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I have a few dynamical questions, that I was hoping to get some "top
line" answers to:- Suppose I want to propel a (hypothetical) 300-kg mass orbiter to rendezvous with the Moon for lunar orbit capture, departing from a circular LEO orbit of 400-km altitude inclined at 20 degrees to Earth equator. Would I be right in thinking the Delta V increment would need acclerate the craft from 7.7 km/s (LEO speed) to 11.3 km/s (Earth escape)... a near 50% increase in velocity to achieve Earth to Moon transfer orbit? What would be the fuel requirements (in terms of additional propellant mass on top of the 300-kg existing orbiter mass) to achieve such a transfer? How long should the burn time be (assuming a simple RP-1 type propellant)? Would my hypothetical LEO orbiter need to pre-adjust its orbital incline from 20 degrees to 28.6 degrees (I assume to be co-planer with the Moon's 23.5 degree ecliptic + 5.1 degrees incline vs Earth equator) prior to firing the LEO departure burn? What would be the transit time (from LEO to lunar orbital capture) and finally, how much retro firing would be required at the Moon end to achieve initial orbit capture... assuming a lunar orbit of reasonable altitde and shape? In this simplified scenario, would I be o.k. to aim for a single impulse Hohmann transfer ellipse (with just one departure burn at LEO and no course corrections!) ensuring that its apogee point will intersect the lunar orbit? Also if the transit time of the orbiter from LEO to Moon is "T" hours, would the major axis of the transfer orbit ellipse need to aim at a point which is (T*0.5) degrees ahead of the Moon in its orbit (assuming the Moon moves roughly 0.5 degrees/hour along its orbit) so that both my orbiter and the Moon meet at the same place at the same time? Sorry for the long post, but I am sure you can appreciate the complications! Sincerely, Abdul Ahad http://uk.geocities.com/aa_spaceagent/ |
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(Abdul Ahad) wrote in message . com...
I have a few dynamical questions, that I was hoping to get some "top line" answers to:- I have a simulator that can be used to figure out answers to trajectory questions in the Earth Moon system. It is a Java applet which you can run from http://spacetethers.com/spacetethers.html -- Vince |
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(Vincent Cate) wrote in message . com...
(Abdul Ahad) wrote in message . com... I have a few dynamical questions, that I was hoping to get some "top line" answers to:- I have a simulator that can be used to figure out answers to trajectory questions in the Earth Moon system. It is a Java applet which you can run from http://spacetethers.com/spacetethers.html -- Vince Hi, Your Java applet doesn't work in my browsers... is there an alternative? cheers AA |
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