Rocket
Fixed design
Reusability
1st engine
kgfQty
1st stage Fuel & Cycle   
2nd engine
kgfQty
2nd stage Fuel & Cycle    
3rd stage Fuel & Cycle    
Stages
Thrust-to-weight ratio
1st  2nd   
Lift-off mass
kg
Rocket mass (Lift off excluding Payload and Fairing)
kg
Max Rocket Body Diameter
m
Fairing mass
kg
Fairing jettison velocity
m/s
Fairing jettison delta-v
m/s
Jettisoned battery mass
kg
Assumed payload mass
kg
2nd stage to Rocket mass ratio
%
Transfer Orbit stage to Rocket mass ratio
%
Decrease Payload <-- --> Increase Payload Limit to reasonable
Set all to Min <-- --> Set all to Max Set averages
1st stage Dry to Wet mass ratio
%
2nd stage Dry to Wet mass ratio
%
Transfer Orbit stage Dry to Wet mass ratio
%
Unused propellant of 1st stage
%
Unused propellant of 2nd stage
%
Unused propellant of Transfer Orbit stage
%
1st stage Isp sea level or at the start altitude
s
1st stage Isp vacuum
s
2nd stage Isp
s
Transfer Orbit stage Isp
s
Specific Impulse variation
%
Spaceport
Air Launch
Launch point Altitude
km
Additional velocity (Air Launch)
m/s
Spaceport Latitude
deg
Auxiliary angle
deg
Launch Azimuth
deg
Earth rotation velocity
m/s
Launch point altitude orb. velocity (imaginary)
m/s
Absolute orbital velocity
m/s
Relative orbital velocity
m/s
Orbital velocity gain due to the Earth rotation
m/s
Delta-v for circular orbit (ideal)
m/s
Delta-v for LEO (losses calc.)
m/s
Orbit
Orbit Perigee
km
Reference Orbit
km 
Orbit Apogee (0 means a circular orbit)
km
Orbit Inclination
deg
Perigee velocity
m/s
Apogee velocity
m/s
Orbital Period
min
Delta-v for change orbit inclination to 0
m/s
Orbital (injection) velocity
m/s
Delta-v for target orbit (ideal)
m/s
Extra velocity for interplanetary transfer
m/s
Losses
Gravity Losses at specific altitude
m/s
Gravity Losses
m/s
Aerodynamic Losses
m/s
Summary Losses
m/s
Assumed Losses
% 
Required delta-v with Losses
m/s
Output
1st stage average trajectory Isp
s 
1st stage delta-v
m/s
1st stage final mass
kg 
1st stage propellant mass
kg
1st stage dry mass
kg
1st stage total thrust
kgf
1st stage engines run time
s 
1st stage Maximum Acceleration
g 
2nd stage delta-v
m/s
2nd stage total (start) mass
kg 
2nd stage total mass before fairing jettison
kg 
2nd stage total mass before battery jettison
kg 
2nd stage delta-v before batt. jettison
m/s
2nd stage final mass
kg 
2nd stage propellant mass
kg 
2nd stage dry mass
kg 
2nd stage total thrust
kgf 
2nd stage engine run time
s 
2nd stage Maximum Acceleration
g 
Transfer Orbit stage delta-v (required)
m/s
Transfer Orbit stage total (start) mass
kg 
Transfer Orbit stage final mass
kg 
Transfer Orbit stage propellant mass
kg 
Transfer Orbit stage dry mass
kg
Calculation Error
m/s