Author name: Gurupriya Dey Sarkar

Deep space engines are typically designed for long-duration missions and operate in the vacuum of space. Various propulsion systems can be used for deep space missions, including chemical rockets, ion thrusters, solar sails, and nuclear propulsion systems. To calculate the specific impulse for a specific deep space engine, you would need specific data on thrust, […]

Ablative rocket engines use ablative materials in the combustion chamber or nozzle, which are designed to gradually erode or ablate as the rocket operates. For ablative rocket engines, the thrust is generated by the expansion of hot gases through the nozzle, and ablative materials in the combustion chamber or nozzle are intentionally designed to erode

A “hydrazine thruster” is a type of rocket engine that uses hydrazine as a propellant. These thrusters are commonly used in spacecraft for various purposes, such as attitude control, orbital maneuvers, and spacecraft station-keeping. Hydrazine is often used as a monopropellant or as one component of a bipropellant system. In the context of monopropellant hydrazine

For liquid bipropellant rocket engines, the thrust is generated by the combustion of two separate propellants (typically a liquid fuel and a liquid oxidizer) in a combustion chamber. The mass flow rate of the propellants, combustion efficiency, and other factors influence the specific impulse. To calculate the specific impulse for a specific liquid bipropellant rocket

Pulsed plasma thrusters (PPTs) are a type of electric propulsion system used in spacecraft. For pulsed plasma thrusters, the thrust is typically generated by the acceleration of ionized plasma. The mass flow rate of the propellant is influenced by the power applied to the thruster, the efficiency of ionization and acceleration, and the specific design

Gridded ion thrusters, also known as electrostatic ion thrusters or ion propulsion systems, are a type of electric propulsion used in spacecraft. For gridded ion thrusters, the thrust is typically generated by the accelerated ions. The mass flow rate of the propellant is influenced by the power applied to the thruster, the efficiency of ionization

Hall effect thrusters are a type of electric propulsion system that uses electric and magnetic fields to ionize and accelerate propellant. For Hall effect thrusters, the thrust is typically generated by the accelerated ions. The mass flow rate (�˙m˙) of the propellant is influenced by the power applied to the thruster, the efficiency of ionization

Magnetoplasma thrusters, including designs like the Variable Specific Impulse Magnetoplasma Rocket (VASIMR), are types of electric propulsion systems that use magnetic and electric fields to ionize and accelerate propellant. For magnetoplasma thrusters, the thrust is typically generated by the accelerated ions or plasma. The mass flow rate of the propellant is influenced by the power

Nuclear pulse detonation rocket engines (NPDR) are theoretical propulsion concepts that involve the use of nuclear detonations to create high-speed shockwaves that produce thrust. For nuclear pulse detonation rocket engines, the challenge lies in defining parameters such as burn time and mass flow rate, as their operation involves discrete nuclear detonations rather than continuous combustion.

Full-flow staged combustion engines represent a type of rocket engine design where both the fuel and oxidizer are fully combusted in separate combustion cycles, and the resulting hot gases are combined and expanded through a rocket nozzle to produce thrust. To assess the specific impulse for a specific full-flow staged combustion engine, you would need