function [hawk,man]=SystemData
% SYSTEMDATA     parameters and data for the wind tunnel aircraft manipulator system
%
%    function [hawk,man]=SystemData 
%

%   (c) James Whidborne & Ade Ishola
%   Cranfield University, 2 December 2024
   
%% aircraft model data
hawk.ma= 2.25;              % mass of aircraft (kg)
hawk.CLwalpha = 3.72;       % wing body lift curve slope (/rad)[Hinds p 84]
hawk.CLtalpha = 2.29;       % tailplane lift curve slope (/rad) [Hinds p 84]
hawk.CL0 = 0.21;            % zero alpha lift coefficient [Hinds p 85]
hawk.dwg = 0.57;            % downwash gradient  
hawk.mac = 0.161;           % mean aerodynamic chord  (m)
hawk.h_0 = 0.113;           % aerodynamic centre fraction of MAC   
hawk.h_cg = 0.2093;         % centre of gravity fraction of MAC   
hawk.h_cg = 0.18;           % centre of gravity fraction of MAC   
hawk.Sw = 0.115;	        % wing area ( m^2)
hawk.St = 0.029;            % tail area eq (72)
hawk.Cm0 = -0.05;           % initial moment coefficient
hawk.CD0 = 0.028;           % zero lift drag coefficient  
hawk.oef = 0.70;            % Oswald efficiency factor   
hawk.Ia = 0.2186;           % moment of inertia about y-axis (kg m^2)
hawk.Lt  = 0.3656;          % tail moment arm (m) p94 O'Gorman
hawk.VHbar = 0.5595;        % tailplane volume coefficient  
hawk.VHbar = hawk.St*hawk.Lt/hawk.Sw/hawk.mac; % ST*hawk.Lt/S/cbar
hawk.Zq = -hawk.VHbar*hawk.CLtalpha;    % Non dimensional normal force due to pitch rate derivative (Cook)
Cmq = hawk.Zq*hawk.Lt/hawk.mac;  % Pitch moment derivative (Cook)
hawk.Cmq = Cmq;             % pitch damping derivative 
hawk.g = 9.81;              % gravitational acceleration constant (m/s^2) 
hawk.Kt = 1/(pi*hawk.oef*(hawk.St/hawk.mac^2));

%% manipulator & wind tunnel data 
% lengths & masses
man.l1 = 0.32;              % link 1 length (m)
man.l2 = 0.32;              % link 2 length (m)
man.m1 = 2.0736;            % link 1 mass (kg)
man.m2 = 2.0736;            % link 12 mass (kg) 
% moments of inertia
man.I1 = (1/12)*man.l1^2*man.m1;  % link 1 inertia  (kg m^2)
man.I2 = (1/12)*man.l2^2*man.m2;  % link 1 inertia  (kg m^2)

man.VWT = 30; % wind tunnel speed (m/s)