Align aircrafta with SIF and add aircrafta2

src/ADNLPProblems/aircrfta.jl

@@ -4,7 +4,7 @@ function aircrfta(; n::Int = default_nvar, type::Type{T} = Float64, kwargs...) w
   function f(x)
     return zero(eltype(x))
   end
-  x0 = T[0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0]
+  x0 = T[0.0, 0.0, 0.0, 0.0, 0.0, 0.1, 0.0, 0.0]
   lvar = T[-Inf, -Inf, -Inf, -Inf, -Inf, 0.1, 0.0, 0.0]
   uvar = T[Inf, Inf, Inf, Inf, Inf, 0.1, 0.0, 0.0]
 

src/ADNLPProblems/aircrfta2.jl

@@ -0,0 +1,44 @@
+export aircrfta2
+
+function aircrfta2(; n::Int = default_nvar, type::Type{T} = Float64, kwargs...) where {T}
+  function f(x)
+    return zero(eltype(x))
+  end
+  x0 = T[0.0, 0.0, 0.0, 0.0, 0.0, 0.1, 0.0, 0.0]
+  lvar = T[-Inf, -Inf, -Inf, -Inf, -Inf, 0.1, 0.0, 0.0]
+  uvar = T[Inf, Inf, Inf, Inf, Inf, 0.1, 0.0, 0.0]
+
+  function c!(cx, x)
+    rollrate, pitchrat, yawrate, attckang, sslipang, elevator, aileron, rudderdf =
+      x[1], x[2], x[3], x[4], x[5], x[6], x[7], x[8]
+    cx[1] =
+      -(3933 // 1000) * rollrate + (107 // 1000) * pitchrat + (126 // 1000) * yawrate -
+      (999 // 100) * sslipang - (4583 // 100) * aileron - (764 // 100) * rudderdf -
+      (727 // 1000) * pitchrat * yawrate + (839 // 100) * yawrate * attckang -
+      (6844 // 10) * attckang * sslipang + (635 // 10) * aileron * attckang
+    cx[2] =
+      -(987 // 1000) * pitchrat - (2295 // 100) * attckang - (2837 // 100) * elevator +
+      (949 // 1000) * rollrate * yawrate +
+      (173 // 1000) * rollrate * sslipang
+    cx[3] =
+      (2 // 1000) * rollrate - (235 // 1000) * yawrate + (567 // 100) * sslipang -
+      (921 // 1000) * aileron - (651 // 100) * rudderdf - (716 // 1000) * rollrate * pitchrat -
+      (1578 // 1000) * rollrate * attckang + (1132 // 1000) * aileron * attckang
+    cx[4] = pitchrat - attckang - (168 // 1000) * elevator - rollrate * sslipang
+    cx[5] = -yawrate - (196 // 1000) * sslipang - (71 // 10000) * aileron + rollrate * attckang
+    return cx
+  end
+
+  return ADNLPModels.ADNLPModel!(
+    f,
+    x0,
+    lvar,
+    uvar,
+    c!,
+    zeros(T, 5),
+    zeros(T, 5),
+    name = "aircrfta2",
+    minimize = true;
+    kwargs...,
+  )
+end

src/Meta/aircrfta.jl

@@ -22,6 +22,8 @@ aircrfta_meta = Dict(
 The aircraft stability problem by Rheinboldt, as a function
 of the elevator, aileron and rudder deflection controls.
 
+See aircrfta2 for the corrected version (CUTEst's AIRCRFTA2).
+
 classification NOR2-RN-8-5
 """,
   :origin_notes => raw"""

src/Meta/aircrfta2.jl

@@ -0,0 +1,62 @@
+aircrfta2_meta = Dict(
+  :nvar => 8,
+  :variable_nvar => false,
+  :ncon => 5,
+  :variable_ncon => false,
+  :minimize => true,
+  :name => "aircrfta2",
+  :has_equalities_only => true,
+  :has_inequalities_only => false,
+  :has_bounds => true,
+  :has_fixed_variables => true,
+  :objtype => :constant,
+  :contype => :general,
+  :best_known_lower_bound => -Inf,
+  :best_known_upper_bound => 0,
+  :is_feasible => true,
+  :defined_everywhere => missing,
+  :origin => :unknown,
+  :implementation => :both,
+  :url => "https://www.osti.gov/biblio/6449249, https://github.com/ralna/SIF/blob/master/AIRCRFTA2.SIF",
+  :notes => raw"""
+The aircraft stability problem by Rheinboldt, as a function
+of the elevator, aileron and rudder deflection controls.
+
+This is CUTEst's AIRCRFTA2. In the fourth equation the coefficient of
+the elevator is -0.168, and the bilinear term with coefficients 63.5
+(first equation) and 1.132 (third equation) is the product of the
+aileron and the angle of attack. aircrfta is the same problem with
+-1.168 and the product of the pitch rate and the angle of attack, as in
+CUTEst's AIRCRFTA.
+
+classification NOR2-RN-8-5
+""",
+  :origin_notes => raw"""
+Problem 9 in
+J.J. More',"A collection of nonlinear model problems"
+Proceedings of the AMS-SIAM Summer Seminar on the Computational
+Solution of Nonlinear Systems of Equations, Colorado, 1988.
+Argonne National Laboratory MCS-P60-0289, 1989.
+
+SIF input: Ph. Toint, Dec 1989.
+           Corrected version of AIRCRFTA by Tim Holy, Oct 2026.
+""",
+  :reference => raw"""
+@article{More1990,
+  title     = {A collection of nonlinear model problems. Computational Solution of Nonlinear Systems of Equations},
+  author    = {Mor{\'e}, Jorge J.},
+  journal   = {Lectures in Applied Mathematics},
+  volume    = {26},
+  pages     = {723--762},
+  year      = {1990},
+  publisher = {American Mathematical Society}
+}
+""",
+  :lib => "CUTEst:AIRCRFTA2",
+)
+get_aircrfta2_nvar(; n::Int = default_nvar, kwargs...) = 8
+get_aircrfta2_ncon(; n::Int = default_nvar, kwargs...) = 5
+get_aircrfta2_nlin(; n::Int = default_nvar, kwargs...) = 0
+get_aircrfta2_nnln(; n::Int = default_nvar, kwargs...) = 5
+get_aircrfta2_nequ(; n::Int = default_nvar, kwargs...) = 5
+get_aircrfta2_nineq(; n::Int = default_nvar, kwargs...) = 0

src/PureJuMP/aircrfta.jl

@@ -22,7 +22,7 @@ function aircrfta(; n::Int = default_nvar, kwargs...)
   @variable(nlp, -Inf <= yawrate <= Inf, start = 0.0)
   @variable(nlp, -Inf <= attckang <= Inf, start = 0.0)
   @variable(nlp, -Inf <= sslipang <= Inf, start = 0.0)
-  @variable(nlp, 0.1 <= elevator <= 0.1, start = 0.0)
+  @variable(nlp, 0.1 <= elevator <= 0.1, start = 0.1)
   @variable(nlp, 0.0 <= aileron <= 0.0, start = 0.0)
   @variable(nlp, 0.0 <= rudderdf <= 0.0, start = 0.0)
 

src/PureJuMP/aircrfta2.jl

@@ -0,0 +1,50 @@
+export aircrfta2
+
+function aircrfta2(; n::Int = default_nvar, kwargs...)
+  nlp = Model()
+
+  @variable(nlp, -Inf <= rollrate <= Inf, start = 0.0)
+  @variable(nlp, -Inf <= pitchrat <= Inf, start = 0.0)
+  @variable(nlp, -Inf <= yawrate <= Inf, start = 0.0)
+  @variable(nlp, -Inf <= attckang <= Inf, start = 0.0)
+  @variable(nlp, -Inf <= sslipang <= Inf, start = 0.0)
+  @variable(nlp, 0.1 <= elevator <= 0.1, start = 0.1)
+  @variable(nlp, 0.0 <= aileron <= 0.0, start = 0.0)
+  @variable(nlp, 0.0 <= rudderdf <= 0.0, start = 0.0)
+
+  @objective(nlp, Min, 0)
+  @constraint(
+    nlp,
+    cons1,
+    (
+      -3.933 * rollrate + 0.107 * pitchrat + 0.126 * yawrate - 9.99 * sslipang - 45.83 * aileron -
+      7.64 * rudderdf - 0.727 * pitchrat * yawrate + 8.39 * yawrate * attckang -
+      684.4 * attckang * sslipang + 63.5 * aileron * attckang
+    ) == 0
+  )
+  @constraint(
+    nlp,
+    cons2,
+    (
+      -0.987 * pitchrat - 22.95 * attckang - 28.37 * elevator +
+      0.949 * rollrate * yawrate +
+      0.173 * rollrate * sslipang
+    ) == 0
+  )
+  @constraint(
+    nlp,
+    cons3,
+    (
+      0.002 * rollrate - 0.235 * yawrate + 5.67 * sslipang - 0.921 * aileron - 6.51 * rudderdf -
+      0.716 * rollrate * pitchrat - 1.578 * rollrate * attckang + 1.132 * aileron * attckang
+    ) == 0
+  )
+  @constraint(nlp, cons4, (pitchrat - attckang - 0.168 * elevator - rollrate * sslipang) == 0)
+  @constraint(
+    nlp,
+    cons5,
+    (-yawrate - 0.196 * sslipang - 0.0071 * aileron + rollrate * attckang) == 0
+  )
+
+  return nlp
+end