초록 ▼

A solid propellant rocket engine includes: a propellant formed into a predetermined shape having a combustion cavity and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle configured and positioned to expand the hot, high-pressure gas into the atmosphere, where the prope

A solid propellant rocket engine includes: a propellant formed into a predetermined shape having a combustion cavity and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle configured and positioned to expand the hot, high-pressure gas into the atmosphere, where the propellant forms the nozzle as a part of the predetermined shape. A multi-stage rocket unit, a multi-engine rocket stage, and a super-staged rocket each has many rocket engines.

대표청구항 ▼

I claim: 1. A multi-engine solid propellant rocket stage, comprising a plurality of solid propellant rocket engines, each solid propellant rocket engine comprising: a propellant formed into a predetermined shape and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle con

I claim: 1. A multi-engine solid propellant rocket stage, comprising a plurality of solid propellant rocket engines, each solid propellant rocket engine comprising: a propellant formed into a predetermined shape and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle configured and positioned to expand said hot, high-pressure gas into the atmosphere, wherein said predetermined shape comprises a combustion cavity, wherein said propellant forms said nozzle as a part of said predetermined shape, wherein said plurality of rocket engines are connected in parallel so that more than one of said rocket engines may burn and provide thrust simultaneously, wherein nozzles of substantially all of said plurality of rocket engines are configured and positioned to expand gas into the atmosphere in a substantially same direction, wherein said multi-engine solid propellant rocket stage is shaped as an integrally formed stackable plate, and wherein corresponding points in said predetermined shapes of said plurality of rocket engines are substantially coplanar. 2. A method of igniting a multi-engine rocket stage, comprising: providing a multi-engine solid propellant rocket stage as claimed in claim 1, wherein said multi-engine rocket stage has a substantially circular cross section and comprises a plurality of annuluses each comprising a plurality of rocket engines; igniting at a first time substantially all rocket engines in a first of said plurality of annuluses; and igniting at a second time substantially all rocket engines in a second of said plurality of annuluses, wherein said second time follows said first time by a substantial fraction, but not more than approximately 50%, of a burn time of said rocket engines. 3. A method for manufacturing the multi-engine solid propellant rocket stage as claimed in claim 1, comprising: forming said propellant into a plate; and forming a plurality of holes in said plate by at least one of molding said holes and boring said holes, whereby said holes define combustion chambers and nozzles of said plurality of rocket engines. 4. The multi-engine solid propellant rocket stage as claimed in claim 1, further comprising a fast-burning igniter located in said combustion cavity of at least one of said rocket engines, wherein said igniter has at least one of a substantially higher burn rate and a substantially lower density than said propellant. 5. A method for manufacturing the multi-engine solid propellant rocket stage as claimed in claim 4, comprising: providing said igniter, said igniter having a predetermined exterior shape; providing said propellant in a substantially fluid form by nature of being molten or mixed with at least one of a fluid binder and a volatile solvent; displacing said propellant by said igniter; and causing said propellant to solidify into said predetermined shape of at least one of said rocket engines, wherein a shape of said combustion cavity of said at least one of said rocket engines corresponds to said predetermined exterior shape of said igniter. 6. The multi-engine solid propellant rocket stage as claimed in claim 1, wherein said predetermined shape of at least one of said rocket engines comprises an indentation configured so that, at an end of a burn of said rocket engine, said rocket engine preferentially bursts and ejects said hot, high pressure gas at a location of said indentation. 7. The multi-engine solid propellant rocket stage as claimed in claim 1, wherein said plurality of rocket engines are integrally connected in parallel. 8. A super staged solid propellant rocket, comprising a plurality of multi-engine solid propellant rocket stages, each multi-engine solid propellant rocket stage comprising a plurality of solid propellant rocket engines, each solid propellant rocket engine comprising: a propellant formed into a predetermined shape and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle configured and positioned to expand said hot, high-pressure gas into the atmosphere, wherein said predetermined shape comprises a combustion cavity, wherein said propellant forms said nozzle as a part of said predetermined shape, wherein said plurality of rocket engines in each multi-engine solid rocket stage are connected in parallel so that more than one of said rocket engines may burn and provide thrust simultaneously, wherein nozzles of substantially all of said plurality of rocket engines in each multi-engine solid rocket stage are configured and positioned to expand gas into the atmosphere in a substantially same direction, wherein said multi-engine solid rocket stages are directly or indirectly stacked on top of each other, wherein each of at least most rocket engines in an upper stage of two adjacent multi-engine stages comprises a first fast-burning igniter located in its combustion cavity, wherein said first igniter has at least one of a substantially higher burn rate and a substantially lower density than said propellant, and wherein said super-staged rocket comprises a layer of a second fast-burning igniter located between said two adjacent multi-engine stages and configured to ignite said first fast-burning igniter of substantially every of said rocket engines in said upper stage. 9. The super staged solid propellant rocket as claimed in claim 8, wherein said predetermined shape of at least one of said rocket engines comprises an indentation configured so that, at an end of a burn of said rocket engine, said rocket engine preferentially bursts and ejects said hot, high pressure gas at a location of said indentation. 10. A method of igniting a super staged solid propellant rocket, comprising: providing the super staged solid propellant rocket as claimed in claim 8, wherein at least one of said multi-engine rocket stages has a substantially circular cross section and comprises a plurality of annuluses each comprising a plurality of rocket engines; igniting at a first time substantially all rocket engines in a first of said plurality of annuluses; and igniting at a second time substantially all rocket engines in a second of said plurality of annuluses, wherein said second time follows said first time by a substantial fraction, but not more than approximately 50%, of a burn time of said rocket engines. 11. A method for manufacturing the super staged solid propellant rocket as claimed in claim 8, comprising: forming said propellant into a plate; and forming a plurality of holes in said plate by at least one of molding said holes and boring said holes, whereby said holes define combustion chambers and nozzles of said plurality of rocket engines of at least one of said multi-engine rocket stages. 12. The super staged solid propellant rocket as claimed in claim 8, wherein said plurality of rocket engines in at least one of said multi-engine rocket stages are integrally connected in parallel. 13. A method for manufacturing the super staged solid propellant rocket as claimed in claim 8, comprising: providing said first fast-burning igniter, said first igniter having a predetermined exterior shape; providing said propellant in a substantially fluid form by nature of being molten or mixed with at least one of a fluid binder and a volatile solvent; displacing said propellant by said first igniter; and causing said propellant to solidify into said predetermined shape of at least one of said rocket engines, wherein a shape of said combustion cavity of said at least one of said rocket engines corresponds to said predetermined exterior shape of said first igniter. 14. A super staged solid propellant rocket, comprising a plurality of multi-engine solid propellant rocket stages, each multi-engine solid propellant rocket stage comprising a plurality of solid propellant rocket engines, each solid propellant rocket engine comprising: a propellant formed into a predetermined shape and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle configured and positioned to expand said hot, high-pressure gas into the atmosphere, wherein said predetermined shape comprises a combustion cavity, wherein said propellant forms said nozzle as a part of said predetermined shape, wherein said plurality of rocket engines in each multi-engine solid rocket stage are connected in parallel so that more than one of said rocket engines may burn and provide thrust simultaneously, wherein nozzles of substantially all of said plurality of rocket engines in each multi-engine solid rocket stage are configured and positioned to expand gas into the atmosphere in a substantially same direction, wherein said multi-engine solid rocket stages are directly or indirectly stacked on top of each other, wherein said super-staged rocket has an approximately pyramid shape, whereby a cross-sectional area of an upper stage of said stacked multi-engine stages is smaller than that of a lower stage of said rocket. 15. The super staged solid propellant rocket as claimed in claim 14, further comprising a fast-burning igniter located in said combustion cavity of at least one of said rocket engines, wherein said igniter has at least one of a substantially higher burn rate and a substantially lower density than said propellant. 16. A method for manufacturing the super staged solid propellant rocket as claimed in claim 15, comprising: providing said igniter, said igniter having a predetermined exterior shape; providing said propellant in a substantially fluid form by nature of being molten or mixed with at least one of a fluid binder and a volatile solvent; displacing said propellant by said igniter; and causing said propellant to solidify into said predetermined shape of at least one of said rocket engines, wherein a shape of said combustion cavity of said at least one of said rocket engines corresponds to said predetermined exterior shape of said igniter. 17. The super staged solid propellant rocket as claimed in claim 14, wherein said predetermined shape of at least one of said rocket engines comprises an indentation configured so that, at an end of a burn of said rocket engine, said rocket engine preferentially bursts and ejects said hot, high pressure gas at a location of said indentation. 18. A method of igniting a super staged solid propellant rocket, comprising: providing the super staged solid propellant rocket as claimed in claim 14, wherein at least one of said multi-engine rocket stages has a substantially circular cross section and comprises a plurality of annuluses each comprising a plurality of rocket engines; igniting at a first time substantially all rocket engines in a first of said plurality of annuluses; and igniting at a second time substantially all rocket engines in a second of said plurality of annuluses, wherein said second time follows said first time by a substantial fraction, but not more than approximately 50%, of a burn time of said rocket engines. 19. A method for manufacturing the super staged solid propellant rocket as claimed in claim 14, comprising: forming said propellant into a plate; and forming a plurality of holes in said plate by at least one of molding said holes and boring said holes, whereby said holes define combustion chambers and nozzles of said plurality of rocket engines of at least one of said multi-engine rocket stages. 20. The super staged solid propellant rocket as claimed in claim 14, wherein said plurality of rocket engines in at least one of said multi-engine rocket stages are integrally connected in parallel.