Abstract: A rocket engine configured to run on a liquid fuel and liquid hydrogen peroxide is started by impinging high pressure streams of a fuel and liquid H2O2 into a combustion chamber under pressure and temperature conditions sufficient to decompose the liquid H2O2 into hot water stream and oxidizer and achieve ignition.

Abstract: Disclosed is a method for initiating startup of a rocket engine configured to run on a liquid fuel and liquid hydrogen peroxide, including the steps of: initially decomposing the liquid hydrogen peroxide by passing the liquid hydrogen peroxide through a catalyst bed; passing decomposition products from the catalyst bed to a reaction chamber of the rocket engine and mixing the decomposition products with the liquid fuel to initiate detonation. Once detonation is initiated, the liquid H2O2 and liquid fuel are passed directly to a reaction chamber of the rocket, bypassing the catalyst bed. A rocket system includes a rocket engine having an initial ignition circuit having a catalyst bed sized to support decomposition of liquid H2O2 for initial reaction with the liquid fuel. The rocket engine, upon initial ignition, is configured to run on liquid fuel and liquid H2O2 without first passing the liquid H2O2 through the catalyst bed.

Abstract: Disclosed is a stabilized solution of 70% to 100% hydrogen peroxide containing an alkali phosphate as a stabilizer, a rocket propellant including a combustible fuel and oxidizer, wherein the oxidizer is a stabilized solution of 70% to 100% hydrogen peroxide, and a rocket having a fuel store, an oxidizer store and a rocket engine, wherein the oxidizer is a stabilized solution of 70% to 100% hydrogen peroxide.