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
1990-01-01
Conference paper
No indication
English
Hybrid Approach to Near-Optimal Launch Vehicle Guidance
Online Contents | 1994
|Hybrid approach to near-optimal launch vehicle guidance
AIAA | 1994
|