Accession Number : ADA259286


Title :   A Simulation Study on Take-Off and Landing Dynamics of the Aircraft of a Fly-By-Wire Control System


Corporate Author : FOREIGN AEROSPACE SCIENCE AND TECHNOLOGY CENTER WRIGHT-PATTERSON AFB OH


Personal Author(s) : Feng, Yachang ; Chen, Gang ; Li, Peiqiong


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a259286.pdf


Report Date : 07 Jan 1993


Pagination or Media Count : 21


Abstract : Based on the dynamic theory of rigid body systems combined with the flying kinetic characteristics of aircraft during take-off and landing, a 6- degree of freedom aircraft equation for a rigid body system formed by landing gears-aircraft fuselage is formulated. The pilot time-domain mathematical models for the step-target tracking was proposed, and these models will help evaluate the flying qualities of the pilot/vehicle system during take-off and landing. Then the mechanical control system and the mathematical models for the control- by-wire system are established. The total time-domain simulation procedure of the non-wire type is worked out to provide a complete quantitative analysis of the dynamic qualities in take-off and landing of aircraft, and the results agree well with the flight test data.... Fly-by-wire-controlled aircraft, Pilot model, Mechanically controlled aircraft, Take-off and landing.


Descriptors :   *AIRCRAFT , *DYNAMICS , *TAKEOFF , *FLY BY WIRE CONTROL , *LANDING , TEST AND EVALUATION , MATHEMATICAL MODELS , CONTROL , SIMULATION , QUANTITATIVE ANALYSIS , CONTROL SYSTEMS , MODELS , WIRE , THEORY , PILOTS , TRACKING , TARGETS , TIME , FLIGHT , FUSELAGES , TRANSLATIONS , VEHICLES , KINETICS , EQUATIONS , TIME DOMAIN , BODIES , GEARS , CHINA , CHINESE LANGUAGE


Subject Categories : Aerodynamics
      Aircraft
      Flight Control and Instrumentation
      Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE