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![]() "Thomas Heger" wrote in message ... Am 17.10.2011 07:01, schrieb Scout: .. For Earth orbit you need much faster flight than you would need to stay in orbit around the moon, but nevertheless it is quite fast. On Earth it took a Saturn V rocket, to lift the craft into orbit. On the Moon it would take less fuel, but way more, than the few gallons, they had in the lander. Ok, let's see your math. I mean if you know they needed more, then clearly you have calculated all this out and know exactly how much they would need and whether they could have that much on the lander. So let's see your work. ---- Insert mathematical proof here. Here I will even aid you with the specifications for the mass, amount of fuel, type of fuel, specific impulse, thrust provided, available delta-V, and so on. http://en.wikipedia.org/wiki/Apollo_...Specifications Well, I'm a little too lazy, but a rough calculation is possible: There is the Tsiolkovsky rocket equation velocity_final=v_exhaust* ln(mass_start/mass_finish) V_end= 2200 m/s * ln (4547 kg/(4547-2353) kg) that is : v_end approx. 1603 m/s this is an estimated calculation without gravity. the final velocity is reduced by delta v = g_moon * (time of engine running) Don't know that number (time_ engine) Maybe 100 seconds (???) makes: delta v = 1.6 m/s²*100 s=160 m/s What gives a rough estimate for the final velocity of the landers ascending stage of v_end = 1440 m/s. Now the orbital velocity had to be compared. But I don't have the data and actually I'm too lazy to find them out. But usual orbits should be a little less than escape velocity, what is v_orbit_escape = 2380 m/s. V_end is a rough estimate ('thumb times pi'). For better calculations someone with more experience in rocket science is needed. I cannot even tell you, if the ascent stage is fast enough or not. But my intuition tells me, it is not. IOW, you don't know what the hell you're talking about, and you're too lazy to do the work needed to find out if what you think actually has merit or is simply bat **** crazy. |
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