Accession Number : ADA008662


Title :   A Differential Thrust Controller for Air Cushion Landing System Aircraft


Descriptive Note : Master's thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING


Personal Author(s) : Husson, Matthew A.


Full Text : http://www.dtic.mil/get-tr-doc/pdf?AD=ADA008662


Report Date : DEC 1974


Pagination or Media Count : 108


Abstract : A control system was designed to improve the heading response of the Air Cushion Landing System aircraft to differential thrust input. The aircraft equations of motion and low speed stability derivatives were obtained from work done at the Air Force Flight Dynamics Laboratory at Wright-Patterson Air Force Base, Ohio. Five different values of engine response time-delay were selected for the design study. These time-delay values were 0.2, 0.4, 0.6, 0.8, and 1.0 seconds. The principle used for the design was to compensate the system ignoring the time-delay and then to compensate for the time-delay. A two stage lead network was used to reduce the effect of the engine time-delay. The system was simulated by using a digital computer program called MIMIC, which simulates the functions of an analog computer.


Descriptors :   *AIRCRAFT , *LANDING GEAR , *AIR CUSHION VEHICLES , CONTROL SYSTEMS , THESES , FEEDBACK , THRUST CONTROL , DIGITAL SIMULATION , CLOSED LOOP SYSTEMS , CONTROL JETS.


Subject Categories : SURFACE EFFECT VEHICLES & AMPHIBIOUS VEHICLES


Distribution Statement : APPROVED FOR PUBLIC RELEASE