Chapter 12 - Solid Propellant Rockets

Abstract

This chapter describes solid rocket and its propellant. The solid rocket is so called because it consists of a mixture of oxidizer and fuel in the form of a solid completely encased in a tank that serves as a pressure vessel and to which is attached a nozzle. Thus, there is no need for separate tanks of oxidizer and fuel or for means to introduce them into the combustion chamber in correct ratio. Burning rate and combustion chamber pressure are discussed. Erosive burning leads to high longitudinal gas velocity in the combustion cavity, particularly at the throat end of the chamber. Materials used for the motor casing must support the grain and contain the combustion chamber pressure during operation. Materials usually used for this purpose include the steel and aluminum alloys—as well as titanium and—increasingly, composite materials. Solid rockets typically use simple conical nozzle. Further hybrid rockets are studied. Hybrid rockets occupy a sought-after middle ground between liquid propellant and solid propellant rockets use a solid fuel but a liquid oxidizer.