Hello again,

For and electric propulsion system optimization, i’m trying to impose zero thrust during eclipse phases, I have this function created:

```
function Step_eclipse(j,r...,r_par...)
Re = 6378
if r_par[j] + sqrt(r^2 - Re^2) ≤ 0
return s=0
else
return s=1
end
end
register(lowThrust, :Step_eclipse, 3, Step_eclipse; autodiff=true)
@NLconstraint(lowThrust, T[j]== Tmax*Step_eclipse(j,r...,r_par...))
```

where Tmax is a constant. But it is constantly dropping error in register and the user defined function definition.

‘r_par’ and r are defined as:

```
@NLexpressions(lowThrust,begin
rx[j=1:n], (r[j]/s[j])*sqrt(μ/p[j])*(cos(L[j]) + (alpha[j]^2)*cos(L[j])+2*h[j]*k[j]*sin(L[j]))
ry[j=1:n], (r[j]/s[j])*sqrt(μ/p[j])*(sin(L[j]) - (alpha[j]^2)*sin(L[j])+2*h[j]*k[j]*cos(L[j]))
rz[j=1:n], (2*r[j]/s[j])*(h[j]*sin(L[j]) - k[j]*cos(L[j]))
end)
@NLexpressions(lowThrust,begin
r_par[j=1:n], rx[j]*r_sun[1] + ry[j]*r_sun[2] + rz*[j]*r_sun[3]
end)
@NLexpressions(lowThrust,begin
q[j=1:n], 1 + f[j]*cos(L[j]) + g[j]*sin(L[j])
r[j=1:n], p[j]/q[j]
alpha[j=1:n], 1 - h[j]^2 - k[j]^2
s[j=1:n], 1 + (h[j])^2 + (k[j])^2
end)
```

P,f,g,h,k, L are the optimization variables and alpha is a NLexpression.

I don’t know how to implement it correctly, if the full code is required please let me know, i’m a little bit desperate.