STEP 0: Pre-Calculation Summary
Formula Used
λ = md/(mp+ms)
This formula uses 4 Variables
Variables Used
Payload Mass Fraction - Payload Mass Fraction quantifies the portion of a rocket's total mass that is attributed to the payload.
Payload Mass - (Measured in Kilogram) - Payload Mass is the mass of the payload that the rocket carries, such as satellites, instruments, or other cargo.
Propellant Mass - (Measured in Kilogram) - Propellant Mass refers to the total mass of propellant used in a propulsion system.
Structural Mass - (Measured in Kilogram) - Structural Mass is the mass of the rocket's structure, including tanks, engines, guidance systems, and other hardware.
STEP 1: Convert Input(s) to Base Unit
Payload Mass: 34 Kilogram --> 34 Kilogram No Conversion Required
Propellant Mass: 13 Kilogram --> 13 Kilogram No Conversion Required
Structural Mass: 44 Kilogram --> 44 Kilogram No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
λ = md/(mp+ms) --> 34/(13+44)
Evaluating ... ...
λ = 0.596491228070175
STEP 3: Convert Result to Output's Unit
0.596491228070175 --> No Conversion Required
0.596491228070175 0.596491 <-- Payload Mass Fraction
(Calculation completed in 00.004 seconds)
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Created by LOKESH
Sri Ramakrishna Engineering College (SREC), COIMBATORE
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Indian Institute of Technology, Kharagpur (IIT KGP), West Bengal
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< 9 Theory Of Rockets Calculators

Rocket Exhaust Gas Velocity
Jet Velocity = sqrt(((2*Specific Heat Ratio)/(Specific Heat Ratio-1))*[R]*Temperature at Chamber*(1-(Nozzle Exit Pressure/Pressure at Chamber)^((Specific Heat Ratio-1)/Specific Heat Ratio)))
Total Velocity Required to Place Satellite in Orbit
Total Velocity of Rocket = sqrt(([G.]*Mass Of Earth*(Radius of Earth+2*Height of Satellite))/(Radius of Earth*(Radius of Earth+Height of Satellite)))
Effective Exhaust Velocity of Rocket
Effective Exhaust Velocity = Jet Velocity+(Nozzle Exit Pressure-Atmospheric Pressure)*Exit Area/Propellant Mass Flow Rate
Throat Velocity of Nozzle
Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber)
Velocity Increment of Rocket
Velocity Increment of Rocket = Jet Velocity of Rocket*ln(Initial Mass of Rocket/Final Mass of Rocket)
Structural Mass Fraction
Structural Mass Fraction = Structural Mass/(Propellant Mass+Structural Mass)
Propellent Mass Fraction
Propellant Mass Fraction = Propellant Mass/Initial Mass
Mass Ratio of Rocket
Mass Ratio = Final Mass/Initial Mass

λ = md/(mp+ms)

The payload mass refers to the mass of the cargo, instruments, or other useful components that a rocket carries and delivers to its intended destination. In the context of rocket engineering, the payload mass represents the primary objective of the rocket mission and is the reason for launching the rocket into space or to a specific target.

How to Calculate Payload Mass Fraction?

Payload Mass Fraction calculator uses Payload Mass Fraction = Payload Mass/(Propellant Mass+Structural Mass) to calculate the Payload Mass Fraction, Payload Mass Fraction is a parameter used in rocket engineering to quantify the proportion of the rocket's total mass attributed to its payload, it is defined as the ratio of the payload mass to the total mass of the rocket the payload ratio is an essential metric in rocket design and optimization, higher values indicate a more efficient use of the rocket's mass for carrying payload, which is desirable in most cases. Payload Mass Fraction is denoted by λ symbol.

How to calculate Payload Mass Fraction using this online calculator? To use this online calculator for Payload Mass Fraction, enter Payload Mass (md), Propellant Mass (mp) & Structural Mass (ms) and hit the calculate button. Here is how the Payload Mass Fraction calculation can be explained with given input values -> 0.596491 = 34/(13+44).