AbstractWe considered the problem of transferring the rocket's orbit to higher energy orbit, using minimum fuel cost, as a problem in change of energy, since this is most convenient. For the generalized Hohmann case (the departure; the transferring and the destination orbits are ellipses), we adopt the first configuration only, when the apogee of transfer orbit, and the apogee of destination orbit are coincident. Firstly, we assign the , increments in velocity at points (the position of peri-apse and apo-apse impulses respectively), as functions of the eccentricity of the transfer orbit, . Subsequently, we apply the optimum condition leading to the derivation of the quartic equation in , and showed how to deduce .A numerical example is presented, in which we determined the four roots of the quartic equation, by a numerical Mathematica Version 2.2.We selected the adequate consistent root, only one in this case, and evaluated for the two orbits of the couple Earth and Mars.This article is a new approach and leads to new discoveries involved in the problem, consequently adds new insight and avoids complexities of previous procedures.
On the optimization of the generalized coplanar Hohmann impulsive transfer adopting energy change concept
Acta Astronautica ; 56 , 4 ; 431-438
2004-04-14
8 pages
Article (Journal)
Electronic Resource
English
The optimization of the orbital Hohmann transfer
Online Contents | 2009
|The optimization of the orbital Hohmann transfer
Online Contents | 2009
|