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] (1xN)
Second input parameter: dv, m or isp [m/s kg or s] (1xN)
Third input parameter: m or isp [kg or s] (1xN)
(optional) Value of gravity acceleration. [m/s^2] (default value is %CL_g0) (1x1)
Value of computed parameter: dm, dv, m or isp [kg m/s kg or s] (1xN)
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