IS IT POSSIBLE TO USE A SPIKE NOZZLE WITH A SOLID FUEL MOTOR?
Sure. The propellant would have to be made to conform to an annular combustion chamber instead of a central conical combustion chamber but if that doesn’t present any incredible technological challenges, I don’t see why an aerospike nozzle couldn’t be used on a solid fuel motor. Since I’m a liquid rocket guy, this may not be the best answer in the world. Is there anyone out there who works in the solid rocket world who could give a better answer to this question and the following questions as well?