Delta-V for a Hohmann transfer between LEO and GEO.

Start in a 200 km circular 9.1 deg orbit. The initial orbit and transfer orbit mass are acheivable by a Falcon 1e rocket.

The Falcon 1e can lift smaller masses into higher orbits so this is not necessarily the best you can do with the Falcon 1e.

Since version 8.
------------------------------------------------------------------------
See also OrbMnvrInclAndHohm and RocketMass.
------------------------------------------------------------------------

Compute the required velocity change
Design the transfer orbit stage

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

h  = 200;            % km Orbit height at separation
i  = 9.1;            % deg Orbit inclination at separation
rI = 6378.165 + 200; % km Initial orbit radius
rF = 42167;          % km Final orbit radius
iI = i*pi/180;       % Initial inclination
iF = 0;              % Final inclination (geosynchronous)

Compute the required velocity change

%-------------------------------------
[deltaV, deltaI, tOF] = OrbMnvrInclAndHohm( rI, rF, iI, iF );

mP  = 170; % kg payload. This makes mT what the Falcon 1e can lift.

iSP = 290; % sec for a modern solid. Liquids can do better.

structuralRatio = 0.1;% Not the best

Design the transfer orbit stage

%--------------------------------
if( exist('RocketMass','file') )
  [mF, mT, mS] = RocketMass( iSP, mP, structuralRatio, deltaV.total ) ;
else
  mF = 0;
  mT = 0;
  mS = 0;
  warning('Function "RocketMass" (in Propulsion module) not found. Cannot compute fuel and structural mass.')
end

fprintf('\nGeo transfer from %4.1f km and %4.1f deg\n',h,i);
fprintf('Structural ratio    = %8.1f\n',     structuralRatio)
fprintf('Isp                 = %8.1f sec\n', iSP)
fprintf('Total mass          = %8.1f kg\n',  mT)
fprintf('Fuel mass           = %8.1f kg\n',  mF)
fprintf('Structural mass     = %8.1f kg\n',  mS)
fprintf('Payload mass        = %8.1f kg\n',  mP)
fprintf('Transfer orbit time = %8.1f hours\n',  tOF/3600)
fprintf('Total Delta-V       = %8.2f km/s\n',  deltaV.total)

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

Geo transfer from 200.0 km and  9.1 deg
Structural ratio    =      0.1
Isp                 =    290.0 sec
Total mass          =    986.3 kg
Fuel mass           =    742.1 kg
Structural mass     =     74.2 kg
Payload mass        =    170.0 kg
Transfer orbit time =      5.3 hours
Total Delta-V       =     3.97 km/s

Delta-V for a Hohmann transfer between LEO and GEO.

Contents

Compute the required velocity change

Design the transfer orbit stage