READING: SSME Mathematical Reference

Model Names refer to Main Engine 1.

Vacuum Thrust (FME1)

where
FME1	= Vacuum Thrust
VEME1	= Exit Volocity
K	= specific heat ratio
R	= universal gas constant = 49,720 ft-lb/slog-R
M	= molecular weight of combustion in chamber
TC	= combustion temperature in chamber = 6,459.69R
PE	= pressure inside combustion chamber = 2,871 psia

Total Mass Flow

HPFTP
Flow Rate

where 
FVLVPOSFTME1	   = Main Fuel Valve position
FUELCONSTFTME1  	   = Fuel Valve Constant (for fuel flow contribution) = 78
OVLVPOSFTME1	   = Fuel Pump Turbo Oxidizer Valve position
OXBALLVLVCNSTFTME1= Oxidizer Valve Constant (for oxidizer flow contribution) = 68

RPM

where
FLOWRATEFTME1	  = HPFTP Flow Rate
FUELPUMPCONSTME1 = Fuel Pump Constant = 232.4383562

HPOTP
Flow Rate

where 
FVLVPOSOTME1              = Fuel Valve position (fuel to HPOTP)
FUELCONSTFTME1         = Fuel Valve Constant (for fuel flow contribution) = 40
OVLVPOSFTME1              = Oxidizer Pump Turbo Oxidizer Valve position
OXBALLVLVCNSTFTME1 = Oxidizer Valve Constant (for oxidizer flow contribution) = 25

RPM

where
OTURBOFLOWME1     =	Liquid Oxygen Flow (demand rate from ET Oxidizer Tank)
OXTURBOCONSTME1 =	Oxidizer Turbo Constant = 0.04173

LPFTP RPM

where
FTURBOFLOWME1 = LPFTP Flow Rate

LPOTP RPM

where
OTURBOFLOWME1 = LPOTP Flow Rate