An experimental investigation on active aeroelastic aircraft structures with bending-torsion coupling properties is presented. Two techniques for vibration and flutter alleviation are studied and tested. The passive approach is based on the use of carbon composite spars with misaligned fibres. The second technique involves an active spar with a multi-cross section embedded with PZT actuators. A wing was designed and manufactured for testing in a wind tunnel and subsequently implemented on a demonstrator platform for flight testing. Results show that a carefully designed misalignment of the fibres can lead to significant performance increase. The active system based on PZT actuators with a linear controller exhibits significant improvements in aeroelastic performance compared to the passive system. The research findings lead to the conclusion that significant vibration reduction and flutter envelope extension can be achieved using the proposed strategies.

Thesis (M.A.)--University of Wisconsin--Madison, 2000. / Typescript. eContent provider-neutral record in process. Description based on print version record. Includes bibliographical references (leaves 53-57).

The purpose of this paper is to describe the mechanization of the basic equations of motion for the performance and maneuver characteristics of an airplane with some simplifications which render solutions more practicable. The results of a study made to program these equations for calculation by the IBM MODEL 650 digital computer are presented as well as the steps to be taken in using this method of calculation.

This paper gives the derivation of a method for determining the forces to be applied to these points which will simulate the load distributed over all the airplane.

This paper is an extension of various projects that the writer has been associated with at Chance Vought Aircraft, Incorporated.

Topic of this diploma thesis is design of delivery drone. This thesis deals with the current situation of the market in design and technical aspects. The main goal is create an original design characteristic in shape and technical ways.

This work describes the creation of detailed FEM models of the selected area. Primarily is focused on the process of creating a detailed FEM model of the part of airplane using the static condensation. This work also contains a description of the process stress analysis of part of the fuselage of the airplane EV-55 Outback.

Every year there are thousands of aviation accidents along with hundreds of human deaths that happen around the world. While the data is sparse, it is well documented that many of these happen from emergency landings gone awry. While pilots can generally make great landings in clear daytime conditions, they are significantly handicapped when it comes to landing at night or amongst poor visibility conditions. Due to the nature of this problem and some of the large scale advances in software technology we propose a solution that provides a significant improvement from the status quo. Using transfer learning on neural networks to classify satellite images along with terrain elevation data from the USGS we are able to recreate maps that can readily direct pilots to locations that are relatively flat and lack structures or vegetation. Using San Luis Obispo as our data set we confirmed that we could correctly classify at least 93\% of landable terrain and then identified areas within that area that could safely be used to land a plane. We then transfer this data into a 3D rendering program that allows us to visualize what is happening. In additional to visualizing where the landing paths are we also create a landing algorithm that demonstrates how the plane will maintain its current glide path and navigate to a successful landing while avoiding obstacles.

This work's objective is to create a type design of a new commuter class airplane according to CS-23 certification specifications. The design will take under account the EV-55 design to reduce the number of new parts and subassemblies. Part of this thesis are mass balance of the new design, basic airplane dimensions and fuselage dimensions estimates. The critical crossection of the fuselage is analyzed (stress analysis) and the system drawings is worked out.

The goal of the submitted Diploma Thesis is to select power units for VUT 200, twin-engine variant of aircraft VUT 100. The Diploma Thesis consists of analysis of power units, mass analysis, design of the structural changes of default aircraft, aerodynamic characteristics, performance and flight characteristics.