Demonstrate the solar sail disturbance model in heliocentric orbit.

The orbit has an apogee of 1 AU and a perigee of 0.25 AU.
Uses the SailWithBoom CAD model. The sail is sun-pointing. The epoch
is JD 2000.

Functions demonstrated:
   QSunPointing
   SailDisturbance

Since version 7.
------------------------------------------------------------------------
See also DrawSCPlanPlugIn, Constant, Plot3D, Unit, JD2000, RARP2A,
RARP2E, RVFromKepler, CEcl2Eq, QSunPointing, DisturbanceStruct,
EnvironmentStruct, SailDisturbance, SailEnvironment
------------------------------------------------------------------------

Contents

%-------------------------------------------------------------------------------
%	  Copyright (c) 2005,2006 Princeton Satellite Systems, Inc.
%   All rights reserved.
%-------------------------------------------------------------------------------

clear SailDisturbance

%--------------------

Load the sail model

%--------------------
g = load('SailWithBoom.mat');
DrawSCPlanPlugIn('initialize',g);

%-------------------

Create the profile

%-------------------

Parameters for the orbit. We are creating an elliptical orbit

%--------------------------------------------------------------
aU            = Constant('au');
mu            = Constant('mu sun');
rP            = 0.25*aU;
rA            = aU;
a             = RARP2A( rA, rP );
e             = RARP2E( rA, rP );
p             = [];
[p.r, p.v, t] = RVFromKepler([a,0,0,0,e,0], [], mu );
p.jD          = JD2000 + t/86400;
n             = length(p.jD);
Plot3D(p.r/aU,[],[],[],'Interplanetary Orbit');
hold on; plot3(0,0,0,'y.','markersize',40)
plot3(p.r(1)/aU,p.r(2)/aU,p.r(3)/aU,'b*')

Vectors must be in ECI

%-----------------------
c   = CEcl2Eq;
p.r = c*p.r;
p.v = c*p.v;

Quaternion (always sun pointing)

%----------------------------------
p.q = QSunPointing( -Unit(p.r) );

% Gimbal angles. The sail is two body with a gimbaled boom
% The first angle is the one nearest the core
% The axes correspond to the angles
% The body array says each gimbal is at the joint between the

core and the boom. The core is defined as body 1 in the CAD file

%-----------------------------------------------------------------
p.angle    = zeros(2,n);
p.axis     = [1 0;0 1;0 0];
p.body     = [2 2];

%--------------------------

Create the data structure

%--------------------------

Get default structure for disturbances and environment

%-------------------------------------------------------
d = DisturbanceStruct;
d = EnvironmentStruct( d );

Turn on aerodynamics

%---------------------
d.aeroOn   = 0.0;

Turn off albedo

%----------------
d.albedoOn = 0.0;

Turn on solar

%--------------
d.solarOn  = 1.0;

Turn off magnetic torques

%--------------------------
d.magOn    = 0.0;

Turn off (planetary) radiation

%-------------------------------
d.radOn    = 0.0;

Turn off gravity gradient

%--------------------------
d.ggOn     = 0.0;

Orbiting the sun

%-----------------
d.planet   = 'Sun';

% Compute the disturbances. It will automatically plot the results.

The inputs are ( cad model, profile structure, function control structure )

%----------------------------------------------------------------------------
e = SailEnvironment( d.planet, p, d );
SailDisturbance( g, p, e, d );


%--------------------------------------
% PSS internal file version information
%--------------------------------------

Published with MATLAB® R2020a