Evaluation of aerodynamic stability and unwanted vibrations on control surfaces under extreme gust loads

Abstract

The paper evaluates the aerodynamic hindrance caused by gust loads and vibrations produced by the aircraft control surfaces during different oscillated flight regimes. The approach aims to design an automated system in order to predict the unknown and required parameters of aircraft in flight testing phase. A mathematical model of a full-scale civilian Unmanned Ariel Vehicle (UAV) was tested along with its industrial prototype to study and observe the unique characteristics of aircraft. The model was synchronized with the parameters of the industrial prototype, and checked according to the aviation standards. It was then verified using the data acquired through real-time flight-testing at the research base. The geographical coordinates of the research base and the weather data from the previous two years were also obtained and introduced into the automated system. A series of automated flight tests were conducted with and without extreme conditions to analyze the feasibility of the novel approach. The experiments were carried out not only to verify the validity and effectiveness of new purposed system but also the characteristics of aircraft through the new method. The simulated results would be beneficial in considering the accuracy of the new automated system, in contrast with the conventional system. The automated system will give the upper hand to verify the end product accurately and with no life-threatening tasks in challenging circumstances, besides it will also assist to refine the procedures and techniques in pre-production research and manufacturing.