Igniter for a rocket engine, method for ignition of a rocket engine

摘要

An igniter for a rocket engine or motor comprising a combustion chamber with a solid fuel, an inlet for supplying an oxidizer to the combustion chamber to ignite the solid fuel and an outlet for discharging exhaust gas, wherein the igniter is arranged to discharge exhaust gas to the rocket engine for igniting the rocket engine. The igniter can be used for multiple ignitions and can also be re-used after re-filling.

主权项

1. A hybrid igniter for a rocket engine, the hybrid igniter comprising a combustion chamber configured to provide a solid material, an inlet for supplying a fluid product to the combustion chamber, an initiating device for inducing ignition of the solid material, and an outlet for discharging an exhaust gas, such that an exothermic reaction of the fluid product with the solid material in the combustion chamber generates a combustion producing the exhaust gas, wherein the igniter is arranged to discharge the exhaust gas to the rocket engine for igniting the rocket engine, and wherein the igniter has a housing with a connection that may be opened for refilling the solid material.