Morphing aircraft offer many benefits. However, the design of stiff yet flexible structures still provides many obstacles to fully exploring and realizing morphing structures. Due to this, many morphing challenges remain open. Topology optimization is a type of structural optimization that optimizes the material layout of a structure based on imposed boundary conditions and load paths. This type of optimization is promising for solving morphing design challenges but many of the optimized structures are not suited for traditional manufacturing and material arrangements. Multi-material additive manufacturing is an emerging technology that can produce a single structure with many different materials integrated in custom geometries. This could be the solution to realizing topology optimized structures. Despite the rich amount of current research in morphing aircraft, many challenges still remain open and topology of morphing structures could provide the solution to these morphing challenges. / Master of Science / Morphing aircraft offer many benefits. However, the design of stiff yet flexible structures still provides many obstacles to fully exploring and realizing morphing structures. Due to this, many morphing challenges remain open. Topology optimization is a type of structural optimization that optimizes the material layout of a structure based on imposed boundary conditions and load paths. This type of optimization is promising for solving morphing design challenges but many of the optimized structures are not suited for traditional manufacturing and material arrangements. Multi-material additive manufacturing is an emerging technology that can produce a single structure with many different materials integrated in custom geometries. This could be the solution to realizing topology optimized structures. Despite the rich amount of current research in morphing aircraft, many challenges still remain open and topology of morphing structures could provide the solution to these morphing challenges.

MBA Professional Report / The goal of this MBA Project is to investigate possible disconnects between doctrine and practice in the employment of the Raven Small Unmanned Aerial Vehicle (SUAV). The Army's current Small UAV requirements are based upon the Future Combat System's Operations Requirements Document and has not been validated at the platoon or company level. The Raven SUAV is a Commercial off the Shelf (COTS) item that swiftly became the Army's Small UAV of choice for operations in Afghanistan and Iraq. Doctrine and Techniques, Tactics, and Procedures (TTP) have been written for the Raven SUAV; however, it is not standard practice for all units operating the system abroad. The last review of the SUAV operational requirements was conducted in 2003 but did not specifically address its usage on the battlefield. In an attempt to fill that gap, this project focuses on real-world usage of the Raven SUAV system. We compare doctrine versus practice using the Department of Defense's (DOD) Doctrine, Organization, Training, Material, Leadership, Personnel, Facilities (DOTML-PF) model as the primary logic construct. The report begins by providing a background of the Raven SUAV, to include its evolution from a COTS item to the Army's SUAV of choice, and how it has impacted the warfighter. Next, the authors provide an overview of DOTML-PF in order to provide a basis for comparing doctrine and practice. The study then looks in-depth at doctrine and practice using DOTML-PF as the model for revealing differences between the two. Finally, the authors analyze these differences and recommend solutions to mitigate shortfalls in actual Raven SUAV usage on the battlefield.--p. i.

ABSTRACT Developments in the field of microturbine technology and gas turbine driven aircraft has been progressing without much progress in light aircraft predominantly propelled by piston engines. Because of inhibitive maintenance and overhaul costs of such however, propulsion via a gas turbine engine has been proposed with the potential of eventually replacing current engine configurations. Subsequently, the objective was to conceptually design a replacement gas turbine engine in the 150 kW range. A selection of case studies was used to illustrate the changing technologies to illustrate the technological viability of micro-gas turbines for light aircraft. Advantages and disadvantages of both engine types were discussed and a concise description of gas turbine operations and its components was given. A brief overview of fundamentals as well as the transmission layout was also supplied. Three configurations were isolated, namely the single spool design, a twin spool design featuring a free power turbine and the effect of a fuel conserving recuperator. Calculations were performed using Microsoft Excel, which proved sufficient in effectively calculating complex formulae - even under the necessary iterative feed-back conditions the design process demanded. Eventually, variable-specific design criteria were derived regarding the three engine types. Because fuel consumption still proved inhibitive, the effect of recuperation was investigated which yielded a very competitive engine - should the possibility of recuperator technology exist on time. As a result, one particular recuperated, single spool gas turbine engine was successfully identified. Having met all the design criteria sufficiently, this preliminary prototype design was numerically described and put within context of principal, peripheral working components such as a compatible gearbox layout.

No description available.

Thesis (M. S.)--Aerospace Engineering, Georgia Institute of Technology, 2010. / Committee Chair: Hodges, Dewey; Committee Member: Bauchau, Olivier; Committee Member: Sankar, Lakshmi. Part of the SMARTech Electronic Thesis and Dissertation Collection.

The Warsaw Convention of 1929, effective since February 13, 1933 (1), is the most widely accepted treaty on international commercial law. It was in force in eighty-two states as of January 10, 1966. (2) [...]

No description available.

Although the contracts of lease and leasing have been used for many years by airline companies, increase in traffic volume predicted for the following years will certainly determine a greater need for aircrafts and consequently a greater demand for use of these kind of contracts. / Not only do they offer economic benefits but they are also very important instruments in the hands of an airline for fleet planning. / Operating and financial lessors have a wide market for their costly "toys", but, as the market and profits expand, so does the need for lessors to be at any time able to keep total control of them. In fact, one of the biggest fears for a lessor is to loose his property because he is not able to repossess it after a default of the lessee. / This thesis first briefly overviews the contract of lease and leasing and how the latter, being a contract of common law origin, has been included in the legal systems of two civil law countries like Italy and Quebec. Subsequently, the main clauses of a contract of aircraft lease or leasing are analysed not only to see the duties that a lessee entering into such a contract has, but also to see if these clauses follow the provisions which govern the contract, in general, and the contract of lease and leasing, in particular, in Italy and Quebec. / Chapter II deals with the remedies that, in case of the lessee's default, a lessor has, in Italy and Quebec, in order to repossess his aircraft; whether these remedies can guarantee speedy repossession and whether the remedy of the "self-help repossession", which is a typical common law legal instrument, can be applied in Italy and Quebec. / Finally there is a short analysis of the "Convention on International Interests in Mobile Equipment" which is being drafted by Unidroit and its possible help in solving the problem of quick repossession in the case of a default by the lessee.

Thesis (M.S.)--California Polytechnic State University, 2009. / Title from PDF title page; viewed on August 3, 2009. Major professor: Daniel Biezad, Ph.D. "Presented to the faculty of California Polytechnic State University, San Luis Obispo." "In partial fulfillment of the requirements for the degree of Master of Science in Aerospace Engineering." "May 2009." Includes bibliographical references (p. 90-91). Also available on microfiche.

Thesis (M.S.)--Brigham Young University. Dept. of Mechanical Engineering, 2007. / Includes bibliographical references (p. 127-130).