Accession Number : AD0860127
Title : A Manual Stand-By Control System For Tactical Fighter Aircraft Through the Use of An Asymmetric Thrust Reverser.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Longstaff, Thomas W.
Report Date : MAR 1969
Pagination or Media Count : 133
Abstract : An asymmetric thrust reverser is evaluated for use as a manual stand-by control system for a tactical fighter aircraft which has lost hydraulic pressure. The aircraft evaluated is an F-5 with its stabilator locked in the vicinity of the trim position. The thrust reverser, located in the ejector section of the engine, is then used as the primary pitch control device. Part of the engine thrust is deflected by one of the thrust reverser doors, which in turn generates a pitching moment on the aircraft. A three degree of freedom longitudinal analog simulation of this F-5 is flown to determine the effect of the thrust reverser as a control. Two cases are covered: (1) Flight near Mach 0.88 and 20,000 ft. altitude; (2) Approach and landing. (Author)
Descriptors : *FLIGHT CONTROL SYSTEMS), (*TURBOJET ENGINES, THRUST REVERSAL), (*JET FIGHTERS, (*AERODYNAMIC CONTROL SURFACES, FAILURE), (*HYDRAULIC EQUIPMENT, REDUNDANT COMPONENTS), AVIATION SAFETY, ELECTRIC WIRE, SIMULATION, THESES.
Subject Categories : Attack and Fighter Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE