DEVELOPMENT OF AN ONLINE PARAMETER ESTIMATION CAPABILITY FOR AIRCRAFT

摘要

Flight Testing is the best means to determine thernflying qualities of aircraft and demonstrate compliancernto airworthiness regulations. Furthermore,rndata recorded in flight can also be usedrnto create mathematical models of the aircraft forrnfurther testing and development. These modelsrnconsist of system parameters known as stabilityrnand control derivatives, which are determinedrnfrom flight and wind tunnel tests by parameter estimationrntechniques. Aircraft system identificationrnas this field is known can be applied to: creaternmodels and data sets for aircraft simulators,rndesign flight control laws for stability augmentationrnsystems, and more recently evaluate UAV's.rnIncentives to perform such a task in real-time include:rndeveloping fault-tolerant aircraft architecturesrnand improved flight test efficiency due tornrapid data analysis. This paper addresses the issuernrelated to smoothing and differentiating thernnecessary data for system identification under thernconstraints of post-manoeuvre performance. Examplesrnof determining the reduced order modelsrnfor the SPPO mode of the Cranfield UniversityrnJetstream-31 (G-NFLA) and a simulated UAVrnare presented.