Thrust duration as function of mass consumed
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]])
The thrust duration can be computed as a function of mass consumed, thrust and propellant specific impulse by the following equation:
Given 3 of the 4 variables that appear in the equation (thrust duration, mass consumed, thrust value and Isp), the function computes the 4th one.
The output argument 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.
Notes:
- Input arguments are always in the same order: dt, dm, F, isp
- The flow rate (mass consumed per unit of time) can be computed by : flow = dm./dt
String defining the parameter to be computed. It can be 'dt,'dm','F' or 'isp'. (1x1)
First input parameter: dt, dm, F or isp [s kg N or s] (PxN)
Second input parameter: dm, F or isp [kg N or s] (PxN)
Third input parameter: F or isp [N or s] (PxN)
(optional) value of gravity acceleration. [m/s^2] (default value is %CL_g0) (1x1)
Value of computed parameter: dt, dm, F or isp [s kg N or s] (PxN)
CNES - DCT/SB
1) Orbital Mechanics for Engineering Students, H D Curtis, Equations 11.10, 11.12, 11.22, 11.30
2) Mecanique spatiale, CNES - Cepadues 1995, Tome I, section 4.8.6