WIND TUNNEL FREE-FLIGHT TEST FOR FLIGHT DYNAMICS AND CONTROL SYSTEM EXPERIMENTS

摘要

In recent years, there has been an increaseemphasis on the potential transition ofadvanced flight control techniques or radicalaircraft configurations to industrial application.Thus require extensive validation testing andbring urgent demand for development of therelative ease, safety, and low cost ofinvestigating infrastructure to flight dynamicsand control system testing. As part of theseefforts, the wind tunnel free-flight test facilityhas been developed. It utilizes powereddynamically-scaled vehicles flown in the tunneltest section that enable the application ofsubscale flight test results to full scale vehicles.This paper describes the development andapplication of the test technique.Implementation of hardware and softwaresubsystems, experimental approach, theassociate modeling and flight simulationprocedure prior to free-flight test will bediscussed as well as the application of the testtechnique to research on the stability andcontrol characteristics of a research fighteraircraft.