CL_man_consumption

Description

• 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.

Parameters

type_output:

String defining the parameter to be computed. It can be 'dm,'dv','m' or 'isp'. (1x1)

par1:

First input parameter: dm, dv, m or isp [kg m/s kg or s] (PxN)

par2:

Second input parameter: dv, m or isp [m/s kg or s] (PxN)

par3:

Third input parameter: m or isp [kg or s] (PxN)

g0:

(optional) Value of gravity acceleration. [m/s^2] (default value is CelestLab predefined data "g0") (1x1)

output:

Value of computed parameter: dm, dv, m or isp [kg m/s kg or s] (PxN)

Authors

• CNES - DCT/SB

Bibliography

• 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

See also

• CL_man_thrustDuration

Examples

// 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