曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
B - 29.3013 2.5764
O 0
-0.2243 -4.6477_
Using MATLAB,I we obtain the eigenvalues ofthe above matrix A as
Ai - 0 (6.198)
A2 -. -8.4804 (6.199)
A3 -. -0.0087 (6.200)
A4.5 = -0.4897+_ j2.3468 (6.201)
The dampjng ratio <, natural frequency c.on,period T, and time for half amplitude
to for the Dutch-roll oscillation are obtained as follows:
<COn : 0.4897 (6.202)
COn =2.3468 ' (6.203)
T-- 27r
co~ 4-2 (6.204)
a = : 69 (6.205)
so that 4' -. 0.2043, tOn - 2.3973 rad/s, T - 2.6773 s, and to -. 1.4090 s-
The free response of the general aviation airplane to various assumed initial
conditions is shown in Figs. 6.13-6.16. From Fig. 6.13, we observe that the re-
sponse to an initial disturbance in sideslip of Sdeg exhibits osciIJatory motion
due to the Dutch-roll rootrs. The disturbance in sideslip decays to zero witfun
two or three oscillations lasting for about 5 to 6 s. The disturbance in sideslip
570
PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
Free Lateral-Dlrectional Rasponse of GeneraIAviation Alrplane
Fig. 6.13 Free OongitudinaD response of the general aviation airplane to a distur-
bance in sideslip.
Frea Lataral-Dfrectlonal Response of General Aviation AWdane
Fig 6.14 Free OongitudinaD response of the general arriation airplane to a distur-
bance in bank angle.
AIRPLANE RESPONSE AND CLOSED-LOOP CONTROL 571
Free Lateral-Directlonal Response ot General Aviation Airplane
┏━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━┓
┃0 2 4 6 8 10 12 14 16 18 ┃
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL3(119)
