Perturbation Theorem, Integral Expansion Theorem and their application to guidance
Abstract
The Perturbation Theorem and the Integral Expansion Theorem are presented. By the first theorem, the propagation value of the deviation caused by disturbance along the trajectory can be estimated. By the second theorem, a function defined on a closed interval, satisfying the condition for the expansion in Taylor Series, can be expanded on the particular base eigenfunction with the expansion coefficients only containing multiple integral of the function in a closed region. Finally, three simple examples applying the theorems to guidance are given.
 Publication:

14th Space Technology and Science Symposium
 Pub Date:
 1984
 Bibcode:
 1984spte.symp.1017L
 Keywords:

 Astrodynamics;
 Entire Functions;
 Perturbation Theory;
 Series Expansion;
 Spacecraft Guidance;
 Spacecraft Trajectories;
 Taylor Series;
 Astrodynamics