Paulo Henriques Iscold Andrade de Oliveira

Development of a Light Aircraft Flight Test Equipment

This paper presents the research efforts of the Center of Aeronautical Studies of the Federal University of Minas Gerais – Brazil to develop a flight test data acquisition system for light aircraft and unmanned aerial vehicles (CEA-FDAS). The main topics regard the system architecture and the interesting results presented by the system in applications such as performance evaluation and stability and control derivatives estimation problems. Finally, the most important conclusion is that this system can efficiently support the demands of the aerospace industry for light aircraft and unmanned aerial vehicles development programs as well as the necessities of the research centers and universities developing aeronautical research and didactic programs.

Aerodynamic and Performance Analysis of Representatives of One Century of Low Speed Aircraft

This work presents a comparative study of aerodynamic and performance characteristics of relevant examples of low speed aircraft that have been built and flown between 1890 and 1990. As speed is related to aircraft mass and wing loading and power, the aircraft analyzed present low weight, low wing loading and low power. To generate this study a set of tools have been developed, which are specifically aimed to slow and light aircraft. One additional goal of the study is to obtain a consistent reference data basis - by using the developed tools to analyze existing aircraft - prior to use these tools in new designs with the features of low speed, low wing loading and low power.

Aspects of the Application of a Three Dimensional Panel Method Tool in the Design of a Light Aircraft

This paper presents the computer implementation process of the Panel Method for aerodynamic analysis of three dimensional bodies with or without lift. The computer implementation consists in the creation of pre and post processing environments and a solver for the solution of the problem in external flow potential over three dimensional bodies with and without lift. For cases in which there’s no lift, a constant distribution of sources over the body (fusaleges, farings, etc.) is used, their intensities calculated in order to guarantee impermeability of the body. For cases in which there is lift, a constant distribution of sources and doublets are used on the body (wings, tails, etc.). The intensity of the sources is solved in the same manner as cases with no lift. Intensity of doublets is solved in order to satisfy the equality condition regarding pressure on the under and upper side of the trailing edge (Kutta Condition) of the body without lift. An analysis of the aircraft CEA308 is shown in order to illustrate the use of the developed program in light aircraft projects.

Flight Path Optimization for Competition Sailplanes through State Variables Parameterization

This paper presents a numerical process for determining optimal flight paths for competition soaring. The goal is reduction of flight time required to fly towards an ascending thermal and climb to a given altitude. The optimization procedure applies a direct method to obtain sub-optimal solutions through parameterization of state variables, unlike a previous study by the same authors which was based on control parameterization. A mathematical programming procedure is used to determine the sub-optimal values for the parameterized state variables. The optimal control law, which is necessary for the generation of the sub-optimal state, is obtained through a step-by-step penalty technique. The results demonstrate that the optimization of transitory phases is important for the minimization of total flight time.