Satellite propellant tank with integrated regulation

Patent metadata

Field	Value
Publication number	US-12129053-B2
Application number	US-202217991671-A
Country	US
Kind code	B2
Filing date	Nov 21, 2022
Priority date	Dec 15, 2021
Publication date	Oct 29, 2024
Grant date	Oct 29, 2024

Abstract

A satellite propellant tank includes a tank body and a dome attached to the tank body to enclose an interior volume for propellant storage. One or more cavities are formed in the dome. One or more propellant control components are located in the one or more cavities formed in the dome.

First claim

What is claimed is:

1. A satellite propellant tank, comprising:
a tank body;
a dome attached to the tank body to enclose an interior volume for propellant storage, the dome formed of an upper portion and a lower portion, the upper portion welded to the lower portion and the lower portion welded to the tank body;
one or more cavities formed in the dome; and
one or more propellant control components located in the one or more cavities formed in the dome.

2. The satellite propellant tank of claim 1 , wherein the one or more propellant control components include at least one of: a pressure regulator, a valve, a filter or an orifice.

3. The satellite propellant tank of claim 1 , wherein the one or more propellant control components include a pressure regulator.

4. The satellite propellant tank of claim 3 , wherein the pressure regulator is configured to reduce pressure from a tank pressure to a reduced pressure for supply to one or more thrusters.

5. The satellite propellant tank of claim 1 , wherein the one or more propellant control components include a valve to control propellant supply to one or more thrusters.

6. The satellite propellant tank of claim 1 , wherein the one or more propellant control components include a filter to remove particles from propellant supplied to one or more thrusters.

7. The satellite propellant tank of claim 1 , wherein the one or more cavities include a high-pressure manifold, a low-pressure manifold that is connected to the high-pressure manifold by a pressure regulator, and an outlet manifold that is connected to the low-pressure manifold by a valve.

8. The satellite propellant tank of claim 7 , further comprising a high-pressure transducer attached to the high-pressure manifold and a low-pressure transducer attached to the low-pressure manifold.

9. The satellite propellant tank of claim 1 , wherein the one or more cavities are located in the lower portion and the propellant control components located in the one or more cavities are enclosed by the upper portion.

10. A method of forming a satellite propellant tank comprising:
forming a lower portion and an upper portion of a tank dome to have one or more cavities;
locating one or more propellant control components in the one or more cavities; and
subsequently attaching the lower portion of the tank dome to the upper portion of the tank dome to enclose the one or more propellant control components.

11. The method of claim 10 , wherein forming the lower portion and the upper portion includes forming at least one of the lower portion or the upper portion using additive manufacturing.

12. The method of claim 10 , wherein locating the one or more propellant control components in the one or more cavities includes constructing at least one propellant control component in a cavity.

13. The method of claim 12 , wherein the at least one propellant control component is a valve that is constructed from components that include a poppet, the cavity having dimensions to enable the poppet to slide between an open position and a closed position using walls of the cavity as a poppet guide.

14. The method of claim 10 further comprising attaching the tank dome and a tank body to enclose an interior of the satellite propellant tank.

15. The method of claim 14 further comprising attaching two or more pressure transducers to the tank dome to measure pressures including pressure in a high-pressure manifold in the tank dome and pressure in a low-pressure manifold in the tank dome.

16. A satellite thruster system comprising:
a propellant tank formed of a tank body and a dome attached to the tank body to enclose an interior volume for storage of propellant, the dome formed of an upper portion and a lower portion, the upper portion welded to the lower portion and the lower portion welded to the tank body with cavities formed between the upper portion and the lower portion of the dome;
one or more satellite thrusters connected to the propellant tank to receive propellant from the propellant tank; and
a plurality of propellant control components located along a propellant flow pathway between the interior volume and the one or more satellite thrusters, one or more of the plurality of propellant control components are located in the cavities.

17. The satellite thruster system of claim 16 , wherein the one or more of the plurality of propellant control components located in the cavities includes a filter, a pressure regulator and a valve.

18. The satellite thruster system of claim 17 , wherein the one or more of the plurality of propellant control components further includes a pressure relief valve.

19. The satellite thruster system of claim 16 , wherein the one or more satellite thrusters are ion thrusters and the propellant is one or more of xenon, krypton or argon.

Assignees

• Maxar Space Llc

Inventors

• Lenguito Giovanni

Classifications

• F02K9/80 Primary

  characterised by thrust or thrust vector control (burning control of solid propellants F02K9/26; feeding control of liquid or gaseous propellants F02K9/56; re-ignitable, restartable or intermittently operated rocket-engine plants F02K9/94) · CPC title

• B64G1/26 Primary

  using jets · CPC title

• B64G1/4021

  Tank construction; Details thereof · CPC title

• B64G1/413 Primary

  Ion or plasma engines · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title