Fa2004 16.33311-10 U - a deg e deg 100 250 300 1600 1400 1200 1000 800 600 15 0δ 300 Figure 14: Nonlinear simulation- Note: throttle at the limits, speed not well main- tained but path similar to linear simulation
Fall 2004 16.333 11–10 0 50 100 150 200 250 300 −10 −5 0 5 U α deg θ deg 0 50 100 150 200 250 300 0 200 400 600 800 1000 1200 1400 1600 Href H 0 50 100 150 200 250 300 −4 −3 −2 −1 0 1 2 3 4 δ e 10*δ t Figure 14: Nonlinear simulation Note: throttle at the limits, speed not well maintained, but path similar to linear simulation
Fa2004 16.33311-11 Recall: could have used throttle to control y directly(see 6-9 Alternative altitude control strategy However, engine lag dynamics are much slower Sunny *+LAhu*huts Signal Buide LKhdu(s)」 上 Clock Mux 5 Figure 15: Altitude Controller using Fb to the thrust 31 0.16 0.045 -0.9-08-0.7-0.6-050.4-0302-0.1 eal Axis igure 16: Root loci associated with simulation(h to dt). Lead controller
K_hu*Khnu(s) Khdu(s) height Lead altu To Workspace Sum4 Signal 2 Signal Builder Signal Generator Scope1 Scope Saturation Sat Ramp Mux Mux Mux Dele Delt u w q theta h all Longitudinal Model -KK_u K_th K_q Kun(s) Kud(s) Engine Lead JNt(s) JDt(s) Engine Dynamics JNe(s) JDe(s) Elevator Lag 0 Constant1 Clock u Fall 2004 16.333 11–11 • Recall: could have used throttle to control γ directly (see 6–9) – Alternative altitude control strategy – However, engine lag dynamics are much slower. Figure 15: Altitude Controller using FB to the thrust. −1 −0.9 −0.8 −0.7 −0.6 −0.5 −0.4 −0.3 −0.2 −0.1 0 0.1 −2 −1.5 −1 −0.5 0 0.5 1 1.5 2 0.82 0.6 0.42 0.31 0.22 0.16 0.1 0.045 0.6 0.31 0.22 0.16 0.1 0.045 1.75 0.82 2 0.42 0.75 0.25 1.25 0.5 1 0.75 1.5 1.25 0.25 0.5 1 2 1.5 1.75 with h FB to δ t command Real Axis Imaginary Axis Figure 16: Root loci associated with simulation (h to δt). Lead controller