Accession Number : ADP007503
Title : Trajectory Optimization for Hypersonic Aircraft Guidance,
Corporate Author : HONEYWELL SYSTEMS AND RESEARCH CENTER MINNEAPOLIS MN
Personal Author(s) : Schutz, R. L. ; Hofman, M. J. ; Case, A. M. ; Sheikh, S. I.
Report Date : MAR 1992
Pagination or Media Count : 16
Abstract : A computationally efficient real-time trajectory optimization and guidance approach for hypersonic aircraft is described. The optimization approach is based on Euler-Lagrange energy state approximations. A three-dimensional, spherical-earth, aircraft-motion model with constraints on temperature, dynamic pressure, acceleration, and angle of attack is employed. Climb-to-orbit, return-from-orbit, flight-to-designated-landing-site, unpowered-abort, and powered-abort flight conditions are considered. Different performance criterion are used for different problems. Solution methods of varying computational complexity and performance capability are developed. An exact solution to the optimization problem using iteration on adjoint variables is developed.
Descriptors : *HYPERSONIC AIRCRAFT, *TRAJECTORIES, *FLIGHT CONTROL SYSTEMS, ABORT, ACCELERATION, AIRCRAFT, ANGLE OF ATTACK, ANGLES, APPROACH, ATTACK, DYNAMIC PRESSURE, DYNAMICS, ENERGY, FLIGHT, GUIDANCE, ITERATIONS, LANDING, MODELS, MOTION, OPTIMIZATION, ORBITS, PRESSURE, REAL TIME, SITES, TEMPERATURE, THREE DIMENSIONAL, TIME, VARIABLES.
Subject Categories : Air Navigation and Guidance
Flight Control and Instrumentation
Research and Experimental Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE