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*Subject*: Re: [amsat-bb] satellite propulsion thrust equations*From*: Achim Vollhardt <avollhar@xxxxxxxxxxxxxxx>*Date*: Wed, 12 Oct 2005 14:42:32 +0200*User-Agent*: Mozilla Thunderbird 1.0.6 (Windows/20050716)

Hi David! I read your idea and found it: 1. an interesting idea 2. very well written 3. a challenge (the propulsion question). So here we are: go to http://gulp.physik.unizh.ch/meosat_propulsion.xls and download the excel sheet. I started from the following boundary conditions: starting orbit circular (no GTO.. this complicates things).. something a russian launcher can deliver (if the staging works well :( ) Target orbit circular.. transfer orbit Hohmann type, so you have two burns: one to change the low orbit into an elliptical with apogee at the height of the high orbit and a second burn to circularize. This is the theoretically most efficient transfer. The input fields are in blue (start height, target height, Isp, dry mass, fueled mass) and the results (required delta_V, achievable delta_v) are in red. I filled in some values from David's website including the Isp for the bi-propellant enging and a 50/50 partitioning of fuel and dry mass for a 20 kg launch mass. It is just possible.. Please play around and report errors.. I do not take responsibility for any wrong mission planning :) 73s Achim, DH2VA/HB9DUN PS: to David, I certainly enjoyed the Surrey colloquium.. see you next year! ---- Sent via amsat-bb@amsat.org. Opinions expressed are those of the author. Not an AMSAT member? Join now to support the amateur satellite program! To unsubscribe, send "unsubscribe amsat-bb" to Majordomo@amsat.org

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