《飞行控制系统》课程实验
输出:
Root Locus Editor for Open Loop 1 (OL1)250.86200150.94-20-4010-600.98554035302520015105-80G.M.: 12.4 dB-100Freq: 9.45 rad/secStable loop-120-900.760.640.50.340.162040Open-Loop Bode Editor for Open Loop 1 (OL1)-50.985-100.94-135-15-180-200.860.76-25-40-300.640.50.340.16-20-10Real Axis0-225P.M.: 62.1 degFreq: 3.16 rad/sec-270-10121010101010Frequency (rad/sec)103图 2-3-2
设计:Kφ=0.5 Simulink仿真:
图 2-3-3
1.41.210.8??0.60.40.2000.511.52t(s)2.533.54
图 2-3-4
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《飞行控制系统》课程实验
4、 设计飞机航向控制系统,并进行仿真。
输入:
a1=alat([1,3],[1,3]) b1=blat([1,3],:) c1=clat([1,3],[1,3]) d1=dlat([1,3],:)
[n,d]=ss2tf(a1,b1,c1,d1,2) g=tf(n(2,:),d)
g1=tf([-10],[1 10]) g2=series(g,g1) sisotool(g2)
输出:
25Root Locus Editor for Open Loop 1 (OL1)250.38200.541515-20100.85-60G.M.: InfFreq: InfStable loop-809050.8100-45150.54-200.38-25-12-10-80.270.2200.140.0850.04-2250-90-135P.M.: 75.2 degFreq: 5.11 rad/sec-18010-20Open-Loop Bode Editor for Open Loop 1 (OL1)200.270.20.140.0850.0420010-4050-545-10-15-6-4Real Axis1010Frequency (rad/sec)2104
图 2-4-1
最大阻尼为0.664,kr=0.333
输入:
[b,a]=ss2tf(alat,blat,clat,dlat,2); g4=tf(b(1,:),a); num1=-10; den1=[1 10];
g1=tf(num1,den1); g=tf(b(3,:),a); g2=0.333*g;
g3=feedback(g1,g2); g5=series(g3,g4); sisotool(g5)
16
《飞行控制系统》课程实验
输出:
Root Locus Editor for Open Loop 1 (OL1)1500.9840.9660.920.750.99201000.996-50500.99810380060040020001-500.9981800.996-1000.9920.9840.9660.920.75-150-1000-5000Real Axis500900-150360270-100G.M.: -14.6 dBFreq: 0.632 rad/secUnstable loop50Open-Loop Bode Editor for Open Loop 1 (OL1)P.M.: 106 degFreq: 0.0319 rad/sec-90-4-202100010101010Frequency (rad/sec)104
图 2-4-2
设计:Kβ=0.7,Kψ=10
图 2-4-3
1.210.80.60.40.20-0.2012345678910
图 2-4-4
17
《飞行控制系统》课程实验
5、 设计飞机方向舵协调控制律,基于侧向线性模型(状态方程),进行航向控制系统的仿真。
图 2-5-1
发现输出波形不理想,对Kψ进行调整,取8
输入: subplot(221) xlabel('t(s)') plot(t,x) ylabel('\\Deltar') xlabel('t(s)') subplot(224) ylabel('\\Delta\\beta)') plot(t,x3) subplot(222) xlabel('t(s)') plot(t,x1) ylabel('\\Delta\\phi') xlabel('t(s)') subplot(221) ylabel('\\Deltap') plot(t,x4) subplot(223) xlabel('t(s)') plot(t,x2) ylabel('\\Delta\\psi')
18
《飞行控制系统》课程实验
输出:
0.20.153020?β0.10.050?p02t(s)46100-1002t(s)460.60.410?r0.20-0.2??02t(s)465002t(s)46
1.51??0.50-0.502t(s)46
图 2-5-2
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