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_dataGet("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