Method for plasma dynamic cancellation for hypersonic vehicles

Patent metadata

Field	Value
Publication number	US-9972907-B2
Application number	US-201615068026-A
Country	US
Kind code	B2
Filing date	Mar 11, 2016
Priority date	Mar 11, 2016
Publication date	May 15, 2018
Grant date	May 15, 2018

Abstract

A sensor system and method of reducing plasma-induced communication inhibition for a main antenna includes using auxiliary antennas for detecting a density of plasma that affects operation of the main antenna, and re-orienting an electromagnetic field around the main antenna in response to the density detected to reduce effect of the plasma on the main antenna. The auxiliary antennas are also operable for data link communication and switchable such if the density of the plasma inhibits receipt or sending of signals by one of the auxiliary antennas, another one of the auxiliary antennas may be used for data link communication.

First claim

What is claimed is:

1. A sensor system comprising:
a main antenna configured to send and/or receive radio-frequency signals;
a plurality of auxiliary antennas configured to detect density of a surrounding plasma field that inhibits sending and/or receipt of the radio-frequency signals by the main antenna, wherein the auxiliary antennas are configured to generate an electromagnetic field and are operable for data link communication; and
a controller operatively coupled to the at least one auxiliary antenna;
wherein the controller receives information from the at least one auxiliary antenna regarding the density of the plasma field; and
wherein the controller is configured to adjust a phase between the auxiliary antennas, thereby reducing at least in part inhibition by the plasma field of the sending and/or receipt of signals of the main antenna.

2. The system of claim 1 , wherein the plurality of auxiliary antennas are switchable with each other in response to density of the plasma field that inhibits the data link communication of one of the plurality of auxiliary antennas.

3. The system of claim 1 , further comprising at least one electromagnet for re-orienting the electromagnetic field.

4. The system of claim 3 , wherein the at least one electromagnet includes a positively charged electromagnet and a negatively charged electromagnet that are spaced apart, and one of the positively charged electromagnet and the negatively charged electromagnet is located distally opposite the main antenna.

5. The system of claim 4 , further comprising a positively or negatively charged two-phase electromagnet that is operable to change phase relative to an oppositely charged electromagnet.

6. The system of claim 3 , wherein the at least one electromagnet includes a plurality of electromagnets that are circumferentially spaced around the main antenna.

7. The system of claim 1 , wherein the at least one auxiliary antenna includes a plurality of auxiliary antennas that are circumferentially spaced around the main antenna.

8. The system of claim 7 , wherein the plurality of auxiliary antennas are diametrically opposed to one another.

9. The system of claim 1 , wherein the system is contained in a radome of a hypersonic vehicle.

10. The system of claim 9 , wherein the radome includes a metallic tip that is negatively or positively charged, and a plurality of charged plates having an opposite charge from the metallic tip that are circumferentially spaced around the main antenna, wherein the metallic tip is located distally opposite the plurality of charged plates.

11. The system of claim 10 , further comprising an electromagnet coupled to the metallic tip for re-orienting the electromagnetic field.

12. The system of claim 1 , wherein the at least one auxiliary antenna has an ultra-wideband antenna structure.

13. The system of claim 1 , wherein the at least one auxiliary antenna has an omni-directional radiation pattern or a forward radiation pattern.

14. A method of reducing plasma-induced communication inhibition using the sensor system according to claim 1 , the method comprising:
detecting a density of plasma that affects operation of the main antenna; and
re-orienting the electromagnetic field around the main antenna in response to the density detected to reduce effect of the plasma on the main antenna.

15. The method of claim 14 , further comprising using the plurality of auxiliary antenna to send information regarding the density of the plasma to the controller and re-orienting the electromagnetic field using the controller.

16. The method of claim 14 , further comprising switching between a first and second auxiliary antenna for data link communication in response to the density detected in a respective region of the first and second auxiliary antenna.

17. The method of claim 15 , further comprising using the at least one auxiliary antenna to detect the density of the plasma in a forward direction and a sideways direction.

18. A sensor system comprising:
a main antenna;
a plurality of auxiliary antennas that are circumferentially spaced around the main antenna and are diametrically opposed to one another; and
a controller operatively coupled to the at least one auxiliary antenna;
wherein the controller receives information from the at least one auxiliary antenna regarding a plasma field that inhibits sending and/or receipt of signals by the main antenna; and
wherein the controller configures an electromagnetic field set up by the at least one auxiliary antenna to reduce density of the plasma field, thereby reducing at least in part inhibition by the plasma field of the sending and/or receipt of signals of the main antenna,
wherein the at least one auxiliary antenna includes a plurality of auxiliary antennas that are circumferentially spaced around the main antenna.

19. A sensor system contained in a radome of a hypersonic vehicle that includes a negatively or positively charged metallic tip, the sensor system comprising:
a main antenna;
at least one auxiliary antenna;
a controller operatively coupled to the at least one auxiliary antenna; and
a plurality of charged plates having an opposite charge from the metallic tip that are circumferentially spaced around the main antenna, wherein the metallic tip is located distally opposite the plurality of charged plates,
wherein the controller receives information from the at least one auxiliary antenna regarding a plasma field that inhibits sending and/or receipt of signals by the main antenna, and
wherein the controller configures an electromagnetic field set up by the at least one auxiliary antenna to reduce density of the plasma field, thereby reducing at least in part inhibition by the plasma field of the sending and/or receipt of signals of the main antenna.

Assignees

• Raytheon Co

Inventors

• Stratis Glafkos K
• Vanderwyst Anton
• Sunne Wayne L
• Derrick David G
• Edmiston James P
• Manzi David G
• Choe Howard C
• Samuel Alphonso A

Classifications

• G01N9/24

  by observing the transmission of wave or particle radiation through the material · CPC title

• H01Q1/281

  Nose antennas · CPC title

• F42B15/12

  Intercontinental ballistic missiles (F42B15/01 takes precedence) · CPC title

• F42B15/10

  Missiles having a trajectory only in the air · CPC title

• H01Q21/28

  Combinations of substantially independent non-interacting antenna units or systems {(multiple beam H01Q25/00)} · CPC title