Electrode design for lift augmentation and power generation of atmospheric entry vehicles during aerocapture and entry, descent, and landing maneuvers

Patent metadata

Field	Value
Publication number	US-12283418-B2
Application number	US-202217727401-A
Country	US
Kind code	B2
Filing date	Apr 22, 2022
Priority date	Apr 23, 2021
Publication date	Apr 22, 2025
Grant date	Apr 22, 2025

Abstract

A magnetohydrodynamic (MHD) flow control mechanism is described which substantially improves the existing processes in that smaller magnetic fields, requiring far less mass, may be placed away from the forebody of the spacecraft to produce Lorentz forces that augment the lift and the drag forces for guidance, navigation, and control of the spacecraft. The MHD flow control mechanism may also be configured to provide additional thermal protection of the electrodes therein.

First claim

We claim:

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.

2. The system of claim 1 , wherein the magnet is selected from the group consisting of a permanent magnet, an electromagnet and combinations thereof.

3. The system of claim 1 , wherein the electrodes are formed of at least one of tungsten and a tungsten alloy.

4. The system of claim 1 , wherein the channel includes slanted side walls.

5. The system of claim 4 , wherein each electrode of the first pair of electrodes is embedded in a slanted side wall.

6. The system of claim 4 , wherein the channel further includes a flat bottom portion connecting the slanted side walls.

7. The system of claim 6 , wherein the magnet is located on an inward facing surface of the aeroshell opposite the flat bottom portion of the channel.

8. The system of claim 1 , wherein the aeroshell is a blunt-body aeroshell.

9. An aeroshell for use with a spacecraft comprising:
a blunt-body configuration having at least one channel formed therein, wherein the at least one channel has multiple sides and a bottom connecting the multiple sides having an outward facing surface and an inward facing surface;
at least a first pair of electrodes embedded in at least two of the multiple sides of the at least one channel;
a magnet placed on an inward facing surface of the bottom of the least one channel.

10. The aeroshell of claim 9 , wherein the channel includes two slanted sides and a flat bottom connecting the two slanted sides.

11. The aeroshell of claim 10 , wherein the electrodes of the at least a first electrode pair are embedded in the two slanted sides, and further wherein the electrodes are located opposite one another across the flat bottom.

12. The aeroshell of claim 9 , wherein the magnet is placed opposite the flat bottom of the channel.

13. The aeroshell of claim 9 , wherein the magnet is selected from the group consisting of a permanent magnet, an electromagnet, and combinations thereof.

14. The system of claim 9 , wherein the electrodes are formed of at least one of tungsten and a tungsten alloy.

15. An aeroshell for use with a spacecraft comprising:
multiple channels formed therein, wherein each of the multiple channels has multiple sides and a bottom connecting the multiple sides including an outward facing surface and an inward facing surface;
multiple electrode pairs embedded in at least two of the multiple sides of one of the multiple channels; and
at least one magnet associated with each of the multiple electrode pairs, the at least one magnet being placed on an inward facing surface of the bottom of the one of the multiple channels containing the multiple electrode pairs embedded therein.

16. The aeroshell of claim 15 , wherein each of the multiple channel includes two slanted sides and a flat bottom connecting the two slanted sides.

17. The aeroshell of claim 16 , wherein the electrodes of each of the multiple electrode pairs are embedded in the two slanted sides of at least one of the multiple channels, and further wherein the electrodes are located opposite one another across the flat bottom.

18. The aeroshell of claim 15 , wherein the at least one magnet is placed opposite the flat bottom of the channel.

19. The aeroshell of claim 15 , wherein each of the multiple electrode pairs is embedded in a different one of the at least one multiple channels.

Assignees

• Nasa

Inventors

• Moses Robert W
• Cheatwood Foy M
• Johnston Christopher O
• Macheret Sergey
• Parent Bernard
• Little Justin

Classifications

• B64G1/62

  Systems for re-entry into the earth's atmosphere; Retarding or landing devices · CPC title

• B64G1/623

  Retarding devices, e.g. retrorockets · CPC title

• B64G1/2421

  Aerobraking · CPC title

• H01F7/02

  Permanent magnets {[PM]} · CPC title

• H01F7/20

  without armatures (cores H01F3/00; coils H01F5/00 {; shaping metal by applying magnetic forces B21D26/14; electromagnets specially adapted for NMR applications G01R33/381}) · CPC title