Abrams, Camden W has requested to schedule their MS Thesis Proposal. This request has been approved by their faculty advisor, the AE Associate Chair for Graduate Programs, and the AE Communications Office. Please proceed to post the annoucement on the OGE website. The details are as follows:

Student Name: Camden Abrams

Advisor: Dr. Cristina Riso

Milestone: MS Thesis Proposal

Degree Program: Aerospace Engineering

Title: Output-Based Limit-Cycle Oscillation Prediction in Aeroelastic Systems with Multiple Structural Nonlinearities and Noise

Abstract: Current trends in aircraft design are increasingly moving towards lightweight and unconventional configurations for higher energy efficiency. In these concepts, flutter is a critical design concern that must be addressed early in the development phase while accounting for disparate sources of nonlinear behavior. Traditional methods for flutter prediction are typically either based on linear assumptions or are computationally expensive and inefficient for iterative design or optimization. A recently proposed method for predicting limit cycle oscillations induced by freeplay nonlinearity offers a potential solution to this problem. The method uses output-data from free-decay time histories prior to the onset of instability to estimate recovery rates to equilibrium following perturbations, which are then used to simultaneously estimate both flutter and limit-cycle oscillation boundaries. This thesis explores three questions to advance the proposed method: How do different forms of structural nonlinearity affect the accuracy of LCO prediction? What level of signal noise may the method tolerate before accuracy critically degrades? Can LCOs due to freeplay be accurately predicted and characterized for models with more complex dynamics? To answer these questions, several studies are proposed. First, the method is applied to cases of polynomial stiffness and combined freeplay-polynomial nonlinearity in a two-degree-of-freedom propeller-nacelle model and compared with alternative methods. Then, predictions are performed for increasing levels of simulated noise. Finally, two additional models are considered, a four-degree-of-freedom propeller-nacelle-wing and five-degree-of-freedom propeller-nacelle-wing-control surface model, with various forms of freeplay nonlinearity. The contributions of this thesis have the potential to improve the prediction of limit cycle oscillations in early design phases for nonlinear aeroelastic systems. 

Date and time: 2026-05-28, 1:00pm

Location: W200

Committee:
Dr. Cristina Riso (advisor), School of Aerospace Engineering
Dr. Keegan Moore, School of Aerospace Engineering
Dr. Graeme J. Kennedy, School of Aerospace Engineering