Propulsion Calculator

The rocket equation for Cold Gas Propulsion (CGP) systems is derived similarly to other rocket equations but takes into account the specific characteristics of cold gas thrusters, which use pressurized gas expelled through a rocket nozzle for propulsion. In these systems, there is no combustion involved. The rocket equation for Cold Gas Propulsion can be […]

The rocket equation describes the relationship between the velocity change (Δv), the effective exhaust velocity (ve​), and the initial and final masses of a rocket. For liquid propellant rockets, the rocket equation is expressed as: Where: Δv is the change in velocity of the rocket (in meters per second, m/s). Isp​ is the specific impulse

The rocket equation is a fundamental equation in rocketry that describes the relationship between the velocity of a rocket (Δv), the effective exhaust velocity of the propellant (ve​), and the initial and final masses of the rocket. The rocket equation for solid propellant rockets is derived similarly to other types of rockets, but the specific

Cold Gas Propulsion (CGP) systems use pressurized gas, often stored at cryogenic temperatures, to provide thrust. These systems are simpler than liquid or solid rocket engines but are often used for specific applications, such as attitude control systems or small-scale propulsion. The burnout mass in the context of a Cold Gas Propulsion system would be

The burnout mass of a liquid propellant rocket engine refers to the mass of the rocket stage or engine casing and any remaining components after the liquid propellants have been fully consumed. Similar to the solid propellant case, the burnout mass is an important parameter in rocket design and performance analysis for liquid-fueled rockets. The

The burnout mass of a solid propellant rocket engine is the mass of the rocket motor casing and any remaining structural components after the propellant has been completely consumed or burned during a rocket launch. This parameter is crucial in rocket design and performance analysis. The formula to calculate the burnout mass Mburnout can be expressed

The rocket equation is a fundamental equation in astronautics that describes the relationship between the mass of a rocket, the speed of its exhaust, and the resulting velocity change (delta-v) it can achieve. It is expressed as follows: Parameters: ΔV (Change in Velocity): Definition: The change in velocity the rocket experiences during its powered phase.

The burnout mass of a rocket refers to the mass of the rocket at the moment when its propellant is completely consumed, and it marks the end of the powered phase of the rocket’s flight. The calculation involves considering the initial mass of the rocket (including the mass of the propellant) and subtracting the mass

A scramjet (supersonic combustion ramjet) engine is an air-breathing engine designed to operate at very high speeds, typically in the hypersonic regime. The nozzle of a scramjet engine plays a crucial role in accelerating the high-speed air and facilitating efficient combustion. Let’s delve into the definition, explanation, and calculation of the nozzle mass flow rate

The mass flow rate through a ramjet engine nozzle is a critical parameter that influences the engine’s performance. A ramjet engine is an air-breathing engine that operates at high speeds, relying on the forward motion of the vehicle to compress incoming air and mix it with fuel for combustion. The velocity (V) of the incoming