A Mathematical Model of a Single Main Rotor Helicopter for ... - Read

gust levels. For this representation, scale length and the wind velocity can be
specified as functions of altitude.
velocity.
The rms gust levels are dependent upon wind
Linearized Six-Degree-of-Freedom Model
A computer subroutine is available that generates the coefficients of a linear,
first-order set of differential equations that represents the rigid body dynamics of
the helicopter for small perturbations from a fixed operating point. The principal
assumption necessary to generate this linear set of equations is that the helicopter
initial angular rates are zero. The differential equations are of the form: G
k = [FIX + [GI6
where x represents perturbations from trim of the state variables u, w, q, 8, v,
p, $, and r; and 6 represents the coctrol displacements from trim Ase, A6,, Asa,
and A$. The generation of the F and G matrices and a description of each element
is given in appendix I.
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