Mass estimation

A liquid launcher stage typically consists of a main propulsion system, a reaction control system (sometimes integrated to some extent with the main propulsion system), (supporting) structure system, forward skirt, aft skirt, aerodynamic control and/or stabilizer surfaces, a separation system and a destruct system. Some upper stages are also equipped with an avionics system, like the AVUM on ESA's Vega launcher.

In the tables below, typical mass data are given that can be used for preliminary system sizing of liquid chemical rocket propelled launcher stages. The mass data given include stage dry (inert) mass, propellant mass and total mass, where total mass is the sum of stage dry mass and propellant mass. 

Table: Mass properties typical cryogenic launcher stages

^{1) ton = metric ton (1000 kg)      2) Dry mass fraction is dry mass/total mass}     
Dry mass versus propellant mass for cryogenic launcher stages is plotted in the next figure.

Regression analysis performed on the above data assuming a logarithmic relationship exists between propellant mass (denoted by x) and propellant- mass-to-total-stage-mass or propellant mass fraction (denoted by y) has been performed, see also figure. No standard error of estimate (SEE) has been determined for this relationship.

Table: Mass properties typical semi-cryogenic propellant launcher stages

^{3) Dry mass-to- propellante mass fraction is dry mass / propellant mass}

Table: Mass properties typical storable propellant launcher stages

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Mail to: b.t.c.zandbergen@lr.tudelft.nl

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^{Updated February 2005: Figure mass data cryogenic launcher stages added.
Previous update: July 2004
Created: May 2003}