Method and system for providing cruciform steered, bent biconic and plasma suppression for maximum accuracy

• US 7,721,997 B1
• Filed: 08/01/2007
• Issued: 05/25/2010
• Est. Priority Date: 05/18/2004
• Status: Active Grant

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Meyer, J. William, Teter, Roger D., Dunn, Steven A.
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US11/832,613
• Time in Patent Office: 1,028 Days
• Field of Search: 244/136, 244/1.N, 244/15, 244/158.9, 244/159.1, 244/159.3, 244/171.7, 244/171.8, 244/158.1, 455/64
• US Class Current: 244/159.1
• CPC Class Codes: B64G 1/62 Systems for re-entry into the earth's atmosphere; Retarding or landing devices

Abstract

A system for reducing plasma induced communication disruption utilizes an electrophilic gas injectant, bent reentry vehicle nose shaping and a number of flaps configured to provide 3-axis steering capability. Injecting electrophilic gas injectant into plasma accomplishes reduction of plasma induced communication disruption by removing free electrons in the plasma which causes the communication disruption. For reentry vehicles, a bent biconic nose also reduces plasma effect during reentry. By combining electrophilic gas injection and bent nose shaping, the system reduces and/or eliminates plasma induced communication disruption, such as, GPS communication blackout, for a reentry vehicle during reentry. Furthermore, the 3-axis steering capability renders the reentry vehicle more maneuverable. Performance of the reentry vehicle during reentry, such as, target accuracy, is thus improved.

Claims

1. A system for reducing plasma induced communication disruption for a flight vehicle traveling at a hypersonic speed, comprising:

a communication antenna mounted on a base of the flight vehicle; and

an electrophilic gas injection system configured to inject an electrophilic gas injectant into plasma in a separated-flow vortex in the vicinity of the communication antenna, wherein the electrophilic gas injectant is injected during a plasma induced communication disruption phase of a hypersonic flight;

wherein the flight vehicle further includes a biconic nose; and

wherein the base is positioned opposite to the biconic nose, and wherein the electrophilic gas injection system includes at least one exit port in the base for injecting the electrophilic gas injectant into plasma near the communication antenna.

2. The system of claim 1, wherein the flight vehicle further includes a plurality of flaps configured to provide 3-axis steering capability;

and

wherein the biconic nose has a bend angle.

3. The system of claim 1, wherein the electrophilic gas injectant is hexafluroethane.

4. A reentry vehicle comprising:

a communication antenna;

a bent nose having a biconic shape;

a plurality of flaps configured to provide 3-axis steering capability; and

an electrophilic gas injection system configured to inject an electrophilic gas injectant into plasma in a separated-flow vortex near the communication antenna, wherein the electrophilic gas injectant is injected during a plasma induced communication disruption phase of reentry;

wherein the communication antenna is mounted on a base of the reentry vehicle, the base positioned opposite to the bent nose, and wherein the electrophilic gas injection system includes at least one exit port in the base for injecting the electrophilic gas injectant into plasma near the communication antenna.

5. The reentry vehicle of claim 4, wherein injecting the electrophilic gas injectant into the plasma creates a low plasma region;

wherein communications with the reentry vehicle are conducted using the communication antenna via the low plasma region; and

wherein the low plasma region reduces plasma induced communication blackout.

6. The reentry vehicle of claim 4, wherein the electrophilic gas injectant is hexafluoroethane.

7. A method for reducing plasma induced communication blackout for a reentry vehicle, comprising the steps of:

providing a biconic nose for the reentry vehicle; and

injecting an electrophilic gas injectant into plasma in the vicinity of a communication antenna located at a posterior of the reentry vehicle, wherein the electrophilic gas injectant is injected into the plasma in a separated-flow vortex near the communication antenna during a plasma induced communication disruption phase.

8. The method of claim 7, wherein the electrophilic gas is hexafluoroethane.

9. The method of claim 7, further comprising:

providing a plurality of flaps for the reentry vehicle to achieve 3-axis steering capability;

wherein the biconic nose has a bend angle.