Print Email Facebook Twitter A method for applying linear optimal control theory to the design of a regulator for a flexible- aircraft Title A method for applying linear optimal control theory to the design of a regulator for a flexible- aircraft Author Erkelens, L.J.J. Simons, J.L. Institution National Aerospace Laboratory NLR Date 1980-03-31 Abstract This report deals with determining a hypothetic control system which provides improved rigid body and structural mode damping of a flexible aircraft in order to improve the riding qualities and to minimize the wing bending moment during flights in turbulence. The equations of motion used in the computations are related to a high' performance fighter aircraft with external stores. The feedback gains have been determinated using linear optimal control theory. The quadratic optimization criterion used takes into account the normal acceleration at the pilot seat and the wing root bending moment. A number of optimal and suboptimal regulators has been calculated. The system performance has been expressed in terms of pole locations, frequency response, power spectra for both pilot seat acceleration and wing root bending moment. Also time histories of the aircraft response to a deterministic gust disturbance have been presented. Subject Gust alleviatorsAircraft stabilityRiding qualityDynamic responseModel responseAtmospheric tiirbulenceAircraft controlFlexible bodiesOptimal controlFighter aircraftsMathematical modelsBending momentsComputer programsWing loading To reference this document use: http://resolver.tudelft.nl/uuid:7d1a8a48-734d-4121-aab2-a393835fd21c Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR-TR 80032 U Part of collection Aerospace Engineering Reports Document type report Rights (c) 1980 National Aerospace Laboratory NLR Files PDF NLR_TR_80032_U.pdf 28.2 MB Close viewer /islandora/object/uuid:7d1a8a48-734d-4121-aab2-a393835fd21c/datastream/OBJ/view