Range optimization for a supersonic aircraftRange optimal trajectories for an aircraft flying in the vertical plane are obtained from Pontryagin's Minimum Principle. Control variables are load factor n which appears nonlinearly in the equations of motion and throttle setting eta, which appears only linearly. Both controls are subject to fixed bounds, namely eta between values of 0 and 1 and absolute value of n not greater than n(max). Additionally, a dynamic pressure limit is imposed, which represents a first-order state-inequality constraint. For fixed flight time, fixed initial coordinates, and partially fixed final coordinates, the effect of the load factor limit absolute value of n not greater than n(max) is studied. Upon varying n(max), six different switching structures are obtained. All trajectories involve singular control along arcs with active dynamic pressure limit.
Document ID
19910065050
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Seywald, Hans (NASA Langley Research Center Hampton, VA, United States)
Cliff, Eugene M. (Virginia Polytechnic Institute and State University Blacksburg, United States)
Well, Klaus H. (DLR Wessling, Federal Republic of Germany, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 91-2712
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference