Electrostatic discharge mitigation for a first spacecraft operating in proximity to a second spacecraft

Patent metadata

Field	Value
Publication number	US-2018297722-A1
Application number	US-201715829758-A
Country	US
Kind code	A1
Filing date	Dec 1, 2017
Priority date	Apr 13, 2017
Publication date	Oct 18, 2018
Grant date	—

Abstract

Methods and systems for mitigating or reducing the risk of an electrostatic discharge due to static charge differentials between a first spacecraft and a second spacecraft as the first spacecraft approaches the second spacecraft may be accomplished using a passive electrostatic discharge mitigation device. In some embodiments, mitigation of static potential between the first spacecraft and the second spacecraft may be actively accomplished by an electric propulsion system provided on the first spacecraft. In some embodiments, mitigation may be provided by both actively and passively mitigating static potential between the first spacecraft and the second spacecraft.

First claim

1 . A system on a first space vehicle for mitigating electrostatic discharge between the first space vehicle and a second space vehicle, the system comprising:
a propulsion mechanism for maneuvering the first space vehicle in space; a capture mechanism positioned on the first space vehicle for at least temporarily joining the first space vehicle to the second space vehicle; and a mechanism for passively mitigating electrostatic discharge comprising one or more resistors and one or more compliant members electrically connected to the one or more resistors,
wherein the one or more compliant members are configured such that one of the compliant members provides the first physical contact between the first space vehicle and the second space vehicle.

2 . The system of claim 1 , wherein the passive electrostatic discharge mitigation system is configured to reduce an electrostatic discharge current between the first space vehicle and the second space vehicle to less than or equal to about 800 milliamps over a time period of less than or equal to about 90 nanoseconds.

3 . The system of claim 1 , wherein the passive electrostatic discharge mitigation system further comprises one or more inductive elements comprising inductors, ferrite beads, or chokes.

4 . The system of claim 1 , wherein the one of more compliant members are configured to extend from the first space vehicle in a direction toward the second space vehicle.

5 . The system of claim 4 , wherein the one or more compliant members are whiskers.

6 . The system of claim 5 , wherein compliance if the of the one or more compliant members is provided, at least in part, by a torsion spring.

7 . A system on a first space vehicle for mitigating electrostatic discharge between the first space vehicle and a second space vehicle, the system comprising:
an active electrostatic discharge system situated on the first space vehicle, wherein the active electrostatic discharge system is configured to use an electric propulsion apparatus on the first space vehicle to reduce an electric potential between the first space vehicle and the second space vehicle by manipulating a plasma field of one of the first space vehicle, the second space vehicle, or both the first space vehicle and the second space vehicle.

8 . The system of claim 7 , wherein the active electrostatic discharge system is configured to manipulate the plasma field of the first space vehicle.

9 . The system of claim 7 , wherein the active electrostatic discharge system is configured to manipulate the plasma field of the second space vehicle.

10 . The system of claim 7 , wherein the electric propulsion apparatus is configured to produce a plasma field significant enough to reduce the potential between the first space vehicle and the second space vehicle to less than about +/−200 volts.

11 . The system of claim 7 , wherein the electric propulsion apparatus is one or more Hall Effect Thrusters.

12 . A system on a first space vehicle for mitigating electrostatic discharge between the first space vehicle and a second space vehicle, the system comprising:
a passive electrostatic discharge mitigation system situated on the first space vehicle, wherein the passive electrostatic discharge mitigation system comprises one or more resistors and one or more compliant members electrically connected to the one or more resistors; and an active electrostatic discharge system situated on the first space vehicle, wherein the active electrostatic discharge system is configured to use an electric propulsion apparatus on the first space vehicle to reduce an electric potential between the first space vehicle and the second space vehicle by manipulating a plasma field of one of the first space vehicle, the second space vehicle, or both the first and second space vehicle.

13 . The system of claim 12 , wherein the passive electrostatic discharge mitigation system is configured to reduce an electrostatic discharge current between the first space vehicle and the second space vehicle to less than or equal to about 800 milliamps over a time period of less than or equal to about 90 nanoseconds.

14 . The system of claim 12 , wherein the passive electrostatic discharge mitigation system further comprises one or more inductive elements comprising inductors, ferrite beads, or chokes.

15 . The system of claim 12 , wherein the one or more compliant members are whiskers.

16 . The system of claim 12 , wherein the active electrostatic discharge system is configured to manipulate the plasma field of the first space vehicle.

17 . The system of claim 12 , wherein the active electrostatic discharge system is configured to manipulate the plasma field of the second space vehicle.

18 . The system of claim 12 , wherein the electric propulsion apparatus is configured to produce a plasma field significant enough to reduce the potential between the first space vehicle and the second space vehicle to less than about +/−200 volts.

19 . The system of claim 12 , wherein the one or more compliant members are configured to provide the first physical contact between the first space vehicle and the second space vehicle.

20 . The system of claim 12 , wherein the one or more compliant members are configured to extend from the first space vehicle in a direction toward the second space vehicle.

Assignees

• Orbital Atk Inc

Inventors

• Agathon-Burton Christine A
• Michel Matthew Alan
• Cochran Dewey Edwin
• Graham Ronald Lynn
• Herbert Gregg A
• Llorens William A

Classifications

• B64G1/52 Primary

  Protection, safety or emergency devices; Survival aids · CPC title

• B64G1/405

  Operations & Transport · mapped topic

• B64G1/646

  Docking or rendezvous systems (refuelling in space B64G1/4024) · CPC title

• B64G1/6464

  Docking probes and receivers · CPC title

• B64G1/413

  Ion or plasma engines · CPC title