Simple solid propellant rocket engine and super-staged rocket

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.

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.