Author name: Gurupriya Dey Sarkar

The term “Liquid Flyback Booster” typically refers to a reusable booster stage of a rocket that uses liquid propulsion and is designed to return to Earth for recovery and reuse. Liquid Flyback Boosters are designed for reusability, and their thrust force equations would include additional parameters related to their return and landing phases, such as […]

Laser Thermal Rocket Engines are a theoretical concept that involves using a laser beam to heat a propellant, typically hydrogen, to generate thrust. The thrust force in a Laser Thermal Rocket Engine can be described using a modified version of the rocket thrust equation. This concept is more complex than traditional rocket engines, and the

“Deep space engines” is a broad term that could refer to various propulsion systems designed for spacecraft intended for deep space exploration. The choice of propulsion depends on mission requirements, fuel efficiency, and the spacecraft’s intended destination. One common type of propulsion for deep space missions is electric propulsion, such as ion thrusters. Electric propulsion

Ablative rocket engines use a combustion process that erodes or ablates the material from the engine’s internal surfaces to produce thrust. Ablative rocket engines are often used in applications where simplicity and cost-effectiveness are priorities. The ablation process helps dissipate the heat generated during combustion, preventing damage to the engine. However, the erosion of the

Hypergolic rocket engines use hypergolic propellants, which are substances that ignite spontaneously upon contact with each other. Hypergolic rocket engines are known for their simplicity and reliability, as they eliminate the need for an external ignition source. They are commonly used in spacecraft for various applications, including orbit insertion, attitude control, and orbital maneuvers. The

Liquid bipropellant engines are rocket engines that use two liquid substances, typically a fuel and an oxidizer, as propellants. Liquid bipropellant engines are commonly used in various space missions due to their controllability and versatility. The specific details of the engine’s performance depend on the choice of propellants, combustion efficiency, and the design of the

Pulsed Plasma Thrusters (PPTs) are a type of electric propulsion system that use pulsed plasma discharges to generate thrust. The thrust force in a Pulsed Plasma Thruster can be described using the basic rocket thrust equation. PPTs are known for their simplicity and reliability, making them suitable for small satellites and spacecraft for attitude control

Grid Ion Thrusters, also known as gridded ion thrusters or electrostatic ion thrusters, operate based on the principle of electrostatic acceleration of ions to generate thrust. The thrust force in a Gridded Ion Thruster can be described using the basic rocket thrust equation. Grid Ion Thrusters are known for their high efficiency and are commonly

Hall-Effect Thruster Engines, also known as Hall-effect thrusters or ion thrusters, use electric and magnetic fields to accelerate ions and produce thrust. The thrust force in a Hall-Effect Thruster can be described using the basic rocket thrust equation. Hall-Effect Thrusters are known for their efficiency and are commonly used in long-duration space missions. The thrust

Magnetoplasma Thruster Engines, often referred to as Hall-effect thrusters or ion thrusters, use electric and magnetic fields to accelerate ions and produce thrust. The thrust force in a Magnetoplasma Thruster Engine can be described using the basic rocket thrust equation. The thrust equation for a turbojet engine using control volume analysis is expressed as: where,