Dual stage catalytic thruster

Patent metadata

Field	Value
Publication number	US-11236703-B2
Application number	US-201515580051-A
Country	US
Kind code	B2
Filing date	Jun 30, 2015
Priority date	Jun 30, 2015
Publication date	Feb 1, 2022
Grant date	Feb 1, 2022

Abstract

A catalytic thruster includes a reaction chamber that extends between first and second opposed chamber ends. The first chamber end includes a thermal standoff cup. There is a catalyst bed in the reaction chamber, and a feed tube extends into the reaction chamber through the thermal standoff cup.

First claim

What is claimed is:

1. A catalytic thruster comprising:
a reaction chamber that extends between a first chamber end and a second chamber end, the first chamber end including a thermal standoff cup;
a catalyst bed in the reaction chamber, the thermal standoff cup bounding the catalyst bed;
a feed tube that extends into the reaction chamber through the thermal standoff cup, the feed tube includes a tube end that has at least one injection port that opens into the reaction chamber; and
a sacrificial flow restrictor that partially blocks the at least one injection port, wherein the sacrificial flow restrictor is formed of a material that degrades and sheds from the at least one injection port upon operation of the catalytic thruster,
the feed tube extending a distance D1 into the reaction chamber, the distance D1 being defined from an inside surface of a narrow bottom of the thermal standoff cup where the feed tube enters to a tip of the feed tube in the reaction chamber, the reaction chamber is disposed about a central axis and has a radial dimension D2 relative to the central axis, and a penetration ratio of the distance D1 to the radial dimension D2 is greater than or equal to 1:1.

2. The catalytic thruster as recited in claim 1 , wherein the sacrificial flow restrictor is a screen attached to an end of the feed tube and disposed within the catalyst bed.

3. The catalytic thruster of claim 1 , wherein the sacrificial flow restrictor is disposed within the feed tube adjacent the catalyst bed.

4. The catalytic thruster of claim 1 , wherein the thermal standoff cup has a frustum geometry.

5. The catalytic thruster of claim 1 , wherein the thermal standoff cup has a cylindrical geometry.

6. The catalytic thruster as recited in claim 1 , wherein the sacrificial flow restrictor includes a mesh, and the mesh is sized with respect to size of catalyst granules in the catalyst bed to block the catalyst granules from entering the at least one injector port.

7. The catalytic thruster as recited in claim 6 , wherein the mesh is a sleeve disposed on the tube end.

8. The catalytic thruster as recited in claim 1 , further comprising a convergent-divergent nozzle at the second chamber end.

9. The catalytic thruster as recited in claim 1 , wherein the operation include a single thrust cycle of the catalytic thruster.

10. The catalytic thruster as recited in claim 1 , wherein the penetration ratio is also less than or equal to 1.25:1.

11. The catalytic thruster as recited in claim 10 , wherein the feed tube is bonded in a joint with the thermal standoff cup.

12. The catalytic thruster as recited in claim 1 , wherein the feed tube and the sacrificial flow restrictor are formed of different alloys.

Assignees

• Aerojet Rocketdyne Inc

Inventors

• Dawson Matthew
• Brewster Gerald

Classifications

• B64G1/402

  Propellant tanks; Feeding propellants · CPC title

• F02K9/68 Primary

  Decomposition chambers · CPC title

• B64G1/403

  Solid propellant rocket engines · CPC title

• F02K9/58

  Propellant feed valves · CPC title

• F02K9/94

  Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants · CPC title