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A propulsion system, such as for use in a missile, includes a multinozzle grid having a pair of plates that are separably mechanically coupled together. When coupled together in a first configuration, the plates provide multiple nozzles in a first nozzle configuration (geometry). Separation of the p

A propulsion system, such as for use in a missile, includes a multinozzle grid having a pair of plates that are separably mechanically coupled together. When coupled together in a first configuration, the plates provide multiple nozzles in a first nozzle configuration (geometry). Separation of the plates, such as by separating an aft plate from a forward plate that remains with the missile, reconfigures the multinozzle grid to a second configuration that has nozzles in a second nozzle configuration (geometry). The nozzle configurations may be suitable for different types of propulsion mechanisms. The hybrid propulsion system utilizing the multinozzle grid may include a pair of pressurized gas sources, for example a solid rocket fuel and a combustion chamber for a ramjet.

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1. A hybrid propulsion system comprising: a solid rocket motor;a ramjet; anda reconfigurable multinozzle grid;wherein the solid rocket motor and the ramjet both pass pressurized gas through the reconfigurable multinozzle grid;wherein the multinozzle grid includes: a forward plate; andan aft plate;wh

1. A hybrid propulsion system comprising: a solid rocket motor;a ramjet; anda reconfigurable multinozzle grid;wherein the solid rocket motor and the ramjet both pass pressurized gas through the reconfigurable multinozzle grid;wherein the multinozzle grid includes: a forward plate; andan aft plate;wherein the plates are separably mechanically coupled together;wherein, when the plates are mechanically coupled together, the plates define a plurality of converge-diverge nozzles each having a first configuration;wherein, when the plates are separated, the nozzles transform to a second configuration, different from the first configuration, with the nozzles defined by only one of the plates; andwherein the multinozzle grid is configured to change from the first configuration to the second configuration during operation of the propulsion system, such that 1) the multinozzle grid is in the first configuration when pressurized gasses from the solid rocket motor pass through the multinozzle grid, and 2) the multinozzle grid is in the second configuration when pressurized gasses from the ramjet pass through the multinozzle grid. 2. The propulsion system of claim 1, wherein the solid rocket motor includes: a case; anda solid propellant in a combustion chamber enclosed by the case;wherein the mutlinozzle grid is attached to an aft end of the case; andwherein the ramjet includes an inlet duct attached to a forward end of the case. 3. The propulsion system of claim 2, further comprising a pressure door that selectively allows airflow from the inlet duct to the combustion chamber. 4. The propulsion system of claim 3, wherein the pressure door hinges off of a center line of the pressure door, thereby automatically opening when pressure in the inlet duct exceeds pressure in the combustion chamber. 5. The propulsion system of claim 1, wherein the plates are both circular disks. 6. The propulsion system of claim 1, wherein further comprising a coupling mechanism separably coupling the plates together. 7. The propulsion system of claim 6, wherein the coupling mechanism includes a separation mechanism for separating the plates. 8. The propulsion system of claim 6, wherein the coupling mechanism includes a severable band around perimeters of the plates. 9. The propulsion system of claim 1, wherein the plates are separably mechanically coupled together by a coupling mechanism separably coupling the plates together; and wherein the coupling mechanism includes a separation mechanism separably joining central axes of the disks, for separating the plates of the multinozzle grid as the multinozzle grid changes from the first configuration to the second configuration during operation of the propulsion system. 10. A hybrid propulsion system comprising: a solid rocket motor;a ramjet; anda reconfigurable multinozzle grid;wherein the solid rocket motor and the ramjet both pass pressurized gas through the reconfigurable multinozzle grid;wherein the multinozzle grid includes: a first plate; anda second plate;wherein the plates are separably mechanically coupled together by a coupling mechanism separably coupling the plates together;wherein, when the plates are mechanically coupled together, the plates define a plurality of converge-diverge nozzles each having a first configuration; andwherein, when the plates are separated, the nozzles transform to a second configuration, different from the first configuration, with the nozzles defined by only one of the plates; andwherein the coupling mechanism allows separation of the plates during operation of the propulsion system. 11. The propulsion system of claim 10, wherein the plates are both circular disks; andwherein the coupling mechanism includes a separation mechanism separably joining central axes of the disks. 12. The propulsion system of claim 10, wherein the plates are both circular disks; andwherein the coupling mechanism includes a severable band around circumferences of the disks. 13. The propulsion system of claim 10, wherein the coupling mechanism includes a pyrotechnic device used to initiate separation of the plates. 14. The propulsion system of claim 10, wherein the solid rocket motor includes: a case; anda solid propellant in a combustion chamber enclosed by the case;wherein the mutlinozzle grid is attached to an aft end of the case; andwherein the ramjet includes an inlet duct attached to a forward end of the case. 15. The propulsion system of claim 14, further comprising a pressure door that selectively allows airflow from the inlet duct to the combustion chamber. 16. The propulsion system of claim 15, wherein the pressure door hinges off of a center line of the pressure door, thereby automatically opening when pressure in the inlet duct exceeds pressure in the combustion chamber. 17. A hybrid propulsion system comprising: a solid rocket motor;a ramjet; anda reconfigurable multinozzle grid;wherein the solid rocket motor and the ramjet both pass pressurized gas through the reconfigurable multinozzle grid;wherein the multinozzle grid includes: a forward plate; andan aft plate;wherein the plates are separably mechanically coupled together;wherein, when the plates are mechanically coupled together, the plates define a plurality of converge-diverge nozzles each having a first configuration;wherein, when the plates are separated, the nozzles transform to a second configuration, different from the first configuration, with the nozzles defined by only one of the plates; andwherein the second configuration includes the nozzles having wider openings than in the first configuration. 18. The propulsion system of claim 17, wherein the plates are both circular disks.