US 12,283,418 B2
Electrode design for lift augmentation and power generation of atmospheric entry vehicles during aerocapture and entry, descent, and landing maneuvers
Robert W. Moses, Poquoson, VA (US); Foy M. Cheatwood, Norfolk, VA (US); Christopher O. Johnston, Yorktown, VA (US); Sergey Macheret, West Lafayette, IN (US); Bernard Parent, Tucson, AZ (US); and Justin Little, Seattle, WA (US)
Assigned to UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASA, Washington, DC (US)
Filed by UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASA, Washington, DC (US)
Filed on Apr. 22, 2022, as Appl. No. 17/727,401.
Claims priority of provisional application 63/178,720, filed on Apr. 23, 2021.
Claims priority of provisional application 63/178,761, filed on Apr. 23, 2021.
Prior Publication US 2022/0348362 A1, Nov. 3, 2022
Int. Cl. B64G 1/62 (2006.01); B64G 1/24 (2006.01); H01F 7/02 (2006.01); H01F 7/20 (2006.01)
CPC H01F 7/0273 (2013.01) [B64G 1/2421 (2023.08); B64G 1/62 (2013.01); H01F 7/02 (2013.01); H01F 7/20 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A magnetohydrodynamic (MHD) flow control system for use with an aeroshell of a spacecraft comprising:
at least a first pair of electrodes configured to be embedded in a first predetermined portion of the aeroshell, wherein the at least a first predetermined portion of the aeroshell is a channel having multiple side walls and a bottom portion connecting the multiple side walls having an outward facing surface and an inward facing surface, and further wherein each electrode is embedded within one of the multiple side walls of the channel; and
a magnet configured for placement on an inward facing surface of the bottom of the channel.