DSpace Collection:https://repositorio.ufu.br/handle/123456789/192342026-10-14T16:52:09Z2026-10-14T16:52:09ZComparative study of aerodynamic models for aeroelastic flutter prediction and dynamic stallhttps://repositorio.ufu.br/handle/123456789/504572026-09-26T06:17:41Z2026-03-24T00:00:00ZTitle: Comparative study of aerodynamic models for aeroelastic flutter prediction and dynamic stall
Abstract: The present work reviews and compares the main methods for modeling bidimensional aeroelastic
flutter, with particular focus on different aerodynamic formulations and their ability to represent
dynamic stall effects. The objective is to provide a comparative view of these methods, serving
as an auxiliary set of tools for estimating and predicting experimental results, especially in the
context of research aeroelastic tests.
Simpler attached-flow formulations, namely quasi-steady and unsteady models, are first investi
gated, followed by more advanced semi-empirical dynamic stall models, namely the ONERA
and Leishman–Beddoes formulations. All models are numerically implemented in MATLAB
and analysed through comparison with a reference experimental case from the literature.
By identifying the main characteristics, advantages, and limitations of each approach, it is
concluded that, among the attached-flow methods, the unsteady Wagner aerodynamic model
provides more accurate predictions than the quasi-steady formulation, since flutter is inherently
a high-frequency dynamic phenomenon. Among the semi-empirical models with dynamic stall
representation, the Leishman–Beddoes method yields the most satisfactory results, mainly due
to the previously validated calibration of its aerodynamic parameters.2026-03-24T00:00:00ZDesenvolvimento de um sistema de controle e guiamento para entrega por paraquedashttps://repositorio.ufu.br/handle/123456789/501082026-09-04T06:31:36Z2026-08-06T00:00:00ZTitle: Desenvolvimento de um sistema de controle e guiamento para entrega por paraquedas
Abstract: The aim of this work is to develop control and guidance for Precision Aerial Delivery Systems
(PADS). To this end, a dynamic model with six degrees of freedom is developed, and based on
its linearization, a state-feedback controller is designed using the Linear Quadratic Regulator
(LQR) methodology. In addition, a Go-to-Target heuristic is employed to determine the direction
that will lead the parachute to the desired target. Thus, the control system performs lateral and
longitudinal control of the parachute in order to follow the orientation defined by the heuristic.
The influence of the controller parameters on system performance is also analyzed, as well as its
behavior under different operating conditions, including the presence and absence of wind.
The simulation results demonstrate that the proposed strategy is capable of autonomously guiding
the parachute to the vicinity of the desired impact point, offering satisfactory performance
combined with simplicity of implementation. However, the approach has limitations related to
the heuristic employed, as it is not capable of landing exactly on the target, since it does not
constitute a position controller per se. Thus, the development of more sophisticated control
strategies is identified as a possibility for future work.2026-08-06T00:00:00ZArtificial neural networks for critical flutter speed prediction in semi-span flat-plate wings with geometric variationshttps://repositorio.ufu.br/handle/123456789/490392026-07-25T06:27:15Z2025-09-30T00:00:00ZTitle: Artificial neural networks for critical flutter speed prediction in semi-span flat-plate wings with geometric variations2025-09-30T00:00:00ZEstudo do comportamento termomecânico de ferramentais de montagem de estruturas aeronáuticashttps://repositorio.ufu.br/handle/123456789/479472025-12-30T06:18:13Z2025-11-06T00:00:00ZTitle: Estudo do comportamento termomecânico de ferramentais de montagem de estruturas aeronáuticas
Abstract: The present work investigates the thermomechanical behavior of assembly tooling for flight critical components, focusing on control surfaces and the effects of thermal expansion on
product tolerances. The analysis carried out is extremely useful for assembly processes located
in thermally uncontrolled environments. Temperature measurements were performed on the
assembly jigs of control surfaces from two aircraft during two hot days, including ambient
and ceiling temperatures in the hangar where these tools were located. Structural models were
developed to perform finite element analyses (FEA), revealing significant displacements in the
vertical and transverse directions, directly impacting hinge tolerances and causing assembly
delays in the absence of corrective shims. To generalize the analysis, a thermal model based
on the Lumped Capacitance Method (LCM) was created to estimate surface temperatures from
environmental conditions. The model showed an average error below 10%, and the subsequent
structural analyses confirmed the displacement results with a low error and differences between
the built models around 0.06 mm, validating the methodology for future evaluations in assembly
processes.2025-11-06T00:00:00Z