Demonstrate the various orbit change functions.

These are a low thrust spiral, a Hohmann transfer and
a Hohmann transfer to an elliptical orbit.

------------------------------------------------------------------------
See also DVHoh, DVHohE, LTSpiral, Tfr2Imp, Tfr3Imp, Accel
------------------------------------------------------------------------

Constants

%--------------------------------------------------------------------------
%   Copyright (c) 1996 Princeton Satellite Systems, Inc.
%   All rights reserved.
%---------------------------------------------------------------------------
%   Since version 1.
%---------------------------------------------------------------------------

Constants

%----------
degToRad = pi/180;

m  = 1000; % kg
f  = 2; % N

a0    = 6378.165 + 500;
aF    = 42167;
accel = 1.e-3*f/m; % km/sec^2

[dV,dVRatio,t] = LTSpiral(a0,aF,accel);
fprintf('Low Thrust Spiral\n----------------\nDelta V         = %8.2f km/sec\nDelta V Ratio   = %8.4f\nTransfer Time   = %8.2f\n',dV,dVRatio,t)

[dV,dV1,dV2] = DVHoh(a0,aF);
fprintf('\nHohmann Transfer\n----------------\nTotal Delta V   = %8.2f km/sec\nPerigee Delta V = %8.4f\nApogee Delta V  = %8.4f\n',dV,dV1,dV2)

[dV,dV1,dV2,eT] = DVHohE(0,a0,0.04,aF);
fprintf('\nHohmann Transfer To a Slightly Elliptic Orbit\n---------------------------------------------\nTotal Delta V   = %8.2f km/sec\nPerigee Delta V = %8.4f\nApogee Delta V  = %8.4f\n',dV,dV1,dV2)

i0 = 23;
iF =  0;
e0 =  0;
eF =  0;
n  = 10;


dV = Tfr3Imp(e0,a0,eF,aF,n,i0,iF);
fprintf('\n\nDelta V Two Impulse with Initial Inclination of  %8.2f deg = %8.2f km/sec\n',i0,dV);
dV = Tfr2Imp(e0,a0,eF,aF,i0,iF);
fprintf('Delta V Three Impulse with Initial Inclination of %8.2f deg = %8.2f km/sec\n',i0,dV);


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

Low Thrust Spiral
----------------
Delta V         =     4.54 km/sec
Delta V Ratio   =   1.1892
Transfer Time   =    26.26

Hohmann Transfer
----------------
Total Delta V   =     3.82 km/sec
Perigee Delta V =   2.3698
Apogee Delta V  =   1.4463

Hohmann Transfer To a Slightly Elliptic Orbit
---------------------------------------------
Total Delta V   =     3.78 km/sec
Perigee Delta V =   2.3969
Apogee Delta V  =   1.3840


Delta V Two Impulse with Initial Inclination of     23.00 deg =     4.40 km/sec
Delta V Three Impulse with Initial Inclination of    23.00 deg =     4.07 km/sec

Demonstrate the various orbit change functions.

Contents

Constants