CL_man_thrustDuration

Description

• 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

Parameters

type_output:

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

par1:

First input parameter: dt, dm, F or isp [s kg N or s] (PxN)

par2:

Second input parameter: dm, F or isp [kg N or s] (PxN)

par3:

Third input parameter: F or isp [N or s] (PxN)

g0:

(optional) value of gravity acceleration. [m/s^2] (default value is %CL_g0) (1x1)

output:

Value of computed parameter: dt, dm, F or isp [s kg N or s] (PxN)

Authors

• CNES - DCT/SB

Bibliography

• 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

See also

• CL_man_consumption

Examples

// mass consumed in kg isp = 220; // seconds dv = 1; // m/s m = 180; // kg dm = CL_man_consumption('dm',dv,m,isp); // thrust duration in seconds F = 1 ; // N [dt] = CL_man_thrustDuration('dt',dm,F,isp)