Guided Missile Propulsion Section

Item Name Code (INC) 61617

Rocket Engines and Components: Federal Supply Class: FSC 2845; NATO Supply Classification Class: NSC 2845
Engines, Turbines, and Components: Federal Supply Group: FSG 28; NATO Supply Classification Group: NSG 28
Item Hits: 160

INC 61617 Guided Missile Propulsion Section

An item consisting of one or more ROCKET ENGINE or ROCKET MOTOR and a portion of the outer aerodynamic shell or skin of a GUIDED MISSILE (as modified) or a BOMB, GUIDED (as modified), designed to provide all or part of the thrust required to power the weapon's flight. May include either moveable control surface(s), steering jets, jet vane(s), or a combination of these, unless equipped with an articulated nozzle. May also have stabilizing fins, but only in combination with other controlling surfaces, jets, or the like. It is designed to mate with other guided missile section(s) or guided bomb sections. Addition of this to a BOMB, GUIDED (as modified) creates a GUIDED MISSILE (as modified). Excludes ROCKET MOTOR; ROCKET MOTOR CLUSTER; and GUIDED MISSILE MAIN ASSEMBLAGE.

Additional Information for Guided Missile Propulsion Section

The Guided Missile Propulsion Section refers to the component of a guided missile that is responsible for providing the necessary thrust and propulsion to propel the missile towards its intended target. It is a critical part of the missile system, as it determines the missile's speed, range, and maneuverability.

The propulsion section typically consists of several key components, including:

1. Rocket Motor: This is the primary source of propulsion for the missile. It is usually a solid-fuel or liquid-fuel rocket motor that generates high-pressure gases to produce thrust. The rocket motor is ignited at the time of launch and continues to burn until its fuel is depleted.

2. Nozzle: The nozzle is the exhaust outlet of the rocket motor. It is designed to efficiently convert the high-pressure gases into a high-velocity exhaust jet, which creates the thrust necessary to propel the missile forward. The shape and design of the nozzle play a crucial role in optimizing the missile's performance.

3. Thrust Vector Control (TVC) System: The TVC system is responsible for controlling the direction of the thrust generated by the rocket motor. It consists of movable control surfaces, such as fins or vanes, located in the exhaust jet. By adjusting the position of these control surfaces, the TVC system can steer the missile and enable it to change its course during flight.

4. Propellant Tanks: In the case of liquid-fueled missiles, the propulsion section also includes propellant tanks that store the liquid fuel and oxidizer. These tanks are designed to withstand the high pressures and temperatures associated with the combustion process.

5. Ignition System: The ignition system is responsible for initiating the combustion process in the rocket motor. It typically consists of an igniter or a pyrotechnic device that ignites the propellant mixture, initiating the controlled burn and generating thrust.

Overall, the Guided Missile Propulsion Section is a critical component of a guided missile, providing the necessary thrust and control to ensure the missile reaches its intended target accurately and effectively.