Name

CL_man_thrustDuration — Thrust duration, mass consumed, thrust value or propellant specific impulse

Calling Sequence

   [output]=CL_man_thrustDuration(type_output,par1,par2,par3,[g0])
   [dt]=CL_man_thrustDuration('dt',dm,F,isp,[g0])
   [dm]=CL_man_thrustDuration('dm',dt,F,isp,[g0])
   [F]=CL_man_thrustDuration('F',dt,dm,isp,[g0])
   [isp]=CL_man_thrustDuration('isp',dt,dm,F,[g0])
   
   

Description

  • This function computes thrust duration, mass consumed, thrust value or propellant specific impulse : given 3 of the previous parameters, it computes the missing one.

    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.

    Input arguments are always in the same order: dt, dm, F, isp

    Note : the flow rate (mass consumed per unit of time) can be computed as : flow = dm./dt

  • The equation used is the following :

  • Last update : 15/2/2008

Parameters

type_output:

string to define parameter to be computed. It can be 'dt,'dm','F' or 'isp'. (1x1)

par1:

first input: dt, dm, F or isp [s kg N or s] (1xN)

par2:

second input: dm, F or isp [kg N or s] (1xN)

par3:

third input: F or isp [N or s] (1xN)

g0:

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

output:

depending on type_ouput : dt, dm, F or isp [s kg N or s] (1xN)

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, CL_man_hohmann, CL_man_biElliptic

Examples

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