CL_man_thrustDuration — Thrust duration, mass consumed, thrust value or propellant specific impulse
[output]=CL_man_thrustDuration(type_output,par1,par2,par3,[g0]) [dt]=CL_man_thrustDuration('dt',dm,F,isp,[g0]) [dm]=CL_man_thrustDuration('dm',dt,F,isp,[g0]) [F]=CL_man_thrustDuration('F',dt,dm,isp,[g0]) [isp]=CL_man_thrustDuration('isp',dt,dm,F,[g0])
type_output defines the parameter to be computed, it can be among the following:
'dt' : thrust duration.
'dm' : mass consumed
'F' : thrust value.
'isp' : propellant specific impulse.
Input arguments are always in the same order: dt, dm, F, isp
Note : the flow rate (mass consumed per unit of time) can be computed as : flow = dm./dt
string to define parameter to be computed. It can be 'dt,'dm','F' or 'isp'. (1x1)
first input: dt, dm, F or isp [s kg N or s] (1xN)
second input: dm, F or isp [kg N or s] (1xN)
third input: F or isp [N or s] (1xN)
(optional) standard value of gravity acceleration. [m/s^2] (default value is %CL_g0) (1x1)
depending on type_ouput : dt, dm, F or isp [s kg N or s] (1xN)