Contents

Enceladus mission

Has the following stages:

1. Spiral out of Earth orbit
2. Straight line to Saturn
3. Spiral to Enceladus orbit about Saturn (unfinished?)
4. Spiral into Enceladus orbit (unfinished?)
%--------------------------------------------------------------------------
% See also: TwoDEscape, StraightLineOptimal, EngineReport,
% SimulateStraightLineTrajectory
%--------------------------------------------------------------------------

%--------------------------------------------------------------------------
%	Copyright (c) 2019 Princeton Satellite Systems, Inc.
%   All rights reserved.
%--------------------------------------------------------------------------

% Constants
radiusEnceladus     = 252;    % km
sMAEnceladus        = 237948; % km
eEnceladus          = 0.0047; % eccentricity
radiusSaturn        = Constant('equatorial radius saturn');
radiusEarth         = Constant('equatorial radius earth');
muSun               = Constant('mu sun');
muEnceladus       	= 0.113*radiusEnceladus^2;
muSaturn            = Constant('mu saturn');
muEarth             = Constant('mu earth');
aU                  = Constant('au');

% Mission parameters
specificPower       = 1000; % W/kg
sigmaTank           = 0.02; % fuel tank fraction

% Spiral from earth
mDry                = 80000; % kg
mF                  = 20000;
m0                  = mDry + mF;
mT                  = sigmaTank*mF;
nEngines            = 6;
p                   = nEngines*5e6; % W
mE                  = p/specificPower;
mP                  = mDry - mE - mT;
uE                  = 140e3; % m/s
eff                 = 0.3;
thrust              = 2*p*eff/uE;
r                   = Constant('equatorial radius earth') + 386;

disp('Spiral:')
mFConsumed = TwoDEscape( muEarth, r, uE, thrust, mDry, mF );

vEarth = sqrt(muSun/aU);
Spiral:
Spiral time:               61.34 days
Fuel consumed:           4867.27 kg
Final radius:          477450.81 km
Delta-V:                    6.99 km/s
Exhaust velocity:         140.00 km/s

Straight line to Saturn

year      = 365.25*86400;
d         = Straight2DStructure;
d.dF      = 1.2e9; % 1.67e9
d.eta     = eff;
d.sigma   = specificPower; % W/kg
d.tF      = 2*year;
d.uE      = uE/1000; % km/s
d.v0      = 0;
d.mP      = 1000;
[uE, thrust, data] = StraightLineOptimal( d );
[~,out] = EngineReport( thrust, data );
SimulateStraightLineTrajectory( out );

fprintf('Straight line:\n  Delta-V: %g km/s\n',out.vS*2);

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% $Date$
% $Id: f9e14f2f94516766a3a5d00e0c579a4fd1d76d5f $
Straight line:
  Delta-V: 76.4084 km/s