Launcher Calculator

Launcher Calculator
An open source orbital launch vehicle payload calculator by Launcher

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Select Rocket
Apollo lunar program launcher

Result

Payload mass (calculated)	48,294 kg
Payload to Lift-off mass ratio	1.63 %
Payload change	99.4 % (-0.6%)
Aggressivity index	5.7 pts

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	2965494 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	4200.0 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	73.66 deg
Launch Azimuth	72.77 deg
Earth rotation velocity	408.2 m/s
Launch point altitude orb. velocity (imaginary)	7909.7 m/s
Absolute orbital velocity	7788.5 m/s
Relative orbital velocity	7397.6 m/s
Orbital velocity gain due to the Earth rotation	390.8 m/s
Delta-v for circular orbit (ideal)	7640.1 m/s
Delta-v for LEO (losses calc.)	7640.2 m/s

Orbit

Trans-Lunar injection orbit

Orbit Perigee	km
Reference Orbit	200 km
Orbit Apogee (0 means a circular orbit)	km
Orbit Inclination	deg
Perigee velocity	7788.5 m/s
Apogee velocity	7788.5 m/s
Orbital Period	1:28:21 s
Transfer time	3d 6:38:27 s
Delta-v for change orbit inclination to 0	0.0 m/s
Orbital (injection) velocity	11131.0 m/s
Delta-v for target orbit (ideal)	10740.1 m/s
Extra velocity for interplanetary transfer	m/s

Losses

Gravity Losses at specific altitude	784.9 m/s
Gravity Losses	1556.7 m/s
Aerodynamic Losses	44.0 m/s
Summary Losses	1745.7 m/s
Assumed Losses	22.85 %
Required delta-v with Losses	12243.3 m/s

Output

1st stage average trajectory Isp	298.1 s
1st stage delta-v	3612.6 m/s
1st stage final mass	861651.8 kg
1st stage propellant mass	kg
1st stage dry mass	kg
1st stage total thrust	kgf
1st stage total impulse	6.149e+9 N*s
1st stage engines run time	160 s
1st stage Maximum Acceleration	4.0 g
2nd stage delta-v	4565.1 m/s
2nd stage total (start) mass	675488.1 kg
2nd stage total mass before fairing jettison	585903.0 kg
2nd stage total mass before battery jettison	361903.9 kg
2nd stage delta-v before batt. jettison	1932.3 m/s
2nd stage final mass	220514.2 kg
2nd stage propellant mass	kg
2nd stage dry mass	kg
2nd stage total thrust	kgf
2nd stage total impulse	1.845e+9 N*s
2nd stage engine run time	357 s
2nd stage Maximum Acceleration	2.4 g
Transfer Orbit stage delta-v (required)	4065.6 m/s
Transfer Orbit stage total (start) mass	171294.9 kg
Transfer Orbit stage final mass	63984.6 kg
Transfer Orbit stage propellant mass	kg
Transfer Orbit stage dry mass	kg
Transfer Orbit stage total impulse	4.430e+8 N*s
Calculation Error	-0.6 m/s