Analysis of targeting method for closed-loop guidance of a multi-stage space launch vehicle

This study considers the orbit insertion targeting problem for guidance of a multi-stage space launch vehicle. To design guidance algorithm for a particular mission target, the orbit designation method should be determined first, as the target orbit of closed-loop guidance during the upper stage flight is usually specified at the end of the final stage. We investigate some advantages of this single target approach over the one with intermediate targets in addition to the final target by comparing them in various flight conditions using an explicit guidance algorithm. We notice that in some cases application of the single targeting can be rather tricky and thus propose here an extended version of the single targeting algorithm that can be applied to problems where the target orbit plane has to be changed during the upper stages flight. We also demonstrate that this pseudo-single target method can be applied to these kinds of problems smoothly in contrast to the conventional single target algorithms by conducting numerical simulations for disturbed off-nominal conditions as well as for the nominal condition.