An approach to optimal guidance of an advanced launch vehicle conceptAn 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.
Document ID
19910045537
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Leung, Martin S. (Georgia Inst. of Tech. Atlanta, GA, United States)
Calise, Anthony J. (Georgia Institute of Technology Atlanta, United States)