Oscillation Susceptibility Analysis of the ADMIRE Aircraft along the Path of Longitudinal Flight Equilibriums in Two Different Mathematical Models

Figure 8

Transfer from 𝛼^1=0.0786697[rad]=4.509^∘; 𝑞^1=0[rad/s]; 𝜃^1=−0.428832[rad]=−24.58^∘ into a state which is appropriate for the touch-down moment: 𝜃^−𝛼^=0 and 𝜃^>0 (𝜃^ small).

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