Author name: Gurupriya Dey Sarkar

Magnetoplasma thrusters, also known as magnetoplasmadynamic (MPD) thrusters, are a type of electric propulsion system that uses magnetic and electric fields to ionize and accelerate propellant to generate thrust. Similar to ion thrusters, they are known for their high specific impulse and propellant efficiency. Magnetoplasma thrusters use a magnetized plasma as the propellant. The propellant […]

The propulsive efficiency (ηp​) of an ion thruster rocket engine, like other rocket engines, is often expressed in terms of the specific impulse (Isp​), which is a measure of the efficiency of the engine. Ion thrusters, also known as electric propulsion or ion propulsion systems, use electric power to ionize and accelerate propellant (usually xenon

The Saturn V rocket, used during the Apollo program, was a multi-stage liquid-fueled launch vehicle. It used a variety of rocket engines for propulsion, including the F-1 engines on the first stage. These engines burned a combination of liquid oxygen (LOX) and kerosene (RP-1) to generate thrust. The propulsive efficiency (ηp​) of a rocket engine,

The propulsive efficiency (ηp​) of a cold gas propulsion rocket engine is a measure of how effectively the stored gas (typically compressed gas) is converted into kinetic energy of the exhaust gases, resulting in thrust. Unlike liquid or solid propellant rockets, cold gas propulsion systems don’t involve combustion; they simply release pressurized gas to generate

The propulsive efficiency (ηp​) of a liquid propellant rocket engine is a measure of how effectively the chemical energy stored in the liquid propellants is converted into kinetic energy of the exhaust gases, resulting in thrust. The efficiency is typically expressed in terms of the specific impulse (Isp​), which is related to the exhaust velocity.

The propulsive efficiency of a solid propellant rocket engine is a measure of how efficiently the chemical energy stored in the solid propellant is converted into kinetic energy of the exhaust gases, ultimately producing thrust. For solid rocket engines, the propulsive efficiency is often expressed in terms of the specific impulse (Isp​), which is a

The propulsive efficiency of a rocket engine is a measure of how effectively the engine converts the chemical energy stored in the propellants into kinetic energy of the exhaust gases, which produces thrust. It is a ratio of the useful kinetic energy of the exhaust gases to the total energy content of the propellants. The

The RD-170 is a liquid rocket engine designed and produced in Russia. Specifically, it is a staged combustion cycle rocket engine. It’s part of the family of rocket engines developed by NPO Energomash. For staged combustion cycle engines, the combustion process is more complex than in traditional rocket engines, and the adiabatic flame temperature can

The Saturn V rocket, used during the Apollo program, was a multi-stage liquid-fueled launch vehicle. It used a variety of rocket engines for propulsion, including the F-1 engines on the first stage. These engines burned a combination of liquid oxygen (LOX) and kerosene (RP-1) to generate thrust. The adiabatic flame temperature Tadiabatic is an estimate of

In a Cold Gas Propulsion Rocket Engine, the term “cold gas” refers to a propulsion system that uses compressed gas, typically stored at ambient or low temperatures, as a propellant. The combustion process in this type of rocket engine is characterized by the rapid expansion of the compressed gas through a nozzle to generate thrust.