问题描述
我正在使用最佳控制优化飞机飞行。飞机飞行了一定距离（path 变量），然后模拟停止。求解器试图通过最大化质量值来最小化燃料消耗 m.Maximize(mass*tf*final)。
我添加了 2 个求解器控制变量：
油门控制，像这样：
Tcontr = m.MV(value=0.2,lb=0.2,ub=1)
Tcontr.STATUS = 1
Tcontr.dcosT = 0
和模拟时间，如下所示：
tf = m.FV(value=1,lb=0.0001,ub=1000.0)#
tf.STATUS = 1
系统按预期工作。 之后，我尝试实现另一个受控变量，坡度控制，如下所示：
Mu = m.MV(value=0,lb=-1.5,ub=1.5)
Mu.STATUS = 1
Mu.dcosT = 0
但出于某种原因，程序说“Mu”未定义。
如何定义 Mu 求解器控制变量？ 如何定义下一个求解器控制变量？
我的代码：
import numpy as np
import matplotlib.pyplot as plt
from gekko import GEKKO
import math
#Gekko model
m = GEKKO(remote=False)
#Time points
nt = 11
tm = np.linspace(0,100,nt)
m.time = tm
# Variables
Ro = m.Var(value=1.1)#air density
g = m.Const(value=9.80665)
pressure = m.Var(value=101325)#
T = m.Var(value=281)#temperature
T0 = m.Const(value=288)#temperature at see level
S = m.Const(value=122.6)
Cd = m.Const(value=0.1)#drag coef
Cl = m.Var(value=1)#lift couef
FuelFlow = m.Var()
D = m.Var()#drag
Thrmax = m.Const(value=200000)#maximum throttle
Thr = m.Var()
V = m.Var(value=100,lb=0,ub=240)#veLocity
#Vmin = m.Var(value=100)
gamma = m.Var(value=0)# Flight-path angle
gammaa = gamma.value
Xi = m.Var(value=0)# heading angle
Xii = Xi.value
#Mu = m.Var()# Bank angle (controlled var)
Muu = Mu.value
#AOA = m.Var()#angle of attack (not needed atm)
x = m.Var(value=0,lb=0)#x position
y = m.Var(value=0,lb=0)#y position
h = m.Var(value=1000)# height
mass = m.Var(value=60000)
path = m.Const(value=5000) #intended distance length
L = m.Var()#lift
p = np.zeros(nt)
p[-1] = 1.0
final = m.Param(value=p)
m.options.MAX_ITER=10000 # iteration number
#Fixed Variable
tf = m.FV(value=1,ub=1000.0)#
tf.STATUS = 1
# Controlled parameters
Tcontr = m.MV(value=0.2,ub=1)# solver controls throttle pedal
Tcontr.STATUS = 1
Tcontr.dcosT = 0
Mu = m.MV(value=0,ub=1.5)# solver controls bank angle - does not work
Mu.STATUS = 1
Mu.dcosT = 0
# Equations
m.Equation(x.dt()==tf*(V*(math.cos(gammaa.value))*(math.cos(Xii.value))))#
m.Equation(Thr==Tcontr*Thrmax)
m.Equation(V.dt()==tf*((Thr-D)/mass))#
m.Equation(mass.dt()==tf*(-Thr*(FuelFlow/60000)))#
m.Equation(D==0.5*Ro*(V**2)*Cd*S)
m.Equation(FuelFlow==0.75882*(1+(V/2938.5)))
m.Equation(x*final<=path)
#pressure and density part(density isnt working)
m.Equation(T==T0-(0.0065*h))
m.Equation(pressure==101325*(1-(0.0065*h)/T0)**((g*0.0289652)/(8.31446*0.0065)))# equation works
#m.Equation(Ro==(pressure*0.0289652)/(8.31446*T))
#2D addition part
m.Equation(y.dt()==tf*(V*(math.cos(gamma.value))*(math.sin(Xii.value))))#
m.Equation(Xi.dt()==tf*((L*math.sin(Muu))/(mass*V)))
m.Equation(L==0.5*Ro*(V**2)*Cl*S)
#3D addition part
# Objective Function
m.Minimize(final*(x-path)**2) #1D part
m.Maximize(mass*tf*final) #objective function
m.options.IMODE = 6
m.options.NODES = 2 # it was 3 before
m.options.MV_TYPE = 1
m.options.soLVER = 3
#m.open_folder() # to search for infeasibilities
m.solve()
tm = tm * tf.value[0]
fig,axs = plt.subplots(6)
fig.suptitle('Results')
axs[0].plot(tm,Tcontr,'r-',linewidth=2,label=r'$Tcontr$')
axs[0].legend(loc='best')
axs[1].plot(tm,V.value,'b-',label=r'$V$')
axs[1].legend(loc='best')
axs[2].plot(tm,x.value,'r--',label=r'$x$')
axs[2].legend(loc='best')
axs[3].plot(tm,D.value,'g-',label=r'$D$')
axs[3].legend(loc='best')
axs[4].plot(tm,mass.value,'g:',label=r'$mass$')
axs[4].legend(loc='best')
axs[5].plot(tm,T.value,'p-',label=r'$T$')
axs[5].legend(loc='best')
#axs[6].plot(tm,Ro.value,label=r'$Ro$')
#axs[6].legend(loc='best')
plt.xlabel('Time')
#plt.ylabel('Value')
plt.show()
解决方法
所以，我发现了问题所在。引用变量 Mu 的变量 Muu 必须在变量 Mu 之后定义，如下所示：
Mu = m.MV(value=0)
Mu.STATUS = 1
Mu.DCOST = 0
Muu = Mu.value
不是这样：
Muu = Mu.value
Mu = m.MV(value=0)
Mu.STATUS = 1
Mu.DCOST = 0