Propellant estimation with height
Propellant estimation with height
(OP)
Hi ya...Does any one knw of any equation to estimate the amount of propellant burn per height climb for a spcaecraft?..doing some spacecraft review.
Cheers.
Cheers.





RE: Propellant estimation with height
Note this equation does not account for atmospheric drag or varying g.
Peter
RE: Propellant estimation with height
Also how can you relate the amount of propellant burn to the height ascent? any equation that relates the two together like we have for aircraft.( i.e. specific thrust and range)
Cheers.
RE: Propellant estimation with height
The answer to your second question is deltaV. For instance liftoff from Earth to LEO might be a deltaV of ~7-10 km/s (depending on the launch site and final orbit). Earth to GEO would be higher, ~12 km/sec (including transfer orbit and plane change maneuvers).
Peter