Accession Number : ADA190567
Title : Parameter-Adaptive Model-Following for In-Flight Simulation.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Pineiro, Luis A
PDF Url : ADA190567
Report Date : Dec 1987
Pagination or Media Count : 320
Abstract : This thesis implements an adaptive, fast-sampling control law to compensate for changing aircraft parameters. The step-response matrix which is required for this implementation is identified recursively using a recently developed technique which does not require special 'test' signals and which automatically discounts old data depending on the input excitation detected. Tracking fidelity is maintained despite parameter changes which occur either abruptly or slowly. Simulations are conducted, using a model of the AFTI/F-16 aircraft and the control design package MATRIX, to test the resulting adaptive system. Actuator position and rate limits are discussed. The performance of the resulting system is excellent and demonstrates the relative advantages of adaptive controllers for in-flight simulation. Recommendations are made for future analysis including the use of moving-bank estimators.
Descriptors : *ADAPTIVE CONTROL SYSTEMS, *FLIGHT SIMULATION, *FLIGHT CONTROL SYSTEMS, ACTUATORS, ADAPTIVE SYSTEMS, AIRCRAFT, EXCITATION, INFLIGHT, INPUT, LIMITATIONS, POSITION(LOCATION), RATES, SIGNALS, TRACKING, DIGITAL SYSTEMS, MULTIVARIATE ANALYSIS, THESES, JET FIGHTERS
Subject Categories : Attack and Fighter Aircraft
Human Factors Engineering & Man Machine System
Distribution Statement : APPROVED FOR PUBLIC RELEASE