actrim.m

matlab的FDC工具箱

      V = 45;
   end

   H = input('Give (initial) altitude [m], default = 0: ');
   if isempty(H)
      H = 0;
   end

   psi  = input('Give heading [deg], default = 0: ')*pi/180;
   if isempty(psi)
      psi = 0;
   end

   ok = 0;
   while ok~= 1
      gammatype = input('Use specified manifold pressure or flight-path angle ([m]/f)? ','s');
      if isempty(gammatype)
         gammatype = 'm';
      end
      if gammatype == 'f'
         gamma = input('Give flightpath angle [deg], default = 0: ')*pi/180;
         if isempty(gamma)
            gamma = 0;
            ok = 1;
         end
      elseif gammatype == 'm'
         ok = 1;
      else
         disp('   Invalid entry. Please choose either ''m'', or ''f''');
      end
   end
      

   phidot   = 0;
   psidot   = 0;
   thetadot = 0;

   rolltype = 'b';   % No rolling, so for reasons of simplicity the default setting, 
                     % i.e. a body-axes roll, will be used.

elseif opt == 2                                       % STEADY TURNING FLIGHT
                                                      % ---------------------
   clc
   disp('Steady turning flight.');
   disp('======================');

   ok = 0;
   while ok~= 1
      turntype = input('Do you want a coordinated or uncoordinated turn ([c]/u)? ','s');
      if isempty(turntype)
         turntype = 'c';
      end
      if turntype == 'c' | turntype == 'u'
         ok = 1;
      else
         disp('   Invalid entry. Please choose either ''c'', or ''u''');
      end
   end

   V = input('Give desired airspeed [m/s], default = 45: ');
   if isempty(V)
      V = 45;
   end

   H = input('Give initial altitude [m], default = 0: ');
   if isempty(H)
      H = 0;
   end

   psi = input('Give initial heading [deg], default = 0: ')*pi/180;
   if isempty(psi)
      psi = 0;
   end

   ok = 0;
   while ok~= 1
      gammatype = input('Use specified manifold pressure or flight-path angle ([m]/f)? ','s');
      if isempty(gammatype)
         gammatype = 'm';
      end
      if gammatype == 'f'
         gamma = input('Give flightpath angle [deg], default = 0: ')*pi/180;
         if isempty(gamma)
            gamma = 0;
            ok = 1;
         end
      elseif gammatype == 'm'
         ok = 1;
      else
         disp('   Invalid entry. Please choose either ''m'', or ''f''');
      end
   end

   phidot = 0;
   thetadot = 0;

   ok = 0;
   while ok~= 1
      answ = input('Use specified turnrate or radius ([t]/r)? ','s'); 
      if isempty(answ)
         answ = 't';
      end
      if answ == 't'
         psidot = input('Give desired rate of turn [deg/s], default = 0: ')*pi/180;
         if isempty(psidot)
            psidot = 0;
         end
         ok = 1;
      elseif answ == 'r'
         R = input('Give desired turn radius (>0) [m], default = straight & level: ');
         if isempty(R) ~= 1
            psidot = V/R;
         else
            psidot = 0;
         end
         ok = 1;
      else
         disp('   Invalid entry. Please choose either ''t'', or ''r''');
      end
   end

   rolltype = 'b';   % No rolling, so for reasons of simplicity the default setting, 
                     % i.e. a body-axes roll, will be used.

elseif opt == 3                                              % STEADY PULL-UP
                                                             % --------------
   clc
   disp('Steady pull-up.');
   disp('===============');

   V = input('Give desired airspeed [m/s], default = 45: ');
   if isempty(V)
      V = 45;
   end

   H = input('Give initial altitude [m], default = 0: ');
   if isempty(H)
      H = 0;
   end

   psi = input('Give initial heading [deg], default = 0: ')*pi/180;
   if isempty(psi)
      psi = 0;
   end

   gammatype = 'f';  % Use specified flightpath angle and numerically
                     % adjust manifold pressure
   gamma = input('Give initial flightpath angle [deg], default = 0: ')*pi/180;
   if isempty(gamma)
      gamma = 0;
   end

   phidot = 0;
   psidot = 0;

   thetadot = input('Give pull-up rate [deg/s], default = 0: ')*pi/180;
   if isempty(thetadot)
      thetadot = 0;
   end

   rolltype = 'b';   % No rolling, so for reasons of simplicity the default setting, 
                     % i.e. a body-axes roll, will be used.

elseif opt == 4                                                 % STEADY ROLL
                                                                % -----------
   clc
   disp('Steady roll.');
   disp('============');

   V = input('Give desired airspeed [m/s], default = 45: ');
   if isempty(V)
      V = 45;
   end

   H = input('Give initial altitude [m], default = 0: ');
   if isempty(H)
      H = 0;
   end

   psi = input('Give initial heading [deg], default = 0: ')*pi/180;
   if isempty(psi)
      psi = 0;
   end

   ok = 0;
   while ok~= 1
      gammatype = input('Use specified manifold pressure or flight-path angle ([m]/f)? ','s');
      if isempty(gammatype)
         gammatype = 'm';
      end
      if gammatype == 'f'
         gamma = input('Give flightpath angle [deg], default = 0: ')*pi/180;
         if isempty(gamma)
            gamma = 0;
            ok = 1;
         end
      elseif gammatype == 'm'
         ok = 1;
      else
         disp('   Invalid entry. Please choose either ''m'', or ''f''');
      end
   end

   thetadot = 0;
   psidot = 0;

   phidot = input('Give desired roll-rate [deg/s], default = 0: ')*pi/180;
   if isempty(phidot)
      phidot = 0;
   end

   if phidot ~= 0
      ok = 0;
      while ok~= 1
         rolltype = input('Roll in body or stability axes reference frame ([b]/s)? ','s');
         if isempty(rolltype)
            rolltype = 'b';
         end
         if rolltype == 'b' | rolltype == 's'
            ok = 1;
         else
            disp('   Invalid entry. Please choose either ''b'', or ''s''');
         end
      end
   else
      rolltype = 'b';   % No rolling, so for reasons of simplicity the default setting, 
                        % i.e. a body-axes roll, will be used.
   end

else
   % Set helpvariable skip = 1, to ensure that the aircraft configuration
   % does not have to be entered if the user chooses option 5 = QUIT.
   % --------------------------------------------------------------------
   skip = 1;
end

%%%%

if skip ~= 1         % DEFINE CONFIGURATION OF THE AIRPLANE, IF NOT QUITTING
                     % -----------------------------------------------------

   % For the 'Beaver' model, the flap angle and engine speed define the
   % configuration of the aircraft (engine speed is selected by the pilot
   % and maintained by the regulator of the propeller). Other aircraft
   % may have other definitions, like gear in/out, slats, settings of trim
   % surfaces, multiple engines, etc., so change the following lines if
   % required!
   % ---------------------------------------------------------------------
   deltaf = input('Give flap angle [deg], default = 0: ')*pi/180;
   if isempty(deltaf)
      deltaf = 0;
   end

   n = input('Give engine speed [RPM], default = 1800: ');
   if isempty(n)
      n = 1800;
   end

   % For the 'Beaver' aircraft, the engine power is determined by the engine
   % speed, which has been set above, and the manifold pressure, which will
   % be involved in the trim process if the flightpath angle gamma is user-
   % specified, or kept constant if pz is user-specified (defined in string-
   % variable gammatype). If the manifold pressure is to be adjusted by the
   % numerical trim algorithm, it is important to specify a meaningful esti-
   % mation of the manifold pressure, because otherwise the trim process may
   % not converge, or may give unrealistic results if the optimization pro-
   % cess converges to a LOCAL minimum.
   % -----------------------------------------------------------------------
   if gammatype == 'f'
      pz = input('Give estimate of manifold pressure pz ["Hg], default = 20: ');
   else  % gammatype == 'm'
      pz = input('Give manifold pressure pz ["Hg], default = 20: ');
   end
   if isempty(pz)
      pz = 20;
   end

%   % Hdot is the rate-of-climb, which is a function of the flightpath angle
%   % (change the program if you want to specify Hdot itself in stead of
%   % the flightpath angle gamma).
%   % ----------------------------------------------------------------------
%   Hdot = V*sin(gamma);

   % G is the centripetal acceleration, used for the coordinated turn
   % constraint.
   % ----------------------------------------------------------------
   G = psidot*V/9.80665;

   % If steady, uncoordinated, turning condition must be determined, the
   % roll angle can be specified freely; equilibrium will be obtained for
   % a trimmed-flight sideslip angle, which in this case usually will be
   % quite large.
   % --------------------------------------------------------------------
   phi = [];
   if opt == 2 & turntype == 'u';  % Steady turn, uncoordinated.
      phi = input('Give desired roll angle phi [deg], default = 0: ')*pi/180;
   end

   if isempty(phi)
      phi = 0;
   end

   % All variables which specify the flight condition will be put in the
   % vector ctrim (constants for trim process). The variables which are
   % varied by the minimization routine FMINS will be put into the vector
   % vtrim (variables for trim process). These vectors will have to be
   % redefined for aircraft which use other state or input vectors.
   %
   % The variable phi in ctrim is used for uncoordinated turns only; if a
   % coordinated turn is required, the coordinated turn constraint determines
   % the values of phi and beta. Type HELP ACCONSTR for more info.
   %
   % Definition: