초록 ▼

The invention relates to a combustion chamber of a ramjet and booster rocket, which comprises an inner envelope provided with upstream lateral ports for the inlet of air and a downstream nozzle for ejecting the combustion gases, to allow functioning of the rocket at cruising speed; an outer envelope

The invention relates to a combustion chamber of a ramjet and booster rocket, which comprises an inner envelope provided with upstream lateral ports for the inlet of air and a downstream nozzle for ejecting the combustion gases, to allow functioning of the rocket at cruising speed; an outer envelope, concentric to the inner envelope and closed, with the exclusion of a single rear port for the ejection of the gases, to allow functioning of the rocket at launching speed; and separating means for separating from the combustion chamber at least a part of the outer envelope, at the end of the launching phase, in order to ensure the clearance of the upstream lateral ports of the inner envelope.

대표청구항 ▼

In a so-called ramjet and booster rocket, a combustion chamber presenting a first speed of propulsion of the rocket type, called launching speed, obtained by the reaction of a fuel and a supporter of combustion disposed in the combustion chamber, and a second speed of propulsion, called cruising spe

In a so-called ramjet and booster rocket, a combustion chamber presenting a first speed of propulsion of the rocket type, called launching speed, obtained by the reaction of a fuel and a supporter of combustion disposed in the combustion chamber, and a second speed of propulsion, called cruising speed, for which the supporter of combustion is constituted by atmospheric air, said combustion chamber comprising an inner envelope provided with upstream lateral ports for the inlet of air and a downstream nozzle for ejecting the combustion gases, to allow functioning of the rocket at cruising speed; an outer envelope, concentric to the inner envelope and closed, with the exclusion of a single rear port for the ejection of the gases, to allow functioning of the rocket at launching speed, and separating means for separating from the combustion chamber at least a part of the outer envelope, at the end of the launching phase, in order to ensure the clearance of the upstream lateral ports of the inner envelope.