# Solid Rocket Engine

## Schematic

On this page, we show a schematic of a solid rocket engine. Solid rocket engines are used on air-to-air and air-to-ground missiles, on model rockets, and as boosters for satellite launchers. In a solid rocket, the fuel and oxidizer are mixed together into a solid **propellant** which is packed into a solid cylinder. A hole through the cylinder serves as a **combustion chamber**. When the mixture is ignited, combustion takes place on the surface of the propellant. A **flame front** is generated which burns into the mixture. The combustion produces great amounts of exhaust gas at high temperature and pressure. The amount of exhaust gas that is produced depends on the area of the flame front and engine designers use a variety of hole shapes to control the change in thrust for a particular engine. The hot exhaust gas is passed through a nozzle which accelerates the flow. **Thrust** is then produced according to Newton’s third law of motion.

## Determining thrust

The amount of thrust produced by the rocket depends on the design of the nozzle. The smallest cross-sectional area of the nozzle is called the **throat** of the nozzle. The hot exhaust flow is **choked** at the throat, which means that the Mach number is equal to 1.0 in the throat and the mass flow rate **m dot** is determined by the throat area. The area ratio from the throat to the exit **A _{e}** sets the exit velocity

**V**and the exit pressure

_{e}**p**. You can explore the design and operation of a rocket nozzle with our interactive thrust simulator program which runs on your browser.

_{e}The exit pressure is only equal to free stream pressure at some design condition. We must, therefore, use the longer version of the generalized thrust equation to describe the thrust of the system. If the free stream pressure is given by **p _{0}**, the thrust

**F**equation becomes:

\(\LARGE F=\dot{m}V_{e}+A_{e}(p_{e}-p_{0})\)

## Rockets in Space

Notice that there is no free stream mass times free stream velocity term in the thrust equation because no external air is brought on board. Since the oxidizer is mixed into the propellant, solid rockets can generate thrust in a vacuum where there is no other source of oxygen. That’s why a rocket will work in space, where there is no surrounding air, and a gas turbine or propeller will not work. Turbine engines and propellers rely on the atmosphere to provide the oxygen for combustion and as the working fluid in the generation of thrust.

The thrust equation given above works for both liquid and solid rocket engines. There is also an efficiency parameter called the specific impulse which works for both types of rockets and greatly simplifies the performance analysis for rocket engines.