Targeting with fixed propellant load
Abstract
The inertial upper stage (IUS) for the space shuttle operation employs solid rocket stages with fixed, propellant loadings. This means that, if for a given mission the satellite weight is less than the maximum, the IUS will deliver higher delta V's than required. One way to waste the excess capability in order to achieve the desired orbit would be to execute a nonoptimal transfer which would require higher than maximum delta V's. An algorithm is presented which defines takeoff points on the parking orbit and the injection points on the orbit for which transfer orbits require a fixed delta V sub 1 and a fixed delta V sub 2 (defined by the satellite weight). It is assumed that both the parking and the target orbit are elliptical. This allows the use of the same algorithm for guidance. The transfer orbit achieved by the erroneous delta V sub 1 is regarded as a new parking orbit and the new transfer problem is solved by assuming a delta, delta V sub 1. The maximum value of delta, delta V sub 1 is the delta V sub 1 variation and its minimum value is the one which still yields a solution by the algorithm. The delta V sub errors are regarded as orbit injection errors and compensated in the usual way.
 Publication:

Flight Mechanics/Estimation Theory Symposium
 Pub Date:
 October 1980
 Bibcode:
 1980fmet.symp...51G
 Keywords:

 Inertial Upper Stage;
 Propellant Mass Ratio;
 Space Shuttles;
 Transfer Orbits;
 Upper Stage Rocket Engines;
 Algorithms;
 Orbital Position Estimation;
 Parking Orbits;
 Trajectory Control;
 Astrodynamics