Results of Short-Period Helicopter System Identification Using Output-Error and Hybrid Search-Gradient Optimization Algorithm

Table 2

Stability and control derivatives of the uncoupled short-period mode at 80 kt and 5,000 ft.

Flight derivatives	Identified parameters	CRLB	Normalized CRLB (%)
$\frac{Z_w}{m}$ [1/s]	0.4710	0.0188	4.0
$\frac{Z_q}{m}$ [m/s$\mathrm{\hspace{0.17em}\hspace{0.17em}}·\mathrm{\hspace{0.17em}\hspace{0.17em}}$rad]	13.2213	0.2062	1.6
$\frac{M_w}{I_y}$ [rad/$\text{m}·\text{s}$,]	−0.0675	0.0014	2.1
$\frac{M_q}{I_y}$ [1/s]	−2.9808	0.0375	1.3
$\frac{Z_{\delta m}}{m}$ [m/s^2$\mathrm{\hspace{0.17em}\hspace{0.17em}}·\mathrm{\hspace{0.17em}\hspace{0.17em}}$cm]	−1.8862	0.0329	1.7
$\frac{M_{\delta m}}{I_y}$ [rad/s^2$\mathrm{\hspace{0.17em}\hspace{0.17em}}·\mathrm{\hspace{0.17em}\hspace{0.17em}}$cm]	0.2308	0.0035	1.5