Patent ID: 6092366
Filing Date: 2000-07-25
Classification: F02K

Abstract:
A hybrid propulsion system for a projectile launchable from a launch platform, comprising:a container having a fluid reactant therein;a combustion chamber containing a solid reactant therein and having a thrust nozzle at one end thereof;a fluid-flow pathway between said fluid reactant container and said combustion chamber; anda flow control member comprising a rupturable diaphragm operatively associated with said fluid-flow pathway to obstruct flow through said fluid-flow pathway when the projectile is in a prelaunch configuration, said diaphragm member including an indentation defining a preferential fracture line and being adapted to rupture therealong to thereby unobstruct flow through said fluid-flow pathway and admit fluid reactant from said container into said chamber for reaction with said solid reactant to produce thrust for propelling the projectile.