Full Stack Mass Properties Version 1.0
Name Weight X Station Y of CG Z of CG Ixx Iyy Izz
(lb) (ft) (ft) (ft) (sl ft2) (sl ft2) (sl ft2)
LTV Dry Total 7,000.00 26.59 0.00 -0.60 3,612.55 44,858.95 44,808.91
100% LTV Propellant 94,000.00 28.20 0.00 0.00 61,719.00 145,456.00 145,456.00
Total LTV CM 101,000.00 28.09 0.00 -0.04
Hab/Desc Dry Total 17,100.00 -15.46 0.00 -0.94 10,828.96 43,771.52 43,748.07
100% Desc Propellant 12,000.00 -33.50 0.00 0.00 3,216.50 1,292.60 1,292.60
Total Hab/Desc 29,100.00 -22.90 0.00 -0.55
Ascent Dry Total 1,400.00 -35.21 -12.00 0.00
100% Ascent Propellant 1,500.00 -35.00 -12.00 0.00
Total Ascent 2,900.00 -35.10 -12.00 0.00
Total Stack 133,000.00 15.55 -0.26 -0.15 92,538.92 2,369,601.39 2,381,775.80
This is the initial release of the Full Stack Mass Properties sheet.
It has been put together to serve primarily as a seed for my spreadsheet.
As such, all values contained in this sheet are to be treated as
extremely preliminary. Unless otherwise noted, consider all
quantities to have a very high degree of uncertainty associated with
them. Please see the individual vehicle (LTV, Habitat/Desc Stage, or
Ascent Stage) mass properties sheets for
a breakdown of each vehicle's mass properties. Please see the Propellant Mass
Calculation sheet for a breakdown of the propellant masses. Please
see the LTV Mass Properties Coordinate System
pages for a description of the coordinate system in which the Centers
of Gravity and Moments of Inertia are represented.
- The total mass properties shown at the bottom of the table are for
the full Artemis stack in Earth orbit, prior to any burns.
- The Propellant masses have been rounded from the values found in
the Fuel Mass Calculation sheet. Propellant moments of inertia have been
computed using these rounded values.
- The Habitat and Descent Stage Dry Total contains 600 lbs for
astronaut space suit backpacks.
- The Ascent Stage Dry Total contains the 750 lbs for the astronauts
and their space suits. EVA backpacks are left on the lunar surface. It
does not contain the 200 lbs of lunar samples to be returned.
Planned enhancements to this and other pages include:
- Breakdowns of other vehicle combinations (e.g., Desc/Hab/Asc and
- Mass properties for propellant amounts less than 100%
- Breakdowns by propellant type (e.g., LH2 and LOX, or MMH and N2O4)
Copyright © 2007 Artemis Society International, for the
contributors. All rights reserved.
This web site contains many trade names and copyrighted articles and images.
John M. Kruep.
ASI Web Team
Submit update to this page.
Maintained with WebSite Director.
Updated Sun, Aug 1, 1999.