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Brad Guth's Credentials
You've GOT to be kidding! lol. Is F=ma worn out too? hahaha...
This has GOT to be a joke. Really. A disinformation tactic!? Those who know laugh, those who don't know are confused or they actually believe the bull****. sigh ROCKET EQUATON Figure out how fast a rocket stage will go knowing only the exhaust speed of the rocket and the fraction of propellant. Vf = Ve * LN(1/(1-u)) is still useful, despite your asinine bull**** here. Vf = final velocity of a rocket propelled projectile Ve = exhaust velocity of the gases coming out of the engine LN(..) = natural logarithm (base 'e') u = propellant fractoin (a number between 0 (empty) and 1 (all propellant) Typical numbers; ADVANCED ROCKETS Solar/laser sail - infinity (no propellant) Fusion pulse - 100,000 m/s Ion - 50,000 m/s Orion Nuclear Pulse -20,000 m/s (effective) Nuclear thermal - 8,500 m/s STATE OF ART ROCKETS LOX/LH2 - 4,200 m/s LOX/RP1 - 3,000 m/s Hypergolic - 2,800 m/s SRB - 2,200 m/s H2O2 - 1,800 m/s Nitrogen - 1,500 m/s THRUST CALCULATION F = mdot * Ve F = thrust (Newtons) mdot = mass flow rate Ve = exhaust velocity POWER CALCULATION P = 1/2 * mdot * Ve^2 Power = watts mdot = mass flow rate Ve = exhaust velocity FRACTIONS 1 = p + s + u p = payload s = structure u = propellant Typical values for s range from 0.08 to 0.22 depending on details like thermal protection systems, and so forth. THRUST TO WEIGHT The thrust to weight of a typical chemical rocket is around 70 to 1. That is for each pound or kg of mass you have 70 pounds or kgs of thrust. But nuclear thermal rockets have a thrust to weight of about 20 to 1 at best. And nuclear pulse rockets like Orion are likely to have a 5 to 1 thrust to weight. Ion rockets have 1/10,000 to 1 - they cannot lift off earth. Fusion pulse rockets that have high performance have very high captue of reaction products which means a very large thrust structure, so they are likely not to have high thrust to weight. Since no one has built these systems before there is a disagreement about what they might achieve. Studies with thrust to weight from 2 to 1 down to 1/3 to 1 have been produced. The 2 to 1 can be used on Earth. The 1/3 to 1 cannot, but can be used on the moon and mars. |
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