CL_man_consumption — Mass consumed, delta V, isp or initial mass
[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])
type_output defines the parameter to be computed, it can be among the following:
'dm' : mass consumed
'dv' : delta V
'isp' : propellant specific impulse.
'm' : initial mass
Input arguments are always in the same order: dm, dv, m, isp
string to define parameter to be computed. It can be 'dm,'dv','m' or 'isp'. (1x1)
first input: dm, dv, m or isp [kg m/s kg or s] (1xN)
second input: dv, m or isp [m/s kg or s] (1xN)
third input: m or isp [kg or s] (1xN)
(optional) standard value of gravity acceleration. [m/s^2] (default value is %CL_g0) (1x1)
depending on type_ouput : dm, dv, m or isp [kg m/s kg or s] (1xN)
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
// Compute mass consumed isp = 220; // seconds dv = 1; // m/s m = 180; // kg dm = CL_man_consumption('dm',dv,m,isp); // mass consumed in kg // Compute delta V isp = 220; // seconds dm = 1; // kg m = 180; // kg dv = CL_man_consumption('dv',dm,m,isp); // delta V in m/s // Compute initial mass isp = 220; // seconds dv = 1; // m/s dm = 1.8; // kg m = CL_man_consumption('m',dm,dv,isp); // initial mass in kg // Compute ISP dm = 1; // kg dv = 1; // m/s m = 180; // kg isp = CL_man_consumption('isp',dm,dv,m); // isp in sec