Patent ID: 9169806
Filing Date: 2015-10-27
Classification: F02C,F02K,F41A,F42B

Abstract:
1. A propulsion system configured to propel a flying device, or an anti-tank missile, the propulsion system comprising: a booster; and a turbojet which comprises: a compressor; a combustion chamber; a turbine; and an ejection nozzle; wherein the booster is incorporated into a rear part of the turbojet, the booster comprising a chamber which is fixed to a casing of the turbojet, by being positioned along the longitudinal axis thereof, which includes a nozzle at a rear, and which includes at least one charge and means of initiating the charge; and the propulsion system further comprises: at least one first gas bleed tube connected to the booster and configured to ignite the combustion chamber; and at least one second gas bleed tube also connected to the booster and configured to start the turbine.