Mass consumed as function of delta-V
output = CL_man_consumption(type_output, par1, par2, par3 [[, g0]]) dm = CL_man_consumption('dm', dv, m, isp [[, g0]]) dv = CL_man_consumption('dv', dm, m, isp [[, g0]]) m = CL_man_consumption('m', dm, dv,isp [[, g0]]) isp = CL_man_consumption('isp', dm, dv, m [[, g0]])
The mass consumed by a maneuver can be computed by the following equation:
Given 3 of the 4 variables that appear in the equation (mass consumed, norm of velocity increment, Isp or initial mass), the function computes the 4th one.
The output argument type_output defines the parameter to be computed. It can be one of the following:
- 'dm': mass consumed
- 'dv': norm of delta-V
- 'isp': propellant specific impulse.
- 'm': initial mass
Note:
-The input arguments are always in the same order: dm, dv, m, isp.
String defining the parameter to be computed. It can be 'dm,'dv','m' or 'isp'. (1x1)
First input parameter: dm, dv, m or isp [kg m/s kg or s] (PxN)
Second input parameter: dv, m or isp [m/s kg or s] (PxN)
Third input parameter: m or isp [kg or s] (PxN)
(optional) Value of gravity acceleration. [m/s^2] (default value is CelestLab predefined data "g0") (1x1)
Value of computed parameter: dm, dv, m or isp [kg m/s kg or s] (PxN)
CNES - DCT/SB
1) Orbital Mechanics for Engineering Students, H D Curtis, Chapter 6, equation 6.1
2) Mecanique spatiale, CNES - Cepadues 1995, Tome I, section 4.8.6