrospray thruster of claim 7 , wherein the extraction grid is spaced apart from the downstream surface of the dielectric by a finite distance.

10 . The electrospray thruster of claim 1 , wherein the extraction grid is in direct contact with the downstream surface of the dielectric, in a manner of a conformal coating.

11 . The electrospray thruster of claim 1 , wherein the extraction grid is spaced apart from the downstream surface of the dielectric by a finite distance.

12 . The electrospray thruster of claim 1 , wherein the electrospray thruster comprises a monolithic construction.

13 . A spacecraft and/or satellite comprising at least one electrospray thruster of claim 1 , wherein:

the at least one electrospray thruster is rigidly attached to an outer surface of the spacecraft and/or satellite; and

the at least one electrospray thruster has a monolithic construction.

14 . An electrospray thruster comprising:

at least one reservoir containing a fluid;

at least first and second electrospray emitters, each comprising:

a dielectric comprising one or more channels formed through a thickness of the dielectric; and

an extraction electrode, wherein the extraction electrode is positioned on an opposite side of the dielectric from the reservoir, in a direction of the thickness of the dielectric;

wherein a first end of each of the channels is in fluidic communication, at an upstream surface of the dielectric, with the fluid contained within the reservoir; and

wherein a second end of each of the channels is in fluidic communication, at a downstream surface of the dielectric, with an external atmosphere surrounding the thruster;

wherein the first and second electrospray emitters are arranged adjacent to each other on opposite sides of a plane and are inclined, relative to the plane perpendicular to a longitudinal direction, at opposite angles from each other;

wherein the first and second electrospray emitters are independently operable from each other; and

wherein the thruster is configured such that:

when the first electrospray emitter is activated by applying an electrospray onset voltage difference between the extraction electrode of the first electrospray emitter and the fluid, the fluid is ejected from the channels of the first electrospray emitter to generate a first thrust, which has a vector inclined relative to the plane at a same angle as the first electrospray emitter; and

when the second electrospray emitter is activated by applying the electrospray onset voltage difference between the extraction electrode of the second electrospray emitter and the fluid, the fluid is ejected from the channels of the second electrospray emitter to generate a second thrust, which has a vector inclined relative to the plane at a same angle as the second electrospray emitter.

15 . The electrospray thruster of claim 14 , wherein:

the fluid comprises an ionic liquid (IL) propellant;

when only the first electrospray emitter is activated, the electrospray thruster is configured to generate a net thrust that causes a rotational moment perpendicular to a first direction;

when only the second electrospray emitter is activated, the electrospray thruster is configured to generate a net thrust that causes a rotational moment perpendicular to a second direction, which is opposite the first direction, relative to an axis of rotation; and

when both the first and second electrospray emitters are activated, the electrospray thruster is configured to generate a net thrust that is substantially in the longitudinal direction with zero rotational moment.

16 . An electrospray thruster comprising:

at least one reservoir containing a fluid;

at least first, second, third, and fourth electrospray emitters, each comprising:

a dielectric comprising one or more channels formed through a thickness of the dielectric; and

an extraction electrode, wherein the extraction electrode is positioned on an opposite side of the dielectric from the reservoir, in a direction of the thickness of the dielectric;

wherein a first end of each of the channels is in fluidic communication, at an upstream surface of the dielectric, with the fluid contained within the reservoir; and

wherein a second end of each of the channels is in fluidic communication, at a downstream surface of the dielectric, with an external atmosphere surrounding the thruster;

wherein the first, second, third, and fourth electrospray emitters are substantially uniformly arranged about a longitudinal axis;

wherein the first and third electrospray emitters define a first electrospray emitter pair and are radially spaced apart from each other by about 180°, such that the first and third electrospray emitters are on opposite sides of the longitudinal axis from each other, and are inclined, relative to a plane that is perpendicular to the longitudinal axis, at opposite angles from each other;

wherein the second electrospray emitter is radially spaced apart from the first and third electrospray emitters by about 90°;

wherein the second and fourth electrospray emitters define a second electrospray emitter pair and are radially spaced apart from each other by about 180°, such that the second and fourth electrospray emitters are on opposite sides of the longitudinal axis from each other, and are inclined, relative to the plane that is perpendicular to the longitudinal axis, at opposite angles from each other;

wherein each of the first, second, third, and fourth electrospray emitters are independently operable from each other; and

wherein the thruster is configured such that:

when the first electrospray emitter is activated by applying an electrospray onset voltage difference between the extraction electrode of the first electrospray emitter and the fluid, the fluid is ejected from the channels of the first electrospray emitter to generate a first thrust, which has a vector inclined relative to the longitudinal axis at a same angle as the first electrospray emitter;

when the second electrospray emitter is activated by applying the electrospray onset voltage difference between the extraction electrode of the second electrospray emitter and the fluid, the fluid is ejected from the channels of the second electrospray emitter to generate a second thrust, which has a vector inclined relative to the longitudinal axis at a same angle as the second electrospray emitter;

when the third electrospray emitter is activated by applying the electrospray onset voltage difference between the extraction electrode of the third electrospray emitter and the fluid, the fluid is ejected from the channels of the third electrospray emitter to generate a third thrust, which has a vector inclined relative to the longitudinal axis at a same angle as the third electrospray emitter; and

when the fourth electrospray emitter is activated by applying the electrospray onset voltage difference between the extraction electrode of the fourth electrospray emitter and the fluid, the fluid is ejected from the channels of the fourth electrospray emitter to generate a fourth thrust, which has a vector inclined relative to the longitudinal axis at a same angle as the fourth electrospray emitter.

17 . The electrospray thruster of claim 16 , wherein:

the fluid comprises an ionic liquid (IL) propellant;

when only the first electrospray emitter is activated, the electrospray thruster is configured to generate a net thrust that causes a rotational moment perpendicular to a first direction;

when only the second electrospray emitter is activated, the electrospray thruster is configured to generate a net thrust that causes a rotational moment perpendicular to a second direction, which is oriented at about 90° relative to the first direction, relative to the longitudinal axis;

when only the third electrospray emitter is activated, the electrospray thruster is configured to generate a net thrust that causes a rotational moment perpendicular to a third direction, which is opposite the first direction, relative to the longitudinal axis;

when only the fourth electrospray emitter is activated, the electrospray thruster is configured to generate a net thrust that causes a rotational moment perpendicular to a fourth direction, which is opposite the second direction, relative to the longitudinal axis; and

when both the first and third electrospray emitters are activated and/or when both the second and fourth electrospray emitters are activated, the electrospray thruster is configured to generate a net thrust that is substantially in a longitudinal direction.

18 . The electrospray thruster of claim 17 , wherein:

the first direction is a positive yaw direction, the second direction is a positive pitch direction, the third direction is a negative yaw direction, and the fourth direction is a negative pitch direction; and

the electrospray thruster is configured to control yaw, pitch, and translator movements.

19 . The electrospray thruster of claim 16 , wherein:

the electrospray onset voltage difference is less than 1,000 Volts (V);

each of the channels for the first, second, third, and fourth electrospray emitters is formed as a microcapillary with a length-to-width ratio of at least 100:1; and

the extraction electrode of each of the first, second, third, and fourth electrospray emitters is an extraction grid comprising a plurality of openings, each opening being substantially coaxial with one of the channels on a same electrospray emitter.

20 . A spacecraft and/or satellite comprising at least one electrospray thruster of claim 16 , wherein:

the at least one electrospray thruster is rigidly attached to an outer surface of the spacecraft and/or satellite; and

the first, second, third, and fourth electrospray emitters have a monolithic construction and either:

the at least one electrospray thruster is in a form of a recess extending inwardly from the outer surface of the spacecraft and/or satellite; or

the at least one electrospray thruster is in a form of a protrusion extending outwardly from the outer surface of the spacecraft and/or satellite.

Assignments (1)

Continuity (2)

References Cited (14)