Propellant mass fraction

Propellant mass fraction

In aerospace engineering, the propellant mass fraction is a measure of a vehicle's performance, determined as the portion of the vehicle's mass which does not reach the destination. In a spacecraft, this is an orbit, while for aircraft it is their landing location. A higher mass fraction represents less weight in a design. Another related measure is the payload fraction, which is the fraction of initial weight that is payload.


In rockets for a given target orbit, a rocket's mass fraction is the portion of the rocket's pre-launch mass (fully fueled) that does not reach orbit. In the cases of a single stage to orbit (SSTO) vehicle the mass fraction is simply the fuel mass divided by the mass of the full spaceship, but with a rocket employing staging, which are the only designs to have reached orbit, the mass fraction is higher because parts of the rocket itself are dropped off en route. Mass fractions are typically around 0.8 to 0.9.

In aircraft, mass fraction is related to range, an aircraft with a higher mass fraction can go farther. Mass fractions are typically around 0.5.

When applied to a rocket as a whole, a low mass fraction is desirable, since it indicates a greater capability for the rocket to deliver payload to orbit for a given amount of fuel. Conversely, when applied to a single stage, where the mass fraction calculation doesn't include the payload, a higher mass fraction corresponds to a more efficient design, since there is less non-propellant mass. Without the benefit of staging, SSTO designs are typically designed for mass fractions around 0.9. Staging increases the mass fraction, which is one of the reasons SSTO's appear difficult to build.

For example, the complete Space Shuttle system has:
*weight at liftoff: 4,500,000 lb (2,040,000 kg)
*weight at end of mission: 230,000 lb (104,000 kg), and
*maximum cargo to orbit: 63,500 lb (28,800 kg)

Given these numbers, the mass fraction is displaystyle 1-(293,500/4,500,000) = 0.935 or perhaps a little less because of the fuel brought to orbit for use when returning: this may not have been counted as cargo, in which case the figure 293,500 should be a little higher.

The mass fraction plays an important role in the rocket equation:

:displaystyle Delta v = -v_e ln (m_f / m_0)

Where displaystyle m_f/m_0 is the ratio of final mass to initial mass (i.e., one minus the mass fraction), displaystyle Delta v is the change in the vehicle's velocity as a result of the fuel burn and displaystyle v_e is the effective exhaust velocity (see below).

The term effective exhaust velocity is defined as:

:displaystyle v_e = g_n I_{sp}

where "I"sp is the fuel's specific impulse in seconds and "gn" is the "standard acceleration of gravity" (note that this is not the local acceleration of gravity).

To make a powered landing from orbit on a celestial body without an atmosphere requires the same mass reduction as reaching orbit from its surface, if the speed at which the surface is reached is zero.



ee also

*Fuel fraction
*Mass ratio

Wikimedia Foundation. 2010.

Игры ⚽ Поможем написать курсовую

Look at other dictionaries:

  • Mass fraction — The mass fraction may refer to: Propellant mass fraction, in aerospace engineering, the amount of mass left behind such as the stages of rockets Payload fraction, also in aerospace engineering, characterizes the efficiency of the mass to be… …   Wikipedia

  • Mass ratio — Astrodynamics Orbital mechanics Equations …   Wikipedia

  • Mass driver — For fictional mass drivers, see List of electromagnetic projectile devices in fiction. Artist s conception of a mass driver for lunar launch A mass driver or electromagnetic catapult is a proposed method of non rocket spacelaunch which would use… …   Wikipedia

  • Rocket propellant — is mass that is stored, usually in some form of propellant tank, prior to being used as the propulsive mass that is ejected from a rocket engine in the form of a fluid jet to produce thrust.Chemical rocket propellants are most commonly used,… …   Wikipedia

  • Ammonium perchlorate composite propellant — (APCP) is a modern solid rocket propellant used in both manned and unmanned rocket vehicles. It differs from many traditional solid rocket propellants such as black powder or Zinc Sulfur, not only in chemical composition and overall performance,… …   Wikipedia

  • Fuel fraction — An aircraft s fuel fraction, fuel weight fraction, [cite book | last = Brandt | first = Steven | title = Introduction to Aeronautics: a Design Perspective | publisher = AIAA (American Institute of Aeronautics Ast | pages = p. 359 | year = 2004 |… …   Wikipedia

  • India and weapons of mass destruction — India Nuclear program start date 1967 First nuclear weapon test 18 May 1974 (Smiling Buddha) …   Wikipedia

  • Iran and weapons of mass destruction — This article is about Iran and weapons of mass destruction. For Iran s nuclear power program, see Nuclear program of Iran. Weapons of mass destruction …   Wikipedia

  • Delta-v — For other uses, see Delta v (disambiguation). In astrodynamics a Δv or delta v (literally change in velocity ) is a scalar which takes units of speed. It is a measure of the amount of effort that is needed to change from one trajectory to another …   Wikipedia

  • Falcon 1 — Infobox rocket imsize = 220 caption = Falcon 1 rocket. name = Falcon 1 function = Orbital launch vehicle manufacturer = SpaceX country origin = United States height = 21.3 m alt height = 70 ft diameter = 1.7 m alt diameter = 5.5 ft mass = 38,555… …   Wikipedia

Share the article and excerpts

Direct link
Do a right-click on the link above
and select “Copy Link”