Prabha Srinivasan, Ashok Joshi, Indira Narayanaswamy, Hemalatha E
DOI Number: N/A
Conference number: IFASD-2015-098
In a fly-by-wire airvehicle, an assessment of the structural coupling levels through analysis and experiments provides structural data for the design of notch filters which are generally utilized in the flight control system to attenuate the flexible response pickup. This is necessitated as during flight, closed loop control actuation driven with flexible response inputs could lead to stability and performance related problems. In the present work, a sensitivity based approach has been implemented to achieve improved predictions of aircraft servoelastic response. Servoelastic responses are generated for symmetric control surface excitation, antisymmetric control surface excitation and for rudder excitation. To illustrate the model updation approach, initial and improved test analysis correlation of aircraft responses for a generic flexible airvehicle are presented. The lateral servoelastic responses arising from an antisymmetric wing control surface excitation, namely the wing antisymmetric bending, lateral acceleration and roll rate responses are shown. The servoelastic responses for a new external store are also computed and validated with test data.