曝光台 注意防骗
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┣━━━━━━━━━━━━━━━┫
┃ -...I.II..\- ┃
┗━━━━━━━━━━━━━━━┛
o 0.5
2 2.5 3 3.5 4
t, s
Fig. 6.24 Unit-step response (lateral-directional) of the general aviation airplane:
roll rate.
Dbiai = -Cypb:(Cip Cnr - Clr Cnr) + C),*(CiBCnrb{ - C,p Izl - IxZI Cnp
- Cu Cnpb:t) + b21Cyp(Ctp Cnr - Ctr Cnp) + bi (mi - bi Cvr )
x(CLp Cnp - Clp Cnp) (6.245)
E8iar = Cy4bi(CipCnr - Cnp Clr) (6.246)
The transfer function for angle of yaw is given by
A p(s)
A8a~s~ =
mis - bi Cyps - ~yB
-(Clp + bi CiBs.)\
-(Cnp + bi CnBs)
-(bi C),pS + C).d)
--Cipbis + Ix1S2
-CnpbiS - /z1S2
Cy8a
Cl8a
Cnbt,
Alar
(6.247)
Let Nl/,./s" denote the determinant in the numerator. Expanding, we get
Nlr;.Bo = Arr S3 + BrpS2 + Cy;s + Dv; (6.248)
!
584 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
step rosponw, phi
~ Roll Subsidence Approjamation
-_ Completc Fiflh-Order System
┏━━━┳━━━━━┳━━━━━━┳━━━━━┳━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━┓
┃ ┃ ┃ I ┃ ┃ Il... ┃
┣━━━╋━━━━━┫ ┣━━━━━╋━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━┳━━━━━━━━━━━━━┫
┃ ┃ ┃ ┃ ┃'- - - -, - - -""'-'-' :.-- = - N'-----.- - -: - - - ┃ ." " " " - ┃
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动力机械和机身手册3(71)
