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fusee Scilab Group Scilab Function fusee
NAME
fusee - a set of Scilab macro for a landing rocket problem
FUSEE
[xdot]=fusee(t,x)
Dynamical motion equation for the rocket
FINIT
finit()
Initialises the following parameters for rocket landing.
k : The acceleration of the rocket engines
gamma
: The moon gravity acceleration.
umax : the gaz ejection flow out.
mcap : the mass of the space capsule.
cpen : penalisation in the cost function of the final state.
FUSEEGRAD
[ukp1]=fuseegrad(niter,ukp1,pasg)
niter
: number of gradient iteration steps.
ukp1 : initial control value ( vector of sie 135 )
pasg : the gradient step value.
DESCRIPTION
Iterate a gradient method and returns the computed control.
FUSEEP
[pdot]=fuseep(t,p)
DESCRIPTION
adjoint equation for the landing rocket problem.
POUSSE
[ut]=pousse(t)
return the value of a piece wise constant control build on the discrete
control uk
UBANG
[uk]=ubang(tf,tcom)
returns a bang-bang control, 0 form time 0 to tcom and 1 form tcom to
tf.
FCOUT
[c,xk,pk,ukp1]=fcout(tf,uk,pasg)
DESCRITION
optimise the following cost function by gradient iterations.
c = -m(tf) + C*( h(tf)**2 + v(tf)**2)
SFUSEE
[]=sfusee(tau,h0,v0,m0,Tf)
DESCRIPTION
computes the rocket trajectory when a bang-bang control is used tau is
the commutation time.
h0 : The initial position (high)
v0 : The initial speed ( negative if the rocket is landing )
m0 : The total initial mass ( capsule and fuel).
Tf : Time horizon.
EQUAD
DESCRIPTION
[xk,pk]=equad(tf,uk)
Computes the state and adjoint state of the rocket system for a given
control ur.
TRAJ
[xt]=traj(t)
returns a piece wise value of the mass evolution.
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