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282 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 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL4
