Please enable JavaScript.
Coggle requires JavaScript to display documents.
Classification of Rocket Propulsion Systems - Coggle Diagram
Classification of Rocket Propulsion Systems
Cold-gas Thrusters
Expansion of pressurized gas at ambient temperature. Low performance
Electric Propulsion
Energy source and propellant are separate, which allows for higher propellant energy; the limitation is the size of the energy conversion system.
Chemical Propulsion
Transform chemical to thermal energy, and then expand. Higher performance.
Electrostatic, Electromagnetic
Directly accelerate the propellant.
Electrothermal
Transform electrical to thermal energy, and then expand
Liquid-Propellant Rocket Engines
Fuel and oxidizer are injected under pressure (> 400 atm) as a spray into the combustion chamber. Two ways to create a high injection-pressure:
Pressure-fed engines
Simple but heavy tanks to withstand the high pressure.
Small rocket engines (T < 4 − 5 kN) and short duration, such as for attitude control.
Pump-fed engines
Complex but lighter tanks.
Various types of combustion cycles: Open cycle, close cycle (staged cycle, full-flow staged cycle).
Large rocket engines, such as for launch vehicles.
Fluid Propellants
Monopropellant
Oxidizing agent and combustible matter in a single liquid substance. Stable at ambient storage condi- tions but decompose and yield hot combustion gases when heated or catalyzed in a chamber.
Cold-gas propellant
A gas is stored at ambient temperatures but at relatively high pressures.
Bipropellant
Liquid fuel and oxidizer are injected separately. A hypergolic combination self-ignites upon contact, whereas a non-hypergolic combination needs an ignition system.