曝光台 注意防骗
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CL = p\/-2S
2 *1500
= ~225~ 0.6*1002
- 0.4
W
ALi - pgSr
1500
= ~225~0 6~9.81* 8
-. 25.4842
Cm8 = -a,Virlrr
-. -0.08 * 0.6 * 0.9 * 0.5
- -0.0216
Nv = ac.w - (-,.,)f -+ V 7 [(1- : )+-,,,]
-. 0.24 - 0.15 + 0.08 *0.6*0.9
Ot)9) [1- 0.35+ 20~25 54~8432 ]
- 0.4193
STATIC STABILITY AND CONTROL
A8e CL(Xc8 - Nm)
Az - Cm8
0.4(0.25 - 0.4193)
== ---
-0.02~6
- -3.1352
=:= 1.0194
A8e - -3.1352 *1.0194
- -3.1960 deg
Now let us calculate the stick force per g as follows:
N:n = a.. - (:g-),+~
[(l - ;f ) _ 2y,] (1 _,CC,,.,)
0.08 * 0.6 *
= 0.24 - 0.15+ 0 9) (1 _ 0.35 _ _. ,)
0.1
x [l - 0.l-,.] '
- 0.3369
&C/ ),,= cg - NL
- 0.25 - 0.3369 '
- -0.0869
dc:. = G, ( V~) ,l,Se e CC., (:C/ ),.
- l.0 *1500 * 0.9 * 2.0 , 0.6 . (-000~66) (-0.0869)
-. 39.105 N/g
257
V.. [(l-g )+2V, (l+')]
(3.235)
An : //-2
Rg
l002
= 1000 * 9.81
258
PERFORMANCE] STABILITY, DYNAMICS, AND CONTROL
3.5 Static Directional Stability
In Section 3.3, we considered the airplane stability with respect to a disturbance
in angle of attack. This disturbance was assumed to be contained in a vertical
plane. We assumed that the airplane response in pitch was sufficiently slow so that
the pitch rate q could be ignored. In Se'9tion 3.4, we extended this approach to the
study of airplane stability during simple maneuvers. In this section, we will study
the airplane stability with respect to a disturbance in sideslip, which is contained in
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