Structural Mass Fraction Calculator

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Rocket Propulsion

Components of Gas Turbine

Jet Propulsion

Thermodynamics and Governing Equations

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✖Structural Mass is the mass of the rocket's structure, including tanks, engines, guidance systems, and other hardware.ⓘ Structural Mass [m_s]			+10% -10%
✖Propellant Mass refers to the total mass of propellant used in a propulsion system.ⓘ Propellant Mass [m_p]			+10% -10%

✖Structural Mass Fraction quantify the proportion of the rocket's total mass attributed to its structure.ⓘ Structural Mass Fraction [σ]

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Formula

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Structural Mass Fraction

Formula

`"σ" = "m"_{"s"}/("m"_{"p"}+"m"_{"s"})`

Example

`"0.77193"="44kg"/("13kg"+"44kg")`

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Structural Mass Fraction Solution

STEP 0: Pre-Calculation Summary

Formula Used

Structural Mass Fraction = Structural Mass/(Propellant Mass+Structural Mass)
σ = m_s/(m_p+m_s)
This formula uses 3 Variables

Variables Used

Structural Mass Fraction - Structural Mass Fraction quantify the proportion of the rocket's total mass attributed to its structure.
Structural Mass - (Measured in Kilogram) - Structural Mass is the mass of the rocket's structure, including tanks, engines, guidance systems, and other hardware.
Propellant Mass - (Measured in Kilogram) - Propellant Mass refers to the total mass of propellant used in a propulsion system.

STEP 1: Convert Input(s) to Base Unit

Structural Mass: 44 Kilogram --> 44 Kilogram No Conversion Required
Propellant Mass: 13 Kilogram --> 13 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

σ = m_s/(m_p+m_s) --> 44/(13+44)

Evaluating ... ...

σ = 0.771929824561403

STEP 3: Convert Result to Output's Unit

0.771929824561403 --> No Conversion Required

FINAL ANSWER

0.771929824561403 ≈ 0.77193 <-- Structural 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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< 9 Theory Of Rockets Calculators

Rocket Exhaust Gas Velocity

Go 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

Go 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

Go Effective Exhaust Velocity = Jet Velocity+(Nozzle Exit Pressure-Atmospheric Pressure)*Exit Area/Propellant Mass Flow Rate

Throat Velocity of Nozzle

Go Throat Velocity = sqrt((2*Specific Heat Ratio)/(Specific Heat Ratio+1)*[R]*Temperature at Chamber)

Velocity Increment of Rocket

Go Velocity Increment of Rocket = Jet Velocity of Rocket*ln(Initial Mass of Rocket/Final Mass of Rocket)

Structural Mass Fraction

Go Structural Mass Fraction = Structural Mass/(Propellant Mass+Structural Mass)

Payload Mass Fraction

Go Payload Mass Fraction = Payload Mass/(Propellant Mass+Structural Mass)

Propellent Mass Fraction

Go Propellant Mass Fraction = Propellant Mass/Initial Mass

Mass Ratio of Rocket

Go Mass Ratio = Final Mass/Initial Mass

Structural Mass Fraction Formula

Structural Mass Fraction = Structural Mass/(Propellant Mass+Structural Mass)
σ = m_s/(m_p+m_s)

What is Structural Mass ?

The structural mass is a critical aspect of rocket design, as it directly impacts the overall mass of the rocket and its performance characteristics. Engineers strive to minimize the structural mass while ensuring that the rocket remains structurally sound and capable of withstanding the forces and loads experienced during launch and flight. Achieving an optimal balance between structural mass, propulsion efficiency, and payload capacity is essential for the success of a rocket mission.

How to Calculate Structural Mass Fraction?

Structural Mass Fraction calculator uses Structural Mass Fraction = Structural Mass/(Propellant Mass+Structural Mass) to calculate the Structural Mass Fraction, Structural Mass Fraction is a parameter used in rocket engineering to quantify the proportion of a rocket's total mass attributed to its structure relative to the total mass of the structure plus the propellant, it is defined as the ratio of the structural mass to the sum of the structural mass and the propellant mass. Structural Mass Fraction is denoted by σ symbol.

How to calculate Structural Mass Fraction using this online calculator? To use this online calculator for Structural Mass Fraction, enter Structural Mass (m_s) & Propellant Mass (m_p) and hit the calculate button. Here is how the Structural Mass Fraction calculation can be explained with given input values -> 0.77193 = 44/(13+44).

FAQ

What is Structural Mass Fraction?

Structural Mass Fraction is a parameter used in rocket engineering to quantify the proportion of a rocket's total mass attributed to its structure relative to the total mass of the structure plus the propellant, it is defined as the ratio of the structural mass to the sum of the structural mass and the propellant mass and is represented as σ = m_s/(m_p+m_s) or Structural Mass Fraction = Structural Mass/(Propellant Mass+Structural Mass). Structural Mass is the mass of the rocket's structure, including tanks, engines, guidance systems, and other hardware & Propellant Mass refers to the total mass of propellant used in a propulsion system.

How to calculate Structural Mass Fraction?

Structural Mass Fraction is a parameter used in rocket engineering to quantify the proportion of a rocket's total mass attributed to its structure relative to the total mass of the structure plus the propellant, it is defined as the ratio of the structural mass to the sum of the structural mass and the propellant mass is calculated using Structural Mass Fraction = Structural Mass/(Propellant Mass+Structural Mass). To calculate Structural Mass Fraction, you need Structural Mass (m_s) & Propellant Mass (m_p). With our tool, you need to enter the respective value for Structural Mass & Propellant Mass and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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