Relative State Transition Matrix Using Geometric Approach for Onboard Implementation

Authors

  • Mankali P. Ramachandran Scientist/Engineer Flight Dynamics Group ISRO Satellite Centre Bangalore India 560017

Keywords:

State transition matrix, Formation flying, Orbit, Oblate.

Abstract

In the present study relative state transition matrix was obtained. It matches the relative motion of 2 satellites while including the oblate perturbation. The used formulation applies the geometric approach and is in Cartesian frame. The relative state transition matrix uses absolute state transition matrix of individual satellites. Thereon, simplification in computing methods and on-board implementation at controls are explored in a leader/follower coordination method. Numerical experiments illustrate the accuracy when the baseline separation is equal to 2 km and eccentricity is 0.005 and 0.05 for all the inclinations.

Author Biography

Mankali P. Ramachandran, Scientist/Engineer Flight Dynamics Group ISRO Satellite Centre Bangalore India 560017

Scientist/Engineer

Department of Space

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Published

2017-08-07

Issue

Section

Original Papers