Stuttgart, Universiẗat, Diss., 2000 (Nicht für den Austausch).

Zugl.: Köln, Rheinische Fachhochsch. (RFH), Diplomarbeit, 2006.

ITC/USA 2014 Conference Proceedings / The Fiftieth Annual International Telemetering Conference and Technical Exhibition / October 20-23, 2014 / Town and Country Resort & Convention Center, San Diego, CA / Airbus is authorized to use S-band for Telemetry transmission until 2015. In October 2011, the decision was taken to move to C-band in 2013, to cope with Airbus development aircraft planning. The objective was a real challenge for 2 main reasons: C-band channel was not characterized in Airbus transmission environment and it was necessary to validate the propagation performance for Flight Tests uses. The selected solution is based on Coded Orthogonal Frequency Division Multiplexing (COFDM) modulation. There was no existing solution so it has led the Airbus Test Centre to drive the development of its own C Band solution. C-band telemetry at Airbus has been tested and evaluated in flight from April 2012. The first goal was to check the coverage and the impact of the bad weather condition. Besides, it was necessary to characterize the channel to choose the optimised parameters for the waveform in the Toulouse Blagnac environment. This selection of parameters allows the high quality and increased data rate required for Airbus Telemetry to be reached. The test results consolidated the choice of a COFDM modulation, when given the high sensitivity to multipath of usual Frequency Modulation in the airport environment full of buildings and aircrafts. Moreover, it has been possible to reach a similar quality to the S-band telemetry systems, thanks to a fine tuning of the waveform parameters, and tracking system. Deployment of the system by modifying 8 reception antennas and 12 development aircrafts was done over a span of 4 weeks in January 2014. No impact on Airbus A350 certification campaign occurred due to close collaboration with Flight Test Operations. The new Telemetry system enables an increase of telemetry capabilities in the future, especially the data throughput, simplified remote control and monitoring. This experience is an opportunity to set up a new standard.

Passau, Univ., Diss., 2008.

Berlin, Freie Universiẗat, Diss., 2000. / Dateiformat: zip, Dateien im PDF-Format.

Reliability and redundancy of safety-critical network systems is a paramount issue in system engineering. Be it in evaluating existing network systems or solving optimization problems for designing network systems, it is important to consider reliability and redundancy. This dissertation is in collaboration with AIRBUS Group, France, and they are very interest in the optimal design of safety-critical aircraft architecture systems which have to consider reliability and redundancy. To address the problem of optimally designing such systems, we chose to focus on one specific aircraft architecture system the door management system. It checks if all doors are properly closed and the cabin has the correct pressure. It is a safety-critical system since it is part of the pressurization system of an aircraft. To optimally design the DMS while considering reliability, a suitable reliability evaluation algorithm is necessary. In this dissertation, we begin by proposing a suitable reliability evaluation algorithm for a type of non series-parallel network system which includes the DMS and which can be used in an optimization model. The reliability evaluation algorithm is based on a simplification of the probability principle of inclusion-exclusion formula for intersections of unions. The simplification exploits the presence of many repeated events and has many fewer terms, which significantly reduces the number of operations needed. We compare its computational efficiency against the sum of disjoint products method KDH88 for a simple artificial example and for the DMS. Afterwards, we introduce the first MILP model for the DMS with k-redundancy. As the model is too difficult to be solved efficiently by standard MILP solvers, we discuss the issues of solving the model with general solving methods such as branch-and-bound and branch-and-price. We introduce specialized branching rules and new heuristics to solve the DMS problem with k-redundancy more efficiently and show results of computational tests which compare the specialized solving algorithms with general solving algorithms for example instances of the DMS problem. Lastly, we discuss the problems of considering reliability in MI(N)LP models for the DMS and how the new reliability evaluation algorithm can be used. In this discussion, we give different MI(N)LP models for the DMS problem with redundancy and reliability. Moreover, we propose a new heuristic for the DMS problem with redundancy and reliability. It is based on branch-and-bound, the Dantzig-Wolfe decomposition and on the new reliability evaluation algorithm. We show results of computational tests of the new heuristic for example instances of the DMS problem and discuss its validity.

<p>The objective with this thesis project was to with the simulations software Delmia make a working build philosophy for the new concept of the fixed leading edge for the Airbus A320 airliner, but also to make two conceptual fixtures in the modular framework BoxJoint for pre-drilling of two sub assemblies.</p><p> </p><p>Everything started with a study in Delmia to both recap on previous knowledge and to learn more about it. This was followed by early simulations on the new concepts that were provided by project partners. Then a study was made in the Affordable Reconfigurable tooling, ART-concept. A suggested build philosophy was created and possible areas for automation were identified. These areas were all the drilling and fettling operations except the drilling in the last stage where the pre-drilled holes are opened up. More investigations needs to be done to see if a robot can install and remove slave pins that are used in the last stage. Two conceptual designs on fixtures were created where one uses two industrial robots with vision systems to get the correct accuracy when drilling the product. The other was build to be able to use a Tau-Gantry robot solution together with a vision system.</p>

The objective with this thesis project was to with the simulations software Delmia make a working build philosophy for the new concept of the fixed leading edge for the Airbus A320 airliner, but also to make two conceptual fixtures in the modular framework BoxJoint for pre-drilling of two sub assemblies.   Everything started with a study in Delmia to both recap on previous knowledge and to learn more about it. This was followed by early simulations on the new concepts that were provided by project partners. Then a study was made in the Affordable Reconfigurable tooling, ART-concept. A suggested build philosophy was created and possible areas for automation were identified. These areas were all the drilling and fettling operations except the drilling in the last stage where the pre-drilled holes are opened up. More investigations needs to be done to see if a robot can install and remove slave pins that are used in the last stage. Two conceptual designs on fixtures were created where one uses two industrial robots with vision systems to get the correct accuracy when drilling the product. The other was build to be able to use a Tau-Gantry robot solution together with a vision system.

Air inlets in some form are used on all commercial airliners today. The type of air inlet investigated in this report is a NACA inlet submerged into a surface. This surface is within this thesis a test section wall of a wind tunnel. The considered wind tunnel is TWG in Göttingen (Germany) that operates in transonic speeds. Submerged inlets have the main advantage of low aeroynamic drag from the inlet itself. The importance of reducing drag, and the attention given to this subject is increasing as fuel prices rise as well as public awareness of environmental impact by all of us. The outcome of this thesis contributes to the government-funded project ECOCENTS which deals with the design of innovative new aircraft cooling systems and the detailed flow analysis of these systems. This thesis was carried out at the company Airbus in Bremen, Germany. The main objective of this report was the evaluation of the ram pressure efficiency of four different ramp angles of a NACA inlet and the estimation of the drag caused by these geometries with the use of Computational Fluid Dynamics (CFD). The flow solver used was TAU, a Reynolds-Averaged Navier-Stokes (RANS) solver developed by the German Aerospace Center (DLR). The inlet consisted of one ramp section where the ramp angle was fixed at 7 degrees, and a second variable ramp section. The following different angles were investigated: 4, 7, 10 and 15 degrees. These configurations were evaluated at a velocity of Mach 0.8 and a Reynolds number of 10*10^6. The ramp angle of 7 degrees was evaluated at two additional velocities (Mach 0.73 and Mach 0.87) and at two additional Reynolds numbers (5*10^6 and 15*10^6) at Mach 0.8. The inlet efficiency outcome of this study was located between two other investigations. The results of this RANS computation predicted a higher total pressure at the inlet throat plane compared to a previous CFD investigation where a different RANS solver at the same geometry was used. In comparison to an estimation method mainly based on experimental data (ESDU method), the recent study showed a lower total pressure at the inlet throat plane. The aerodynamic drag that arised by the presence of the inlet system was calculated within this thesis to be higher than the outcome of the experimental data based (ESDU) method. The advantage of using a NACA type inlet was observed to be highly related to the ramp angle. Vortices are originated and develop along the edges of the intake ramp walls. These two vortices help to transport higher energy flow from the free stream into the inlet and therefore reduce the boundary layer thickness in the inlet region. For lower mass flows (0.10 - 0.20 kg/s) a ramp angle of 7 degrees was seen to be prefered in view of ram pressure efficiency. At a higher mass flow (0.25 kg/s) the 10 degrees ramp angle was prefered, followed by the 15 degrees ramp angle at the highest investigated mass flows (0.30 - 0.35 kg/s). In view of drag, the lowest ramp angle possible for a given mass flow was seen to be most advantagous. Future work on this subject will include simulation of an inlet in combination with a heat exchanger and a ram air outlet. This arrengement will be the same as in the investigation at the TWG test campaign and therefore comparable. The difference in outcome of the separate CFD analysis was discussed within this investigation but could not be completely cleared.

The aviation industry has more than a hundred years in history in the United States. And the industry has always been one of the important projects to conduct of the country. The industry involves not only technology, capitals but also politics. In order to maintain the influential power to the world, countries, especially the United States and Western Europe invest huge amount in this industry. However, under the globalization and high oil prices era, the industry encounters some difficulties to change. Outsourcing has become the solution for those manufacturers. The high growth of economic in Asia becomes another battle field for western countries to fight, especially in China. Chinese power is getting stronger; however, western countries concern about the special political backgrounds in China. Nevertheless, conducting business and finding cheap labor resource have been multinational companies¡¦ priority these days. The influential power of multinational companies and those parent countries become the major decision maker in the game. The Boeing Company has all the characteristics of these controversial issues. Chinese government, the Boeing Company, the rival Airbus and the U.S. government in the game would affect the industry.