Demonstrate the AttitudeProfile function.

Plots the resulting quaternion and the separation angle from the secondary target.

Mode 1:      Body y to Sun     (Body x to Nadir secondary)
Mode 2:      Body x to Lat/Lon (Body y to Sun secondary)
Mode 3:      Different Lat/Lon

See also AttitudeProfile, ObservationTimeWindows, PlotOrbit, Q2Eul, Plot2D, Date2JD, ObservationTimeWindowsPlot, Period, RVFromKepler

Orbit and time information
Mode 1: Body y to Sun (Body x to Nadir secondary)
Mode 2: Body x to Lat/Lon (Body y to Sun secondary)
Mode 3: Body x to Lat/Lon (Body y to Sun secondary)
Compute observation windows for this target
Compute the attitude profile
Plot quaternion and separation angle over time

%--------------------------------------------------------------------------
%   Copyright (c) 2009 Princeton Satellite Systems, Inc.
%   All rights reserved.
%--------------------------------------------------------------------------
%   Since version 8.
%--------------------------------------------------------------------------

clear a; clear b; clear c; clear d;

Orbit and time information

%---------------------------
d.jD0 = Date2JD;
d.t = 0:15:86400;
d.el = [6800,pi/6,pi/3,0,0,0];
[d.r,d.v] = RVFromKepler( d.el, d.t );
PlotOrbit(d.r,d.t,d.jD0);

Mode 1: Body y to Sun (Body x to Nadir secondary)

%---------------------------
a.type1  = 'nadir';
a.body1   = [1;0;0];
a.target1 = [];
a.type2  = 'orbitnormal';
a.body2   = [0;1;0];
a.target2 = [];

Mode 2: Body x to Lat/Lon (Body y to Sun secondary)

%---------------------------
b.type1  = 'latlon';
b.body1   = [1;0;0];
b.target1 = [0;90];
b.type2  = 'orbitnormal';
b.body2   = [0;1;0];
b.target2 = [];

Mode 3: Body x to Lat/Lon (Body y to Sun secondary)

%---------------------------
c.type1  = 'latlon';
c.body1   = [1;0;0];
c.target1 = [35;-90];
c.type2  = 'orbitnormal';
c.body2   = [0;1;0];
c.target2 = [];

Compute observation windows for this target

%--------------------------------------------
fov = pi;
[track,obs] = ObservationTimeWindows( d.el, [b.target1,c.target1], d.jD0, d.t(end), fov );
b.window    = obs(1).window;
c.window    = obs(2).window;

ObservationTimeWindowsPlot(track,obs);

Compute the attitude profile

%-----------------------------
d = AttitudeProfile( d, a, b, c );

Plot quaternion and separation angle over time

%-----------------------------------------------
Plot2D(d.t/3600,d.q,'Time (hrs)','Quaternion')
Plot2D(d.t/3600,d.sep*180/pi,'Time (hrs)','Separation Angle (deg)')

eul = zeros(3,length(d.t));
for k = 1:length(d.t)
  eul(:,k) = Q2Eul( d.q(:,k) );
end
Plot2D(d.t/Period(6800),eul*180/pi,'Time (orbits)',{'Roll','Pitch','Yaw'},'Euler Angles (deg)')


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