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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL4

时间:2010-06-01 00:57来源:蓝天飞行翻译 作者:admin 点击:
曝光台 注意防骗 曝光赚黑心钱的骗子公司北京大地印象装饰装潢有限公司 谨防上当
  

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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL


   Substituting the mass and aerodynamic characteristics of the general aviation
airplane, we get the approximate transfer functions of the general aviation airplane
for aileron and rudder inputs as follows.
    For the roll subsidence mode,
A~(s)      0.1342
A8a~s~ = s~0~46s+0038. .   7)
Aq3(s)     0.0118
A8~s~ = s~0 0046s+0.0387)
(6.280)
(6.281)
'1
588 PERFORMANCE,STABILITY,DYNAMICS,ANDCONTROL
     For the Dutch-roll approximation,
           Ap(s) __      0.0076s             (6.282)
    A8a~s~-. 76~:;~7tf
               Ayr(s) --    ._0.00'76s _0.002             (6.283)
    A8a~s~-6. 76.6~~76.
             A[3(s) __    0.0024S2+0.16s       .    (6.284)
     A8r~S~-6. .76~.6~~76.
     Arjr(s)=. _0.1582s-0.0294    (6.285)
     A78r(S)=6. 76-.t~7f16.
For the spiral approximation,
    Ap(s)_ 0.0021s2+0.0016s
    ~8(s~= ood0: -J:0-4S
           Ap(s) _        0.0097s
   A8o~s~=-.6~fT.T. ~04S
                         Ap(s)_ = 1.8204 x l0~4 SZ +8.6321 x 10-4S
   A8r~S- ~7~7~=G-
              Ayj(s) .            0.0061
   ~ ))=-6. -7. To4S
               A8 (s '
(6.286)
(6.287)
(6.288)
(6.289)
We note that
                                                                            p(s)  = s A~(s)                                                    (6,290)
                                                                     r (s) = sAp(s)                                               (6.291)
                                                                           n zurplane and the final
 Usmg the above transfer functions of the g~tatralt~fesatioof the lateral_directional
 va}ue theorem (see Chapter 5), the steady-st       Ls a step input can be obtained.
  variables Ap, A4, and p for a grven input such as :
  However, this is left as an exercise to the reader.
  6.3.4  Lateral.Oirectional Frequency Response
                 ~elateral_directionalfrequency responrseol:tsouaileron and rudderinputs is ofinter-
        est oecause the pilotinput to these two contrrol surfaces can be considered as a signal
 
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