Spacecraft propulsion system and method

Patent metadata

Field	Value
Publication number	US-2017210493-A1
Application number	US-201515329470-A
Country	US
Kind code	A1
Filing date	Jul 27, 2015
Priority date	Jul 30, 2014
Publication date	Jul 27, 2017
Grant date	—

Abstract

A space propulsion system includes an electrostatic thruster with a first electrical load; a resistojet; a propellant fluid feed circuit; and an electrical power supply circuit including a first power supply line and a first switch for selecting between connecting the first power supply line to the resistojet and connecting the first power supply line to the first electrical load of the electrostatic thruster. The propulsion system thus enables a space propulsion method to be applied that includes a switching step for selecting a first propulsion mode in which the resistojet is activated, or a second propulsion mode in which the electrostatic thruster is activated.

First claim

1 . A space propulsion system comprising:
an electrostatic thruster with at least a first electrical load; a resistojet; a propellant fluid feed circuit; and an electrical power supply circuit comprising at least a first power supply line and a first switch for selecting between connecting said first power supply line to the resistojet and connecting said first power supply line to said first electrical load of the electrostatic thruster.

2 . The space propulsion system according to claim 1 , wherein said first electrical load comprises a heater element of an emitter cathode of said electrostatic thruster.

3 . The space propulsion system according to claim 2 , wherein said first switch serves to select between connecting said first power supply line, without any current or voltage conversion or transformation, to a resistor forming a heater element of the resistojet, and connecting said first power supply line, without any current or voltage conversion or transformation, to a resistor forming the heater element of the emitter cathode of said electrostatic thruster.

4 . The space propulsion system according to claim 1 , wherein said propellant fluid feed circuit includes at least one valve for feeding the electrostatic thruster and at least one valve for feeding the resistojet.

5 . The space propulsion system according to claim 4 , further comprising at least one valve-opening control line and a second switch for selecting between connecting said valve-opening control line to the valve for feeding the electrostatic thruster, and connecting said valve-opening control line to at least one feed valve of the resistojet.

6 . The space propulsion system according to claim 1 , wherein said power supply circuit comprises at least one thruster selection unit in which at least said first switch is integrated.

7 . The space propulsion system according to claim 1 , wherein said power supply circuit further includes at least one power processing unit suitable for powering at least one other electrical load of the electrostatic thruster at a voltage that is considerably higher than the first electrical load.

8 . The space propulsion system according to claim 1 , wherein said electrostatic thruster is a Hall effect thruster.

9 . The space propulsion system according to claim 1 , comprising a plurality of the electrostatic thruster.

10 . The space propulsion system according to claim 9 , wherein said propellant fluid feed circuit includes at least one pressure regulator common to the plurality of said electrostatic thruster.

11 . The space propulsion system according to claim 9 , wherein said propellant fluid feed circuit includes an individual pressure regulator for at least one of said plurality of said electrostatic thruster.

12 . . An attitude and/or trajectory control system comprising:
the space propulsion system according to claim 1 .

13 . A spacecraft including comprising:
a space propulsion system according to claim 1 .

14 . A space propulsion method comprising:
switching between an electrostatic thruster and a resistojet, wherein a first switch is used for connecting a first electrical power supply line to the resistojet or to a first electrical load of the electrostatic thruster in order to select a first propulsion mode in which the resistojet is activated or else a second propulsion mode in which the electrostatic thruster is activated.

Assignees

• Safran Aircraft Engines

Inventors

• Marchandise Frederic

Classifications

• B64G1/443

  Photovoltaic cell arrays · CPC title

• F03H1/0075

  with an annular channel; Hall-effect thrusters with closed electron drift · CPC title

• F03H1/0012

  Means for supplying the propellant · CPC title

• F03H1/0018 Primary

  Arrangements or adaptations of power supply systems (for cosmonautic vehicles B64G1/42) · CPC title

• B64G1/405

  Operations & Transport · mapped topic