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AIRCRFTA.SIF (Ph. Toint's SIF input of problem 9 in J. J. Moré, "A collection of nonlinear model problems") fixes the three controls through their bounds, elevator = 0.1, aileron = 0 and rudderdf = 0, and starts each of them at its fixed value, with the five states at zero. The ADNLPProblems and PureJuMP implementations started the elevator at 0, outside its bounds 0.1 <= elevator <= 0.1. The starting point is now (0, 0, 0, 0, 0, 0.1, 0, 0) in both implementations. It satisfies the variable bounds, and the constraint values there are (0, -2.837, 0, -0.1168, 0). See JuliaSmoothOptimizers#37. Assisted-by: Claude Opus 5.5 <noreply@anthropic.com>
aircrfta2 is the aircraft stability problem of AIRCRFTA2.SIF. It differs from aircrfta (AIRCRFTA.SIF) in two places: the elevator coefficient in the fourth equation is -0.168 rather than -1.168, and the bilinear terms with coefficients 63.5 (first equation) and 1.132 (third equation) are products of the aileron and the angle of attack rather than of the pitch rate and the angle of attack. With the controls fixed at their SIF values, the five equations have a solution, so the best known upper bound on the constant objective is 0. See JuliaSmoothOptimizers#37. Assisted-by: Claude Opus 5.5 <noreply@anthropic.com>
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Gives
aircraftathe same starting point as the SIF version.Adds
aircrafta2, which SIF calls the corrected version ofaircrafta. This problem differs both in coefficients and the form of the product.