Sounding Rocket Flight Analysis
Analytical solution: no drag, gravity loss, vertical ascent, pressure thrust variation, constant g
Innovatia Laboratories
Units conversions
Constants
Earth mean radius =
Mission Parameters
Specific Impulse =
Mass ratio = m0/mb =
Thrust ratio = F/W0 =
Rocket final mass (at burnout) =
Initial speed =
Iterative Design with no drag, single stage, vertical ascent
Effective exhaust speed =
Rocket initial mass =
Rocket initial weight =
Rocket final weight =
Propellant initial mass =
Propellant initial weight =
Total thrust =
Initial acceleration =
Nozzle exit pressure =
Nozzle exit area =
Altitude =
Ambient pressure =
Pressure thrust =
Reaction thrust (in vacuum) =
Propellant burn time =
Propellant burn rate =
Propellant weight burn rate =
Exhaust speed =
Burnout speed =
Burnout speed =
Burnout (max) acceleration =
Burnout height =
work done by gravity = kinetic energy at burnout
->
Coasting distance =
Apogee = total altitude =
