Embedded pressurization system for hybrid rocket motor

In a hybrid rocket motor including a combustion chamber, a liquid propellant component container disposed outside the combustion chamber, and first conduit means leading from the container into the combustion chamber, the combination comprising:

• a solid propellant component grain supported inside the combustion chamber;
• a pressurizing gas tank supported inside the combustion chamber which is at least partially imbedded in and provides support for the grain;
• and
• second conduit means leading from the tank into the container.

In a hybrid rocket motor including a combustion chamber, a liquid propellant component container disposed outside the combustion chamber, and first conduit means leading from the container into the combustion chamber, the combination comprising:

• a solid propellant component grain supported inside the combustion chamber;
• a pressurizing gas tank which is at least partially imbedded in and provides support for the grain;
• and
• second conduit means leading from the tank into the container;
• the grain being formed with longitudinal flow passageways for combustive flow of said liquid propellant component therethrough, the tank being imbedded in a radially central portion of the grain with the flow passageways formed radially outward thereof;
• the grain comprising a central hub in which the tank is embedded, an outer ring, and a plurality of radial spokes interconnecting the hub and ring, the flow passageways being defined between the spokes.