There’s little I dislike more than a person who spreads lies and ignorance, which places Bart Sibrel near the top of my hate list. His latest intro shows he is either a buffoon, or a conman, or both. The man is an idiot and he won’t be happy until he pulls everyone else down with him.
First off, like a typical layman he seems to think that everything in rocketry has to do with thrust. While thrust is an important factor in rocket design, it ultimately has little to do with determining how fast, hence how far, a rocket will go. ESA’s SMART-1 spacecraft made it all the way to the Moon using an engine with a thrust of only 70 milliNewtons. Yet, Sibrel starts his intro by giving the formula for impulse thrust as if it alone is sufficient to determine whether the Saturn V could send Apollo to the Moon. Knowing thrust is not enough, and if Bart Sibrel wasn’t such a dolt he could easily perform the calculations to show the Saturn V was more than up to the task.
Traveling through space is nothing more than transferring from one orbit to another. A spacecraft’s orbit is determined by its state vector, i.e. its position and velocity. To change the orbit we change the state vector by adding or subtracting velocity. The following Web page gives the lowdown on orbital maneuvers:
www.braeunig.us/space/orbmech.htm#maneuverThe job of the Saturn V was to launch the Apollo spacecraft and then inject into a transfer orbit between Earth and the Moon. To do this, the Saturn V had to provide only enough velocity to get into low Earth orbit and then to change from a circular Earth parking orbit to an elliptical orbit with an apogee beyond the orbit of the Moon. This was done within the first few hours of the mission, after which the job of the Saturn V was finished.
Velocity in low Earth orbit is about 7.8 km/s, but a launch vehicle must also provide enough velocity to overcome gravity and drag during ascent to orbit. This generally requires another 1.5 km/s. However, due to the Earth’s rotation a spacecraft launched from Florida is already moving about 0.4 km/s. Therefore, the total velocity required to reach orbit is about 7.8+1.5-0.4 = 8.9 km/s.
Escape velocity from low Earth orbit is 11 km/s, thus the change in velocity needed to go from a circular orbit to an escape trajectory is 11-7.8 = 3.2 km/s. However, the Apollo spacecraft needed to get to the Moon only, not escape Earth’s gravity all together, thus a change in velocity of about 3.1 km/s was used. This means the total velocity the Saturn V had to provide was about, 8.9+3.1 = 12 km/s.
From these Web pages,
www.braeunig.us/space/specs/saturn.htmwww.braeunig.us/space/specs/apollo.htmwww.braeunig.us/space/specs/lm.htmwe get the following data:
Escape tower: 4,173 kg
Command module: 5,806 kg
Service module: 24,523 kg
Lunar module: 16,440 kg
Spacecraft-LM adapter: 1,800kg
Instrument unit: 2,030 kg
Stage 3, propellant: 106,940 kg
Stage 3, dry: 11,380 kg
Stage 3, other: 755 kg
Stage 2-3 interstage: 3,650 kg
Stage 2, propellant: 451,650 kg
Stage 2, dry: 36,395 kg
Stage 2, other: 505 kg
Stage 1-2 interstage: 5,195 kg
Stage 1, propellant: 2,149,500 kg
Stage 1, dry: 130,570 kg
Stage 1, other: 2,450 kg
TOTAL MASS: 2,953,762 kg
Stage 3 specific impulse: 427 s vac, at 5:1 mixture ratio
Stage 2 specific impulse: 424 s vac, at 5.5:1 mixture ratio
Stage 1 specific impulse: 265 s SL
The following Web pages show the derivation of Tsiolkovsky's rocket equation and the correct method for calculating the delta-V of a multi-stage rocket:
www.braeunig.us/space/propuls.htm#impulsewww.braeunig.us/space/propuls.htm#stageApplying this method to the Saturn V we can calculate its delta-V. After stage 1 burnout we jettison stage 1, 1-2 interstage, and escape tower. After stage 2 burnout we jettison stage 2 and 2-3 interstage. We therefore have,
dV1 = 265*9.80665*LN(2,953,762/(2,953,762-2,149,500))
dV1 = 3,381 m/s
mo2 = 2,953,762-2,149,500-130,570-2,450-5195-4,173 = 661,874 kg
dV2 = 424*9.80665*LN(661,874/(661,874-451,650))
dV2 = 4,769 m/s
mo3 = 661,874-451,650-36,395-505-3,650 = 169,674 kg
dV3 = 427*9.80665*LN(169,674/(169,674-106,940))
dV3 = 4,166 m/s
Total dV = 3,381+4,769+4,166 = 12,316 m/s
12,316 m/s > 12,000 m/s, so where’s the problem?