Stage and Stage Subsystem Scaling

(Updated 5 October 2012)

References:

Preliminary Assessment of Using Gelled and Hybrid Propellant Propulsion for VTOL/SSTO Launch SystemsNASA TM 1998-206306
Design Mass Properties II: Mass Estimating and Forecasting for Aerospace Vehicles based on Historical DataNASA JSC-26098 (November 1994) (6.1 MB PDF)

Aerodynamic Fins (NASA TM-86520) (September 1985)

This report on designing a Heavy Lift Launch Vehicle says that a 675 ft2 fin on the proposed HLLV booster would mass 10,390~ lbs; or about 15.4~ lb/ft2.

Estimating Propellant Tank Structure Mass (NASA JSC-26098)

MTank = 10.41 * (VTank)0.75

Where:

MTank = Tank Mass in Pounds
VTank = Tank Volume in Cubic Feet (ft3)

Notes: The standard units formula is from the following graph from JSC-26098 (LINK), and covers only the propellant tanks and their insulation.

Generic O2/H2 Upper Stage Dry Mass (NASA TM 1998-206306)

DMass = 373.8 + (0.1576 * PMass)

Where:

DMass: Dry Mass of the Stage in pounds
PMass: Propellant Mass of the Stage in pounds

Notes: Design is assumed to be a high pressure, pump fed system.

Generic NTO/MMH Upper Stage Dry Mass (NASA TM 1998-206306)

DMass = 440.0 + (0.1358 * PMass)

Where:

DMass: Dry Mass of the Stage in pounds
PMass: Propellant Mass of the Stage in pounds

Notes: Design is assumed to be a high pressure, pump fed system.