Too many input arguments.

Question

Turgut Ataseven 2021-12-26

0
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此问题的直接链接

https://ww2.mathworks.cn/matlabcentral/answers/1617615-too-many-input-arguments

评论： Star Strider 2021-12-26

Hi. My code tries to solve 6 ODEs with 6 state variables [horizontal position (x1 and x2), altitude (x3), the true airspeed (x4), the heading angle (x5) and the mass of the aircraft (x6)] and 3 control inputs [engine thrust (u1), the bank angle (u2) and the flight path angle (u3)] by using Euler's method.

Velocities.m, Cruise_Vel.m, Des_Vel.m, Thr_cl.m, Thr_cr.m, Thr_des.m, fuel_cl.m, fuel_cr.m, fuel_des.m are functions in seperate files. Code in the main file (FlightPlan.m) is:

% Climb from h1=1100 [m] to h2=1600 [m] with α=5 flight path angle.
% Perform cruise flight for t=60 minutes.
% Turn with β=30 bank angle until heading is changed by η=270◦.
% Descent from h2=1600 [m] to h1=1100 [m] with ζ=4◦ flight path angle.
% Complete a 360◦ turn (loiter) at level flight.
% Descent to h3=800 [m] with κ=4.5◦ flight path angle.
% Aircraft Properties
W = .44225E+06;                             % .44225E+03 tons = .44225E+06 kg 
S = .51097E+03;                             % Surface Area [m^2]
% Equations
% dx1 = x4*cos(x5/180*pi)*cos(u3/180*pi);       
% dx2 = x4*sin(x5/180*pi)*cos(u3/180*pi);       
% dx3 = x4*sin(u3/180*pi);               
% dx4 = -C_D*S*p*x4.*x4/(2*x6)-g0*sin(u3/180*pi)+u1/x6; 
% dx5 = -Cl*S*p*x4/(2*x6)/sin(u2/180*pi);
% dx6 = -f;       
dx1dt = @(x4,x5,u3)            x4.*cos(x5*pi/180).*cos(u3*pi/180);       
dx2dt = @(x4,x5,u3)            x4*sin(x5*pi/180)*cos(u3*pi/180);       
dx3dt = @(x4,u3)               x4*sin(u3*pi/180);               
dx4dt = @(C_D,p,x6,x4,u3,u1)   -C_D*S*p*x4.*x4/(2*x6)-g0*sin(u3)+u1/x6; 
dx5dt = @(Cl,p,x6,x4,u2)       -Cl*S*p*x4/(2*x6)/sin(u2);
dx6dt = @(f)                   -f;       
% solving 1st order ODE using numerical methods 
t0=0;           
tend=66;
h=0.2; 
N=(tend-t0)/h;
t=t0:h:tend;
% Initial conditions
x1(1) = 0;               % Initial position [m]
x2(1) = 0;               % Initial position [m]
x3(1) = 3608.92;         % Initial altitude [ft]
x4(1) = Vtas_cl(1);      % Initial speed [m/s]
x5(1) = 0;               % Assuming aircraft headed to North initially.
x6(1) = W;               % Initial mass [kg]
u1(1) = Thr_jet_climb_ISA(1);   % Initial thrust [N]
u2(1) = 0;               % Initial bank angle [deg]
u3(1) = 5;               % Initial flight path angle [deg]
if and (t >= 0,t<=1) % Climb from h1=1100 [m] to h2=1600 [m] with α=5 flight path angle.
   x3(t) = linspace(3608.9,5249.3,2);                   % Changing altitude [m] -> [ft]
   x4(t) = Velocities(3608.9,5249.3);                   % Changing speed [m/s]
   x5(t) = 0;                                           % Changing head angle [deg]
   f(t) = fuel_cl(3608.9,5249.3);                       % Changing fuel flow [kg/min] 
   
   u1(t) = Thr_cl(3608.9,5249.3);                       % Changing thrust [N]
   u2(t) = 0;                                           % Changing bank angle [deg]
   u3(t) = 5;                                           % Changing flight path angle [deg]
   V_ver(t) = x4(t)*sin(u3(t)*pi/180);                  % Changing vertical speed [m/s]
end
if and (t >1,t<=61) % Perform cruise flight for t=60 minutes.
   x3(t) = 5249.3;                                      % Changing altitude [m] -> [ft]
   x4(t) = Cruise_Vel(5249.3);                          % Changing speed [m/s]
   x5(t) = 0;                                           % Changing head angle [deg]
   f(t) = fuel_cr(5249.3);                              % Changing fuel flow [kg/min] 
   
   u1(t) = Thr_cr(5249.3);                              % Changing thrust [N]
   u2(t) = 0;                                           % Changing bank angle [deg]
   u3(t) = 0;                                           % Changing flight path angle [deg]
   V_ver(t) = x4(t)*sin(u3(t)*pi/180);                  % Changing vertical speed [m/s]
end
if and (t >61,t<=62) % Turn with β=30 bank angle until heading is changed by η=270◦.
   x3(t) = 5249.3;                                      % Changing altitude [m] -> [ft]
   x4(t) = Cruise_Vel(5249.3);                          % Changing speed [m/s]
   x5(t) = 0:30:270;                                    % Changing head angle [deg]
   f(t) = fuel_cr(5249.3);                              % Changing fuel flow [kg/min] 
   
   u1(t) = Thr_cr(5249.3);                              % Changing thrust [N]
   u2(t) = 30;                                          % Changing bank angle [deg]
   u3(t) = 0;                                           % Changing flight path angle [deg]
   V_ver(t) = x4(t)*sin(u3(t)*pi/180);                  % Changing vertical speed [m/s]
end
if and (t >62,t<=63) % Descent from h2=1600 [m] to h1=1100 [m] with ζ=4◦ flight path angle.
   x3(t) = linspace(5249.3,3608.9,2);                   % Changing altitude [m] -> [ft]
   x4(t) = Des_Vel(5249.3,3608.9);                      % Changing speed [m/s]
   x5(t) = 270;                                         % Changing head angle [deg]
   f(t) = fuel_des(5249.3,3608.9);                      % Changing fuel flow [kg/min] 
   
   u1(t) = Thr_des(5249.3,3608.9);                      % Changing thrust [N]
   u2(t) = 0;                                           % Changing bank angle [deg]
   u3(t) = 4;                                           % Changing flight path angle [deg]
   V_ver(t) = x4(t)*sin(u3(t)*pi/180);                  % Changing vertical speed [m/s]
end
if and (t >63,t<=65) % Complete a 360◦ turn (loiter) at level flight.
   x3(t) = 3608.9;                                      % Changing altitude [m] -> [ft]
   x4(t) = Cruise_Vel(3608.9);                          % Changing speed [m/s]
   lon = [270 300 360 60 120 180 240 270];
   x5(t) = wrapTo360(lon);                              % Changing head angle [deg]
   f(t) = fuel_cr(3608.9);                              % Changing fuel flow [kg/min] 
   
   u1(t) = Thr_cr(3608.9);                              % Changing thrust [N] 
   u2(t) = 0;                                           % Changing bank angle [deg]
   u3(t) = 0;                                           % Changing flight path angle [deg]
   V_ver(t) = x4(t)*sin(u3(t)*pi/180);                  % Changing vertical speed [m/s]
end
if and (t >65,t<=66) % Descent to h3=800 [m] with κ=4.5◦ flight path angle.
   x3(t) = linspace(3608.9,2624.67,2);                  % Changing altitude [m] -> [ft]
   x4(t) = Des_Vel(3608.9,2624.67);                     % Changing speed [m/s] 
   x5(t) = 270;                                         % Changing head angle [deg]
   f(t) = fuel_des(3608.9,2624.67);                     % Changing fuel flow [kg/min] 
   
   u1(t) = Thr_des(3608.9,2624.67);                     % Changing thrust [N] 
   u2(t) = 0;                                           % Changing bank angle [deg]
   u3(t) = 4.5;                                         % Changing flight path angle [deg]
   V_ver(t) = x4(t)*sin(u3(t)*pi/180);                  % Changing vertical speed [m/s]
end
for i=1:N
% solving using Euler's explict method
   x1(i+1)=x1(i)+h*dx1dt(t(i),x4(i),x5(i),u3(i));       % line 127 %%%%%%%%%%%%%%%%%%%%%%%%%
   x2(i+1)=x2(i)+h*dx2dt(t(i),x4(i),x5(i),u3(i));
   x3(i+1)=x3(i)+h*dx3dt(t(i),x4(i),u3(i));
   x4(i+1)=x4(i)+h*dx4dt(t(i),C_D(i),p(i),x6(i),x4(i),u3(i),u1(i));
   x5(i+1)=x5(i)+h*dx5dt(t(i),Cl(i),p(i),x6(i),x4(i),u2(i));
   x6(i+1)=x6(i)+h*dx6dt(t(i),f(i));
  
end
tot=cell2mat(f);        % Total fuel consumption during mission [kg/min]
Tot_fuel=sum(tot);
figure(1)
plot3(x1(:),x2(:),x3(:));       % 3D position graph
figure(2)
plot(t,x4(:));                  % Vtas − Time graph
figure(3)
plot(t,V_ver(:));               % V_vertical − Time graph
figure(4)
plot(t,x5(:));                  % Heading − Time graph
figure(5)
plot(t,x6(:));                  % Mass − Time graph
figure(6)
plot(t,u1(:));                  % Thrust − Time graph
figure(7)
plot(t,u2(:));                  % Bank Angle − Time graph
figure(8)
plot(t,u3(:));                  % Flight Path Angle − Time graph
fprintf('Total fuel consumption during mission is %.2f [kg]',Tot_fuel*tend);
legend('Euler');

And I encountered with this error:

Error using FlightPlan>@(x4,x5,u3)x4.*cos(x5*pi/180).*cos(u3*pi/180)
Too many input arguments.
Error in FlightPlan (line 127)
   x1(i+1)=x1(i)+h*dx1dt(t(i),x4(i),x5(i),u3(i));
   

x3,x4,V_ver,x6,C_D,Cl,p,u1 varies with altitude. u1, u2 and u3 are not in any of the seperate files I mentioned above.

As you see, I need to plot "time vs variables" graphs and print total fuel consumption. I don't know if I defined them correctly with respect to time correctly, can you inform me?

What should I change to work Euler method correctly?

I can uplod other files if necessary.

Thank you all.