Multi-functional pulse-divided rocket
View Patent ↗A multi-pulse rocket is equipped with a thermally insulating barrier that serves as a rupture disk or a movable plug or plate separating staged propellant grains. When a rupture disk it used, the disk can be equipped with a pyrotechnic actuator to weaken the disk upon command, enabling the propellant grain on the fore side of the disk to burst the disk at a relatively low pressure when ignition of the propellant grain is needed for additional thrust. Rupturing of the disk can also be controlled by attitude maneuvering ports on the fore side of the barrier whose open or closed conditions are controlled by independently operable closures. When a movable plug is used, the plug is movable between a closed position separating rocket chamber into subchambers isolating the propellant grains from each other and an open position allowing the flow of combustion gas between the two subchambers to achieve additional axial thrust. In all cases, the barrier when intact serves to contain both propellant grains regardless of whether one or both is ignited. The propellant grain on the fore side of the barrier can thus be used for either axial thrust augmentation or for attitude maneuvering.
1. A multi-purpose rocket motor comprising:
(a) a chamber having a longitudinal axis terminating at a fore end and an aft end, and comprising a nozzle at said aft end,
(b) a thermally insulating barrier dividing said chamber into fore and aft segments arranged along said longitudinal axis, with a fore propellant grain in said fore segment and an aft propellant grain in said aft segment,
(c) an attitude maneuvering port in said fore segment oriented to produce attitude maneuvering of said rocket motor; and
(d) a guidance and control system selecting between
a first mode of operation wherein said barrier is in a closed condition, causing combustion gas from combustion of said fore propellant grain to be released from said chamber through said attitude maneuvering port, and
a second mode of operation wherein said barrier is in an open condition permitting flow of combustion gas generated in said fore segment through said aft segment to achieve combined axial thrust from said fore and aft propellant grains when combusted, said guidance and control system being independent of ignition of either said fore propellant grain or said aft propellant grain, and wherein said barrier is sufficiently frangible to rupture to said open condition upon ignition of said fore propellant grain when said attitude maneuvering port is closed.
2. The multi-purpose rocket of claim 1 wherein said thermally insulating barrier comprises a rupture disk facing said aft segment of said chamber and a frangible support member facing said fore segment of said chamber.
3. A multi-purpose rocket motor comprising:
(a) a chamber having a longitudinal axis terminating at a fore end and an aft end, and comprising a nozzle at said aft end,
(b) a thermally insulating barrier dividing said chamber into fore and aft segments arranged along said longitudinal axis, with a fore propellant grain in said fore segment and an aft propellant grain in said aft segment,
(c) an attitude maneuvering port in said fore segment oriented to produce attitude maneuvering of said rocket motor; and
a guidance and control system selecting between
a first mode of operation wherein said barrier is in a closed condition, causing combustion gas from combustion of said fore propellant grain to be released from said chamber through said attitude maneuvering port, and
a second mode of operation wherein said barrier is in an open condition permitting flow of combustion gas generated in said fore segment through said aft segment to achieve combined axial thrust from said fore and aft propellant grains when combusted, said guidance and control system being independent of ignition of either said fore propellant grain or said aft propellant grain, and wherein said barrier contains score lines to control rupture of said barrier and to provide said barrier with a burst pressure that is lower by at least 1,000 psi due to inclusion of said score lines.
4. The multi-purpose rocket of claim 3 , wherein score lines lower said burst pressure from about 5,000 psi to about 1,000 psi.