An approximate solution for the maximum payload trajectory of a two-stage launch vehicle using a regular perturbation technique is presented. A zero-order solution for a two-stage vehicle based on a flat-earth approximation and negligible atmospheric effects is obtained in closed form. High-order correction terms are obtained from the solution of nonhomogeneous, first-order linear differential equations by quadrature. This promises the capability for an onboard optimal guidance law implementation.
An approach to optimal guidance of an advanced launch vehicle concept
01.01.1990
Aufsatz (Konferenz)
Keine Angabe
Englisch
Hybrid Approach to Near-Optimal Launch Vehicle Guidance
Online Contents | 1994
|Hybrid approach to near-optimal launch vehicle guidance
AIAA | 1994
|