Analyze the thruster layout for the Asteroid Prospector spacecraft

Create a thruster layout and save it to a mat-file for further use. The two files saved are:

- RCS-AsteroidProspector.mat - APThrusters-Xenon.mat

The function loads AsteroidProspector.obj as the basis for the thruster layout.

One u is 10 cm

%-----------------
u               = 0.1;              % meters
zBox            = 1.4*u;
xBox            = 3*u;
yBox            = 2*u;
thrust          = 0.5;              % N
g               = 9.806;
pressure        = 350*6894;
uE              = 235*g;
thrustCoeff     = thrust/pressure;
thrustIon       = 1.8e-3/pressure;  % N
iSpBIT3         = 2460;
uEBIT3          = iSpBIT3*g;
xenonMass       = 6;
rhoXenon        = 2750;             % kg/m^3
fuelMass        = 2;
rhoFuel         = 1240;             % kg/m^3
tNom            = 300;
pI              = 350*6895;
pF              = 100*6895;


rThruster = [xBox/2 -xBox/2 -xBox/2  xBox/2 xBox/2 -xBox/2 -xBox/2  xBox/2;...
             yBox/2  yBox/2 -yBox/2 -yBox/2 yBox/2  yBox/2 -yBox/2 -yBox/2;...
             zBox    zBox     zBox     zBox      0       0       0       0];


uThruster = Unit([-1  1  1 -1 0 0 0 0;...
                  -1 -1  1  1 0 0 0 0;...
                  -1 -1 -1 -1 1 1 1 1]);

ThrusterLayout('initialize','AsteroidProspector.obj')
ThrusterLayout('update',uThruster,rThruster);

save(FileFullpath('RCS-AsteroidProspector.mat'), 'rThruster','uThruster');

[v, mP] = BDDesign( fuelMass, rhoFuel, tNom, pI, pF );

fprintf(1,'\n\n------------- Variable Data for RCS System -------------\n\n');
fprintf(1,'fuelDensity     %12.4f\n',	rhoFuel);
fprintf(1,'fuelPressure    %12.4f\n',	pI);
fprintf(1,'mass            %12.4f\n',	fuelMass);
fprintf(1,'massPressurant  %12.4f\n',	mP);
fprintf(1,'temperatureTank %12.4f\n',   tNom);
fprintf(1,'volumeTank      %12.4f\n',	v);

fprintf(1,'\n\n------------- Thruster Data for RCS System Setup File -------------\n\n');
for k = 1:size(rThruster,2)
    fprintf(1,'[%7.2f %7.2f %7.2f %7.2f %7.2f %7.2f %7.2e  %7.2f %7.5f %7.4f %7.2f]\n',...
                rThruster(:,k),uThruster(:,k),thrustCoeff,uE,0.02,0.001,1);
end

[v, mP] = BDDesign( xenonMass, rhoXenon, tNom, pI, pF );

fprintf(1,'\n\n------------- Variable Data for Xenon System -------------\n\n');
fprintf(1,'fuelDensity     %12.4f\n',	rhoXenon);
fprintf(1,'fuelPressure    %12.4f\n',	pI);
fprintf(1,'mass            %12.4f\n',	xenonMass);
fprintf(1,'massPressurant  %12.4f\n',	mP);
fprintf(1,'temperatureTank %12.4f\n',   tNom);
fprintf(1,'volumeTank      %12.4f\n',	v);

rThruster = [0;0;-zBox/2];
uThruster = [0;0;1];

fprintf(1,'\n\n------------- Thruster Data for Xenon System Setup File -------------\n\n');
for k = 1:size(rThruster,2)
    fprintf(1,'[%7.2f %7.2f %7.2f %7.2f %7.2f %7.2f %7.2e  %7.2f %7.5f %7.4f %7.2f]\n',...
                rThruster(:,k),uThruster(:,k),thrustIon,uEBIT3,0.02,0.001,1);
end

save(FileFullpath('APThrusters-Xenon.mat'), 'thrust','g','pressure',...
  'uE','thrustCoeff','thrustIon','iSpBIT3','uEBIT3','xenonMass','rhoXenon',...
  'fuelMass','rhoFuel','tNom','pI','pF','rThruster','uThruster');



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

ans =
     []


------------- Variable Data for RCS System -------------

fuelDensity        1240.0000
fuelPressure    2413250.0000
mass                  2.0000
massPressurant        0.0025
temperatureTank     300.0000
volumeTank            0.0023


------------- Thruster Data for RCS System Setup File -------------

[   0.15    0.10    0.14   -0.58   -0.58   -0.58 2.07e-07  2304.41 0.02000  0.0010    1.00]
[  -0.15    0.10    0.14    0.58   -0.58   -0.58 2.07e-07  2304.41 0.02000  0.0010    1.00]
[  -0.15   -0.10    0.14    0.58    0.58   -0.58 2.07e-07  2304.41 0.02000  0.0010    1.00]
[   0.15   -0.10    0.14   -0.58    0.58   -0.58 2.07e-07  2304.41 0.02000  0.0010    1.00]
[   0.15    0.10    0.00    0.00    0.00    1.00 2.07e-07  2304.41 0.02000  0.0010    1.00]
[  -0.15    0.10    0.00    0.00    0.00    1.00 2.07e-07  2304.41 0.02000  0.0010    1.00]
[  -0.15   -0.10    0.00    0.00    0.00    1.00 2.07e-07  2304.41 0.02000  0.0010    1.00]
[   0.15   -0.10    0.00    0.00    0.00    1.00 2.07e-07  2304.41 0.02000  0.0010    1.00]


------------- Variable Data for Xenon System -------------

fuelDensity        2750.0000
fuelPressure    2413250.0000
mass                  6.0000
massPressurant        0.0034
temperatureTank     300.0000
volumeTank            0.0031


------------- Thruster Data for Xenon System Setup File -------------

[   0.00    0.00   -0.07    0.00    0.00    1.00 7.46e-10  24122.76 0.02000  0.0010    1.00]

Analyze the thruster layout for the Asteroid Prospector spacecraft

Contents

One u is 10 cm