Title:
STRUCTURAL PROPELLANT FOR ION ROCKET (SPIR)
Document Type and Number:
Japanese Patent JP2017129115
Kind Code:
A
Abstract:
PROBLEM TO BE SOLVED: To provide a structural propellant for ion rockets (SPIR).SOLUTION: Systems, methods, and apparatus for a structural propellant for ion rockets (SPIR) are disclosed. A method for in-space propulsion of a spacecraft involves a step of removing, by a removal device 310, a portion of the structure 330 of a spacecraft. The method further involves a step of feeding, by the removal device, the portion into a Hall thruster system. Further, the method involves a step of utilizing, by the Hall thruster system, the portion as a propellant to produce thrust. The structure is an upper stage of the spacecraft. At least the upper stage comprises at least one structural support and/or at least one upper stage housing. The structure is manufactured from magnesium, bismuth, zinc, and/or indium.SELECTED DRAWING: Figure 3
Inventors:
JAMIE J CHILDRESS
THOMAS L KESSLER
THOMAS L KESSLER
Application Number:
JP2016211479A
Publication Date:
July 27, 2017
Filing Date:
October 28, 2016
Export Citation:
Assignee:
BOEING CO
International Classes:
F03H1/00
Attorney, Agent or Firm:
Yasuhiko Murayama
Tatsuhiko Abe
Kuroda Shinpei
Choi
Tatsuhiko Abe
Kuroda Shinpei
Choi
Previous Patent: A reducing valve for gas
Next Patent: A heat exchanger for engine inclusion: Duct crossing portion
Next Patent: A heat exchanger for engine inclusion: Duct crossing portion