Patent
US 10,696,424SPACECRAFT STRUCTURES INCORPORATING GRAPHENE AND OPERATION THEREOF
Vadim KHAYMS, Steven W. SINTON, Peter V. BEDWORTH
LOCKHEED MARTIN CORPORATION·US
Copyright © 2026 Matter42. All rights reserved.
Patent
Atlas literature
Patent
US 10,696,424Claims define the patent's legal scope. Independent claims stand alone; dependent claims (nested) narrow them. Click a claim to expand its dependents.
A spacecraft structure comprising: an electric propulsion system, wherein the electric propulsion system comprises one or more exhaust source points; a functional component, wherein at least one of the one or more exhaust source points is pointed toward the functional component to direct at least a portion of an outflow of the electric propulsion system to impact the functional component; and a graphene coating upon the functional component, wherein the graphene coating overcoats an existing charge control coating upon the functional component. Currently amended
The spacecraft structure of claim 1, wherein the functional component is selected from the group consisting of a solar panel, an optical solar reflector, a radiof r equency reflector, a gold mesh reflector, a solar array, a communication array, an antenna, an optical sensor, a thermal blanket, and any combination thereof. Original
The spacecraft structure of claim 1, wherein the existing charge control coating comprises indium tin oxide or a metal film. Previously presented
The spacecraft structure of claim 1, wherein at least a portion of the graphene coating comprises single-layer graphene. Original
The spacecraft structure of claim 1, wherein the graphene coating comprises a plurality of graphene flakes. Original
The spacecraft structure of claim 1, wherein the graphene coating decreases optical transparency by about 10% or less. Original
The spacecraft structure of claim 1, wherein graphene comprising the graphene coating is grown upon a surface of the functional component. Original
The spacecraft structure of claim 1, wherein graphene comprising the graphene coating is grown upon a secondary substrate and is subsequently transferred to the functional component as a conformal coating. Original
The spacecraft structure of claim 1, wherein the spacecraft structure comprises a satellite. Original
Canceled
Canceled
A method comprising: generating an outflow of energetic particles from an electric propulsion system of a spacecraft structure, the electric propulsion system comprising one or more exhaust source points; and pointing at least one of the one or more exhaust source points toward a functional component to direct at least a portion of the outflow toward the functional component to impact the functional component, the functional component having a graphene coating thereon, wherein the graphene coating overcoats an existing charge control coating upon the functional component. Currently amended
The method of claim 12, wherein the functional component is selected from the group consisting of a solar panel, an optical solar reflector, a radiofrequency reflector, a gold mesh reflector, a solar array, a communication array, an antenna, an optical sensor, a thermal blanket, and any combination thereof. Original
The method of claim 12, wherein the existing oxide or a metal film. Previously presented
The method of claim 12, wherein at least a layer graphene. Original
The method of claim 12, wherein the graphene flakes. Original
The method of claim 12, wherein the graphene about 10% or less. Original
The method of claim 12, wherein graphene the functional component. Original
The method of claim 12, wherein graphene secondary substrate and is subsequently transferred coating. Original charge control coating comprises indium tin portion of the graphene coating comprises single-coating comprises a plurality of graphene coating decreases optical transparency by comprising the graphene coating is grown upon comprising the graphene coating is grown upon a to the functional component as a conformal
Canceled
Layer stacks claimed or described, ordered top of device to substrate.
spacecraft structure with graphene-coated functional component
Materials described outside the worked examples.
graphene coating
existing charge control coating
Additional fabrication and treatment steps described in the patent.
Performance values and ranges asserted in the specification or claims.
| Property | Value | Material |
|---|---|---|
optical transparency decrease due to graphene coating | ≤ 10 % | graphene coating |
— | 100–1500 eV |
Patent
Atlas literature
Patent
US 10,696,424Claims define the patent's legal scope. Independent claims stand alone; dependent claims (nested) narrow them. Click a claim to expand its dependents.
A spacecraft structure comprising: an electric propulsion system, wherein the electric propulsion system comprises one or more exhaust source points; a functional component, wherein at least one of the one or more exhaust source points is pointed toward the functional component to direct at least a portion of an outflow of the electric propulsion system to impact the functional component; and a graphene coating upon the functional component, wherein the graphene coating overcoats an existing charge control coating upon the functional component. Currently amended
The spacecraft structure of claim 1, wherein the functional component is selected from the group consisting of a solar panel, an optical solar reflector, a radiof r equency reflector, a gold mesh reflector, a solar array, a communication array, an antenna, an optical sensor, a thermal blanket, and any combination thereof. Original
The spacecraft structure of claim 1, wherein the existing charge control coating comprises indium tin oxide or a metal film. Previously presented
The spacecraft structure of claim 1, wherein at least a portion of the graphene coating comprises single-layer graphene. Original
The spacecraft structure of claim 1, wherein the graphene coating comprises a plurality of graphene flakes. Original
The spacecraft structure of claim 1, wherein the graphene coating decreases optical transparency by about 10% or less. Original
The spacecraft structure of claim 1, wherein graphene comprising the graphene coating is grown upon a surface of the functional component. Original
The spacecraft structure of claim 1, wherein graphene comprising the graphene coating is grown upon a secondary substrate and is subsequently transferred to the functional component as a conformal coating. Original
The spacecraft structure of claim 1, wherein the spacecraft structure comprises a satellite. Original
Canceled
Canceled
A method comprising: generating an outflow of energetic particles from an electric propulsion system of a spacecraft structure, the electric propulsion system comprising one or more exhaust source points; and pointing at least one of the one or more exhaust source points toward a functional component to direct at least a portion of the outflow toward the functional component to impact the functional component, the functional component having a graphene coating thereon, wherein the graphene coating overcoats an existing charge control coating upon the functional component. Currently amended
The method of claim 12, wherein the functional component is selected from the group consisting of a solar panel, an optical solar reflector, a radiofrequency reflector, a gold mesh reflector, a solar array, a communication array, an antenna, an optical sensor, a thermal blanket, and any combination thereof. Original
The method of claim 12, wherein the existing oxide or a metal film. Previously presented
The method of claim 12, wherein at least a layer graphene. Original
The method of claim 12, wherein the graphene flakes. Original
The method of claim 12, wherein the graphene about 10% or less. Original
The method of claim 12, wherein graphene the functional component. Original
The method of claim 12, wherein graphene secondary substrate and is subsequently transferred coating. Original charge control coating comprises indium tin portion of the graphene coating comprises single-coating comprises a plurality of graphene coating decreases optical transparency by comprising the graphene coating is grown upon comprising the graphene coating is grown upon a to the functional component as a conformal
Canceled
Layer stacks claimed or described, ordered top of device to substrate.
spacecraft structure with graphene-coated functional component
Materials described outside the worked examples.
graphene coating
existing charge control coating
Additional fabrication and treatment steps described in the patent.
Performance values and ranges asserted in the specification or claims.
| Property | Value | Material |
|---|---|---|
optical transparency decrease due to graphene coating | ≤ 10 % | graphene coating |
— | 100–1500 eV |
Patent
Atlas literature
Patent
US 10,696,424Claims define the patent's legal scope. Independent claims stand alone; dependent claims (nested) narrow them. Click a claim to expand its dependents.
A spacecraft structure comprising: an electric propulsion system, wherein the electric propulsion system comprises one or more exhaust source points; a functional component, wherein at least one of the one or more exhaust source points is pointed toward the functional component to direct at least a portion of an outflow of the electric propulsion system to impact the functional component; and a graphene coating upon the functional component, wherein the graphene coating overcoats an existing charge control coating upon the functional component. Currently amended
The spacecraft structure of claim 1, wherein the functional component is selected from the group consisting of a solar panel, an optical solar reflector, a radiof r equency reflector, a gold mesh reflector, a solar array, a communication array, an antenna, an optical sensor, a thermal blanket, and any combination thereof. Original
The spacecraft structure of claim 1, wherein the existing charge control coating comprises indium tin oxide or a metal film. Previously presented
The spacecraft structure of claim 1, wherein at least a portion of the graphene coating comprises single-layer graphene. Original
The spacecraft structure of claim 1, wherein the graphene coating comprises a plurality of graphene flakes. Original
The spacecraft structure of claim 1, wherein the graphene coating decreases optical transparency by about 10% or less. Original
The spacecraft structure of claim 1, wherein graphene comprising the graphene coating is grown upon a surface of the functional component. Original
The spacecraft structure of claim 1, wherein graphene comprising the graphene coating is grown upon a secondary substrate and is subsequently transferred to the functional component as a conformal coating. Original
The spacecraft structure of claim 1, wherein the spacecraft structure comprises a satellite. Original
Canceled
Canceled
A method comprising: generating an outflow of energetic particles from an electric propulsion system of a spacecraft structure, the electric propulsion system comprising one or more exhaust source points; and pointing at least one of the one or more exhaust source points toward a functional component to direct at least a portion of the outflow toward the functional component to impact the functional component, the functional component having a graphene coating thereon, wherein the graphene coating overcoats an existing charge control coating upon the functional component. Currently amended
The method of claim 12, wherein the functional component is selected from the group consisting of a solar panel, an optical solar reflector, a radiofrequency reflector, a gold mesh reflector, a solar array, a communication array, an antenna, an optical sensor, a thermal blanket, and any combination thereof. Original
The method of claim 12, wherein the existing oxide or a metal film. Previously presented
The method of claim 12, wherein at least a layer graphene. Original
The method of claim 12, wherein the graphene flakes. Original
The method of claim 12, wherein the graphene about 10% or less. Original
The method of claim 12, wherein graphene the functional component. Original
The method of claim 12, wherein graphene secondary substrate and is subsequently transferred coating. Original charge control coating comprises indium tin portion of the graphene coating comprises single-coating comprises a plurality of graphene coating decreases optical transparency by comprising the graphene coating is grown upon comprising the graphene coating is grown upon a to the functional component as a conformal
Canceled
Layer stacks claimed or described, ordered top of device to substrate.
spacecraft structure with graphene-coated functional component
Materials described outside the worked examples.
graphene coating
existing charge control coating
Additional fabrication and treatment steps described in the patent.
Performance values and ranges asserted in the specification or claims.
| Property | Value | Material |
|---|---|---|
optical transparency decrease due to graphene coating | ≤ 10 % | graphene coating |
— | 100–1500 eV |
Patent
Atlas literature
Patent
US 10,696,424Claims define the patent's legal scope. Independent claims stand alone; dependent claims (nested) narrow them. Click a claim to expand its dependents.
A spacecraft structure comprising: an electric propulsion system, wherein the electric propulsion system comprises one or more exhaust source points; a functional component, wherein at least one of the one or more exhaust source points is pointed toward the functional component to direct at least a portion of an outflow of the electric propulsion system to impact the functional component; and a graphene coating upon the functional component, wherein the graphene coating overcoats an existing charge control coating upon the functional component. Currently amended
The spacecraft structure of claim 1, wherein the functional component is selected from the group consisting of a solar panel, an optical solar reflector, a radiof r equency reflector, a gold mesh reflector, a solar array, a communication array, an antenna, an optical sensor, a thermal blanket, and any combination thereof. Original
The spacecraft structure of claim 1, wherein the existing charge control coating comprises indium tin oxide or a metal film. Previously presented
The spacecraft structure of claim 1, wherein at least a portion of the graphene coating comprises single-layer graphene. Original
The spacecraft structure of claim 1, wherein the graphene coating comprises a plurality of graphene flakes. Original
The spacecraft structure of claim 1, wherein the graphene coating decreases optical transparency by about 10% or less. Original
The spacecraft structure of claim 1, wherein graphene comprising the graphene coating is grown upon a surface of the functional component. Original
The spacecraft structure of claim 1, wherein graphene comprising the graphene coating is grown upon a secondary substrate and is subsequently transferred to the functional component as a conformal coating. Original
The spacecraft structure of claim 1, wherein the spacecraft structure comprises a satellite. Original
Canceled
Canceled
A method comprising: generating an outflow of energetic particles from an electric propulsion system of a spacecraft structure, the electric propulsion system comprising one or more exhaust source points; and pointing at least one of the one or more exhaust source points toward a functional component to direct at least a portion of the outflow toward the functional component to impact the functional component, the functional component having a graphene coating thereon, wherein the graphene coating overcoats an existing charge control coating upon the functional component. Currently amended
The method of claim 12, wherein the functional component is selected from the group consisting of a solar panel, an optical solar reflector, a radiofrequency reflector, a gold mesh reflector, a solar array, a communication array, an antenna, an optical sensor, a thermal blanket, and any combination thereof. Original
The method of claim 12, wherein the existing oxide or a metal film. Previously presented
The method of claim 12, wherein at least a layer graphene. Original
The method of claim 12, wherein the graphene flakes. Original
The method of claim 12, wherein the graphene about 10% or less. Original
The method of claim 12, wherein graphene the functional component. Original
The method of claim 12, wherein graphene secondary substrate and is subsequently transferred coating. Original charge control coating comprises indium tin portion of the graphene coating comprises single-coating comprises a plurality of graphene coating decreases optical transparency by comprising the graphene coating is grown upon comprising the graphene coating is grown upon a to the functional component as a conformal
Canceled
Layer stacks claimed or described, ordered top of device to substrate.
spacecraft structure with graphene-coated functional component
Materials described outside the worked examples.
graphene coating
existing charge control coating
Additional fabrication and treatment steps described in the patent.
Performance values and ranges asserted in the specification or claims.
| Property | Value | Material |
|---|---|---|
optical transparency decrease due to graphene coating | ≤ 10 % | graphene coating |
— | 100–1500 eV |
indium tin oxide
metal film
single-layer graphene
graphene flakes
graphene
| — |
Thickness | 0.68–3.4 nm | — |
Duration | 2–8 hours | — |
indium tin oxide
metal film
single-layer graphene
graphene flakes
graphene
| — |
Thickness | 0.68–3.4 nm | — |
Duration | 2–8 hours | — |
indium tin oxide
metal film
single-layer graphene
graphene flakes
graphene
| — |
Thickness | 0.68–3.4 nm | — |
Duration | 2–8 hours | — |
indium tin oxide
metal film
single-layer graphene
graphene flakes
graphene
| — |
Thickness | 0.68–3.4 nm | — |
Duration | 2–8 hours | — |