Author name: Gurupriya Dey Sarkar

Full Flow Staged Combustion (FFSC) engines are a type of rocket engine that uses a staged combustion cycle where both the fuel and oxidizer are fully burned before entering the combustion chamber. These engines are known for their high efficiency and performance. In a Full Flow Staged Combustion engine, the mass flow rate of exhaust […]

Pulsed Detonation Engines (PDEs) are a type of propulsion system that relies on the detonation of fuel-air mixtures to generate thrust. These engines operate by initiating detonations in a cyclical or pulsed manner, producing high-speed exhaust gases. In a Pulsed Detonation Engine, the mass flow rate of exhaust gases is influenced by the rate of

For a methane rocket engine, the mass flow rate of exhaust gases is influenced by the rate of combustion of methane and the oxidizer (e.g., liquid oxygen). The exhaust velocity is determined by the combustion characteristics and the design of the rocket nozzle. The pressure of the exhaust gases is dependent on the combustion process.

A pulse-fed engine is a type of rocket engine that receives propellant in discrete pulses rather than continuously. These engines are commonly used in certain spacecraft propulsion systems, particularly those requiring precise control and modulation of thrust. In a pulse-fed engine, the mass flow rate of exhaust gases during each pulse is determined by the

Hybrid rocket engines combine features of both liquid and solid rocket engines. In a hybrid rocket engine, one component is typically in a liquid state (such as a liquid oxidizer), while the other component is in a solid state (such as a solid fuel). For a hybrid rocket, the mass flow rate of exhaust gases

The Saturn V was the launch vehicle used in the Apollo program, and it had multiple stages, each with its own rocket engines and nozzles. The first stage, known as the S-IC stage, was powered by five Rocketdyne F-1 engines, and the second stage, known as the S-II stage, was powered by five Rocketdyne J-2

Cold gas propulsion systems use pressurized gases (usually inert gases like nitrogen or helium) for thrust generation. Unlike traditional rocket engines that involve combustion, cold gas propulsion relies on the rapid expulsion of pressurized gas to produce thrust. In a cold gas propulsion system, the mass flow rate of expelled gas is determined by the

The thrust force of a liquid propellant rocket nozzle can be calculated using the basic rocket thrust equation. In a liquid propellant rocket, the mass flow rate of exhaust gases is influenced by factors such as the rate of propellant combustion and the efficiency of the combustion process. The exhaust velocity is affected by the

Solid propellant rocket nozzles are crucial components in rocketry that help direct and accelerate the flow of exhaust gases generated by the combustion of solid propellant. The design of the rocket nozzle is critical in determining the efficiency of the rocket motor. The specific shape and dimensions of the nozzle influence the expansion of the

Ion thrusters, also known as ion propulsion systems or ion drives, operate on the principle of accelerating ions (usually xenon) to generate thrust. These engines are commonly used in spacecraft for long-duration missions due to their high specific impulse. Control volume analysis, as traditionally used in fluid dynamics, may not be directly applicable to ion