An adaptive guidance law for single stage to low earth orbitAn adaptive guidance algorithm based on a cubic spline representation of the ascent profile and imposition of a dynamic pressure constraint is studied for a single stage to low earth orbit. The flight path is divided into initial and terminal phases. In the initial phase, fully adaptive, and in the terminal phase, semi-adaptive, guidance schemes are used. The cubic spline paqrameters are determined by gradient optimization for maximum payload to orbit. In the terminal phase, a linear quadratic regulator is used to derive the optimal feedback gains to keep the vehicle close to the nominal path. The computational aspects of the guidance algorithm are examined and criteria are developed to ensure stability and convergence.
Document ID
19890065171
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pamadi, Bandu N. (Vigyan, Inc. Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 89-3443
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference