An explicit solution to the exoatmospheric powered flight guidance and trajectory optimization problem for rocket propelled vehiclesA derivation of an explicit solution to the two point boundary-value problem of exoatmospheric guidance and trajectory optimization is presented. Fixed initial conditions and continuous burn, multistage thrusting are assumed. Any number of end conditions from one to six (throttling is required in the case of six) can be satisfied in an explicit and practically optimal manner. The explicit equations converge for off nominal conditions such as engine failure, abort, target switch, etc. The self starting, predictor/corrector solution involves no Newton-Rhapson iterations, numerical integration, or first guess values, and converges rapidly if physically possible. A form of this algorithm has been chosen for onboard guidance, as well as real time and preflight ground targeting and trajectory shaping for the NASA Space Shuttle Program.
Document ID
19770059962
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Jaggers, R. F. (McDonnell Douglas Technical Services Co. Houston, Tex., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1977
Subject Category
Space Communications, Spacecraft Communications, Command And Tracking