Hydrogen peroxide catalyst

Patent metadata

Field	Value
Publication number	US-2016229694-A1
Application number	US-201414917562-A
Country	US
Kind code	A1
Filing date	Sep 8, 2014
Priority date	Sep 9, 2013
Publication date	Aug 11, 2016
Grant date	—

Abstract

A catalyst for decomposing high-concentration hydrogen peroxide comprises an active layer on a carrier comprising gamma-phase alumina. The carrier can also comprise aluminium, with the gamma-phase alumina forming a passivating layer on the surface of the aluminium. The active layer can comprise platinum. Apparatus for decomposing hydrogen peroxide can include the catalyst in a decomposition chamber arranged to receive hydrogen peroxide. The apparatus can be used as a thruster, comprising a nozzle arranged to generate thrust by directing exhaust gases in a specific direction. For example, the thruster can be a monopropellant, bipropellant, or hybrid thruster. In other embodiments, the apparatus can be used as a gas generator or a fuel cell.

First claim

1 . Apparatus comprising:
a decomposition chamber comprising an inlet arranged to receive high-concentration hydrogen peroxide; and a catalyst disposed in the decomposition chamber to catalyse decomposition of the high-concentration hydrogen peroxide received through the inlet, the catalyst comprising an active layer on a carrier comprising gamma-phase alumina.

2 . The apparatus of claim 1 , wherein the carrier further comprises aluminium and the gamma-phase alumina is disposed on the surface of the aluminium as a passivation layer.

3 . The apparatus of claim 1 , wherein the active layer comprises platinum.

4 . The apparatus of claim 1 , further comprising:
a reservoir storing hydrogen peroxide with a concentration of 80% to 100%, the reservoir being arranged to provide the hydrogen peroxide to the inlet.

5 . The apparatus of claim 1 , wherein the catalyst is in pellet, granule or monolithic form.

6 . The apparatus of claim 1 , wherein the apparatus is a thruster and further comprises:
a nozzle in fluid communication with the decomposition chamber, the nozzle being arranged to provide thrust by directing gas produced during decomposition of the hydrogen peroxide.

7 . The apparatus of claim 6 , wherein the apparatus is a bipropellant thruster, and the decomposition chamber further comprises a fuel inlet arranged to receive fuel from a fuel tank, the fuel inlet being disposed such that the fuel combusts with oxygen produced by the decomposition of the hydrogen peroxide.

8 . The apparatus of claim 6 , wherein the apparatus is a hybrid thruster and further comprises:
a solid fuel arranged to combust with oxygen produced by the decomposition of the hydrogen peroxide.

9 . The apparatus of claim 1 , further comprising:
a separating unit for separating water vapour and oxygen produced by the decomposition of the hydrogen peroxide.

10 . The apparatus of claim 1 , wherein the apparatus is a fuel cell and further comprises:
an anode comprising the catalyst; a cathode arranged to be electrically connected to the anode via a load; and an electrolyte separating the anode from the cathode, the electrolyte being arranged to permit movement of hydrogen ions from the anode to the cathode.

11 . A spacecraft comprising the apparatus of claim 1 .

12 . A method of generating thrust, the method comprising:
using a catalyst comprising an active layer on a carrier comprising gamma-phase alumina to catalyse the decomposition of hydrogen peroxide to produce exhaust gases; and directing the exhaust gases through a nozzle to generate thrust.

13 . The method of 12 , further comprising:
combusting a fuel with oxygen produced from the decomposition of the hydrogen peroxide, to produce the exhaust gases.

14 . The method of claim 12 , wherein the hydrogen peroxide has a concentration of 100%.

15 . Use of a catalyst comprising an active layer on a carrier comprising gamma-phase alumina, to catalyse the decomposition of hydrogen peroxide.

Assignees

• Airbus Defence & Space Ltd

Inventors

• Wynn Jonathan Thomas William
• Musker Anthony Joseph

Classifications

• B64G1/401

  Liquid propellant rocket engines (Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415) · CPC title

• C06D5/04

  by auto-decomposition of single substances · CPC title

• F02K9/08

  using solid propellants (F02K9/72 takes precedence; using semi-solid or pulverulent propellants F02K9/70) · CPC title

• B01J23/42

  Platinum · CPC title

• C01B13/0214 Primary

  Hydrogen peroxide · CPC title