Optimal on primer–vector four–impulse rendezvous in the vicinity of circular orbit
Abstract:
The four–impulse rendezvous of two spacecrafts moving initially on close near–circular coplanar orbits is investigated in linear statement. Numerical dependencies of the angles of application of impulses and their orientation of the angular distance of the transfer are found for the solutions satisfying sufficient optimality conditions. Simple analytical dependencies that approximate these numerical ones with sufficient accuracy are suggested. The use of these formulas allows to lead the process of determining optimal solution to the inversion of the matrix of influence, which coefficients are found analytically. The domains of existing optimal on primer–vector four–impulse solutions are investigated. The efficiency of the suggested method is illustrated by the solution of the problem of rendezvous of two- spacecrafts initially moving on the same circular orbit.
Keywords:
optimal space maneuvers, rendezvous maneuvers, multi–impulse transfers, primer–vector, geostationary satellites
