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
(4.436)
(4.437)
(4.438)
(4.439)
(4.440)
Now suppose the aircraft is disturbed in angle of attack. The forces acting on the
airplane in the disturbed state are shown in Fig. 4.17b. We have
so that
F.ro - -Do + T - W sin Oo -. 0 (4.441)
F, - Fxo + AF;. (4.442)
- L sin Acy - D cos Aar + T - W sin 00 (4.443)
= (Lo + AL)sin Aar _ (Do + AD)cos Aa + T - W sin Oo
(4.444)
Similarly,
so that
AF\- - Lo Aa - AD
aAFx 8Fx=Lo_aAD
aA~ = a~ = - d~ = ~0 -- 8aD
Clu, - CL - CDct
Fzo = -Lo + W cos Oo
(4.445)
(4.446)
(4.447)
(4.448)
Fz - Fzo + AFz
= -(Lo + AL)cos Aaf - (Do + AD)sin Aa- + W cos 00 (4.449)
- -Lo - AL - DoAcy + W cos 00 (4.450)
AFz ~ -AL - DoAa
aAFz aFz aAL
aA -= aa =-a~L _Do
= - ?dL _ Do
(4.451)
(4.452)
(4.453)
EQUATIONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 383
or
It can be shown that
CZCL = -CLa - CD
Cxcr - CLa Acy - CDrr ~ -CDa
Cxq = CLq Act - CDq ~ -CDq
Cza = -CLd, - CDd Aa -CLa,
Czq = -CLq - CDq AcY ~ -CLq
Usually, CDcir and CDq are small and ignored.
(4.454)
(4.455)
(4.456)
(4.457)
(4~458)
Lateral-directiona/ equations of motion for sma// disturbance. Substitu-
ting for ACy, ACi, and ACn from Eqs. (4.412), (4.414), and (4.416) in Eqs.
(4.394), (4.396), and (4.398), we obtain
(m, dd _ b,CyB dd _ Cyp) Ap - (b,Cyp dd + Cy*) A4 + (m, dd _ b,Cyr dd) A k
= Cy8r A8r + Cyasa A8a (4.459)
(-C,p - bi CiB dd )AB + (-bi Cipdd + /x, dd )A4
+(_b,C,rdd _/z,dd )Ayr=Cl8rA8r+Cl8aA8a (4.460)
(-: C,,p - b,Cnp dd )Ap + (-bi Cnp dd _ /xz,dd )A4
+(_biCnrdd+Iz,dd )A =Cn8rA8r+Cn&1A8a (4.461)
where
d4
dt =P - (4.462)
d~
dt =r (4.463)
bi
Ixl =
(4.464)
(4.465)
b
= 2U
Ix
2~p U2Sb
384 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
Iz
Izl = ;-p U2Sb
Ixz
lxzl = 2pU2Sb
(4.466)
(4.467)
Now let us evaluate various derivatives like Cyp, C),4, etc., appearing in Eqs.
(4.459-4.461).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
动力机械和机身手册2(102)
