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Begonnen: Projekte, Bachelor- und Masterarbeiten

item 1. Prüfer: Prof. Dr.-Ing. Dieter Scholz, MSME

Name Thema Aufgabenstellung Typ der Arbeit In-/Ausland
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Anmeldedatum
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Abgabedatum
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Geheim VH
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Tutor
Mehria Noory Wartungskosten von Passagierflugzeugen bei unterschiedlicher Anzahl an Triebwerken berechnet nach DOC-Methoden Ein Passagierflugzeug(-entwurf) benötigt einen bestimmten Schub, der auf 2, 3 oder 4 Triebwerke aufgeteilt werden kann. Wir sehen heute, dass Entwürfe mit 3 oder 4 Triebwerken am Markt kaum noch eine Chance haben. Woran liegt das? Es handelt sich hier um eine Fragestellung, die den Flugzeugentwurf ganzheitlich betrifft (Kraftstoffverbrauch, Nullwiderstand der Triebwerksgondeln, Masse der Triebwerke und damit eine Änderung des induzierten Widerstands). Ein Hauptgrund für den Trend zu zwei Triebwerken sind aber vermutlich die Wartungskosten, die bei mehreren kleinen Triebwerken höher sind als bei zwei großen Triebwerken. Diese Arbeit legt den Schwerpunkt auf die Wartungskosten und geht der Vermutung auf den Grund gehen. Dazu stehen recht einfache Formeln zur Abschätzung der Wartungskosten aus den DOC-Methoden zur Verfügung. Zu nennen sind hier: ATA 1967, AA 1980, DLH 1982, AEA 1989, AI 1989 (alle @ AERO verfügbar). Weitere Gleichungen gibt es aus der Literatur zum Flugzeugentwurf von Raymer und Jenkinson. Einlesen kann man sich mit http://www.fzt.haw-hamburg.de/pers/Scholz/skriptFEs/skriptFE14.pdf (User: student; PW: ?). Als aktuelle Weiterführung der Überlegung: Wie würde sich die Situation ändern, wenn statt derzeit genutzter Turbofan- oder Turboproptriebwerke Elektromotore mit Propellern zum Einsatz kämen? Hier denkt man an eine hohe Anzahl der Antriebe (20 und mehr). Es geht also um hybrid-elektrische Antriebe für Passagierflugzeuge (siehe oben). Bachelorarbeit Inland WS17/18
?
?
? nein N-V DS
Moritz Grieb Ein Vergleich von Klimarechnern zur Ermittlung des CO2-Fußabdrucks und der Emissionen individueller Flugreisen
Im Fokus: Berechnungsmethoden zur Schadstoffmenge und zur Höhe der Kompensationsspende
Welche Eingangsdaten verlangt der Klimarechner? Was wird berechnet (CO2, weitere Schadstoffe, CO2-Äquivalente)? Wie lauten die Formeln zur Berechnung? Werden die Auswirkungen der Flughöhe berücksichtigt? Wieviel kostet die Kompensation einer Tonne CO2(-Äquivalente)? Starten Sie mit einer Literaturrecherche! Wieviel Sinn macht CO2-Kompensation? Welche Klimarechner gibt es im WWW? Grobbewertung der Klimarechner! Auswahl von Klimarechnern für die Vergleichsstudie! Testszenario, Test, Auswertung!

http://sustainability.tufts.edu/get-involved/green-guide/flying http://www.co2offsetresearch.org/aviation/index.html http://www.co2offsetresearch.org/aviation/AirtravelLinks.html https://www.welt.de/wirtschaft/article2179351 https://www.atmosfair.de/portal/documents/10184/31806/VZBV_Studie_Eberswalde.pdf

http://www.icao.int/ENVIRONMENTAL-PROTECTION/CarbonOffset/Pages/default.aspx
Documented here:
http://www.icao.int/environmental-protection/CarbonOffset/Documents/Methodology_ICAO_Carbon_Calculator_v9_2016.pdf
Appendix C: Interesting Aircraft Fuel Data that could be evaluated!

Projekt im Master Inland SS17
17.03.17
Helios
V 01.10.17 nein J DS
Alex Gindorf Proposing a Classification for Aeronautics, Astronautics, and Aerospace Sciences Classifications - the heart of science. Examples of classifications: DDC, ICD-10, ... Standards for creating classifications. For the task here, please have a look at this: A first idea to get started. What else exists in our field? Project Inland SS17
17.03.17
Helios
17.10.17 nein J DS
Jascha McDavid Empennage Sizing - The Tail Lever Arm as a Percentage of Fuselage Length Determined from Statistics *.pdf

We investigated the Tail Volume Coefficient already well (see Technical Note Ch. 2.5.2 and 3.1). What we need next is an evaluation and estimation of the lever arm measured from the wing to the tail in preliminary aircraft design. The lever arm is a percentage of the fuselage length. First hints are given in the lecture notes "Aircraft Design", Chapter 9. We need to rework the topic in more detail.

Project Inland SS17
25.04.17
Helios
25.10.17 nein J DS
Marcus Burzlaff The Fuel Consumption of Extreme Long and Short Flights The average fuel consumption expressed in kg/100 km is relatively high for very long flights, but also for very short flights. Plotting the fuel consumption of the aircraft versus flight distance we expect to get a typical "bath tub curve". Plotting the fuel consumption per passenger versus flight distance has to take the number of passengers on board into account which is decreasing with increasing range. Input to these calculations requires knowledge of the aircraft's mass, aerodynamics and specific fuel consumption of the engines. Since not all of this is in the public domain, methods have to be found how to extract the data from published payload range diagrams. Project Inland SS17
13.05.17
Helios
13.11.17
Work will start WS17/18
nein J DS
Marcel Mutschall Die Genauigkeit einer vereinfachte Berechnung der Steigzeit von Flugzeugen Eine vereinfachte Berechnung der Steigzeit ergibt sich, wenn man eine lineare Abnahme der Steiggeschwindigkeit mit der Höhe annimmt. Wie verläuft die Abnahme der Steiggeschwindigkeit über der Höhe wirklich? Wie groß sind die Abweichungen gegenüber einer genaueren Rechnung? Grundlagen findet man in meiner Vorlesung "Flugmechanik" (Tafelbilder bzw. Skript). Projekt Inland SS17
26.05.17
Helios
26.11.17 nein J DS
Moritz Schuldt Der zivile Flugzeugbau im Umschwung - Eine Analyse des Weltmarktes Lange Zeit beherrschten der europaische Flugzeughersteller Airbus und der US amerikanische Flugzeughersteller Boeing als Duopol den Weltmarkt fur zivile Schmalrumpf- und Grßraumflugzeug. Mit dem Entwicklungsbeginn verschiedener Flugzeugtypen, wie bspw. dem Superjet 100 des russischen Flugzeugbauers Suchoi Civil Aircraft, dem MS21 des ebenfalls russischen Herstellers Irkut, den zwei Flugzeugtypen C919 und ARJ21 des chinesischen Flugzeugherstellers COMAC - Commercial Aircraft Corporation of China sowie dem Flugzeugtyp MRJ des japanischen Flugzeugherstellers Mitsubishi Aircraft Corporation sind auf dem Weltmarkt Produkte erschienen, die als direkte Konkurrenz den vielverkauften und als überaus betriebssicher und wirtschaftlich geltenden Schmalrumpfflugzeugen des Duopols gegenübergestellt werden sollen ... Projekt im Master Inland SS17
29.05.17
Helios
29.11.17 nein J DS
Arne Möller Verifying a Simple Method for Mental Arithmetic Converting CAS to TAS

Überprüfung einer einfachen Kopfrechenmethode zur Umrechnung von CAS in TAS

The method is used by pilots flying faster aircraft. The simple method is explained here
http://www.fzt.haw-hamburg.de/pers/Scholz/materialFM1/1-19.JPG (unten)
The correct calculation is shown here to work well (as far as this one example is concerned):
http://www.fzt.haw-hamburg.de/pers/Scholz/materialFM1/1-20.JPG
Prove with varying input parameters and/or with some kind of prove that the method has general validity.
Projekt Inland SS17
10.07.17
Helios
10.01.18 nein N-H DS

 

Die folgenden Arbeiten wurden bereits abgegeben
eine Aufarbeitung zur Veröffentlichung im Netz steht aber noch aus!
Name Thema Aufgabenstellung Typ der Arbeit In-/Ausland
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Anmeldedatum
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Abgabedatum
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Geheim Bew.
*****
Tutor
Laura Salcedo Campoamor Calculating the Power of Wind Turbines with the Blade Element Momentum Theory A) Literature review of available free tools to calculated the aerodynamic power output of wind turbines. B) Programming of an Excel-based tool to estimate the aerodynamic power output of wind turbines with the Blade Element Momentum Theory (BEM) - allowing also for limited wind turbine optimization.

Please see also my (old, but still valid) student work on wind energy at Hannover University.

Master Thesis Ausland SS17
20.03.17
Helios
E-Mail, FSB
10.09.17 nein J DS
Emiel De Grave Case Studies in Aircraft Design Abstract: This thesis explains how the classified design parameters of existing passenger jets can be de-termined. The classified design parameters are; the maximum lift coefficient for landing and take-off, the maximum aerodynamic efficiency and the specific fuel consumption. The entire concept is based on the preliminary sizing of jet powered civil aeroplanes. This preliminary sizing is explained in detail because it is the foundation of the final result. The preliminary sizing is combined using reverse engineering which is not a strict method. Therefore, only the basics are explained. By applying reverse engineering on the preliminary sizing and aiming for the classified design parameters as output, formulas are deviated to calculate the maximum lift coefficients, the maximum aerodynamic efficiency and the specific fuel consumption. The goal is to calculate these parameters, using only aircraft specifications that are made public by the manufacturer. The calculations are complex with mutual relations, iterative processes and optimizations. Therefore, it is interesting to integrate everything in a tool. The tool is built in Microsoft Excel and explained in detail adding operating instructions. The program is executed for miscellaneous aeroplanes, supported with the necessary comments. Investigated aeroplanes are: Caravelle 10B (Sud-Aviation), Boeing 707-320C, BAe 146-200 (British Aerospance), A320-200 (Airbus), 'Rebel' (based on A320), Boeing SUGAR High, Boeing 747-400, Blended Wing Body VELA 2 (VELA) and Dassault Falcon 8X. Master Thesis Ausland SS17
20.03.17
Helios
E-Mail, FSB
10.09.17 nein J DS
Lynn Van Endert Definition of an Ecolabel for Aircraft Abstract: In attempting to increase the environmental awareness in the aviation sector and to eliminate the green washing phenomenon, an investigation was done into the development and definition of an ecolabel for aircraft. Based on life cycle assessment it was found that aviation affects the environment most with the impact categories resource depletion and global warming (both due to fuel consumption), local air pollution (due to the nitrogen oxide emissions in the vicinity of airports) and noise pollution. For each impact category a calculation method was developed based solely on official, certified and publicly available data to meet the stated requirements of the ISO standards about environmental labeling. To ensure that every parameter is evaluated independent on aircraft size, which allows comparison between different aircraft, normalizing factors such as number of seats, rated thrust and noise level limits are used. Additionally, a travel class weighting factor is derived in order to account for the space occupied per seat in first class, business class and economy class. To finalize the ecolabel, the overall environmental impact is determined by weighting the contribution of each impact category. For each category a rating scale from A to G is developed to compare the performance of the aircraft with that of others. The harmonization of the scientific and environmental information, presented in an easy understandable label, enables the traveling customers to make a well informed and educated choice when booking a flight, selecting among airline offers with different types of aircraft and seating arrangements. Master Thesis Ausland SS17
20.03.17
Helios
E-Mail, FSB
10.09.17 nein J DS
Nicolai Lützen,
Amine Bahrani
Aerodynamic Investigation of C-Wings with Tornado Tornado is a vortex lattice method implemented in Matlab. It is used here to calculate the lift distribution especially on the upper horizontal part of the C-wing to understand the concept. Tornado is also used to calculate the induced drag of C-wings of different shapes (in comparison to the reference wing without a wing tip device). Aim is to confirm or correct the handbook method as given in the paper Estimating the Oswald Factor from Basic Aircraft Geometrical Parameters. Project Inland WS16/17
09.10.16/26.10.16
Helios
V 12.07.17 nein J DS
David Schubert Wirtschaftlichkeit eines Airbus A380 mit neuen Triebwerken Airbus considers launching an A380neo. With a classical design study, we look at how parameters will match up. Project Inland WS16/17
22.09.16
Helios
V 22.05.17 nein N DS
Rachna Harsh Creating Interactive Elements for an "Aircraft Design" "Open Educational Resource" (OER) This is the Aircraft Design OER. It includes this interactive element Task was to design more interactive elements for the Aircraft Design OER with H5P like drag-the-words, fill-in-the-blanks, image-hotspot-question, mark-the-words, multichoice, personality-quiz or questionnaire (to let user design aircraft), question-set(!!!), single-choice-set, summary, true-false or maybe even an interactive-video. Idea: Activate students with design activities and interactive questions so that learning is even more fun.

The results of this project can now be found here.

Bachelor Thesis Ausland SS17
20.03.17
Helios
E-Mail, FSB
03.09.17 nein J DS
Peter Löwen,
Marco Krause
Publishing a Dataset with Aircraft Parameters in a Data Repository Research data should be stored in a data repository. See also this picture. We will look at various repositories like the Harvard Dataverse Network. We will then accumulate aircraft data from many sources on the Internet. On such source is Jenkinson's Dataset. Eventually we will make our dataset available to the world in a professional way according to current standards. Team Project Inland Krause:
WS15/16
??.??.??
Helios

Löwen:
WS16/17
27.09.16
Helios

27.03.17 nein J DS
Lennart Hildebrandt,
Nemo Juchmann
Analyse der Flugdynamik in den Flugsimulatoren FSX und X-Plane Vergleich von realen flugdynamischen Eigenschaften ausgewählter Flugzeugmuster (selbst erflogen oder aus Tabellen) mit den aus herkömmlichen Flugsimulatoren (FSX, X-Plane 10) erflogenen Eigenschaften. Dies soll erste Hinweise geben auf die Güte dieser Flugsimulatoren. Projekt im Team Inland SS16
05./06.04.16
Helios
V: 24.11.16 nein J DS
Finn Wulbrand Fuel Consumption during Extreme Long and Short Flights The average fuel consumption expressed in kg/100 km is relatively high for very long flights, but also for very short flights. Plotting fuel consumption versus flight distance we expect to get a typical "bath tub curve". This curve should be analyzed and discussed. Project Inland 4.0-Bescheinigung
25.02.16
--- nein J DS
Alexander Broer Verbesserung des aerodynamischen Modells zur Berechnung von Böenlasten auf Passagierflugzeuge Bestandteil der BA Bachelor Arbeit Inland SS16
22.06.16
E-Mail, FSB
10.09.16 ja J DS
Wim Breugelmans Predicting Buffet Onset in Conceptual Aircraft Design A method to quickly compute the buffet envelope of a new aircraft geometry is given in the literature. The method is semi-empirical. It uses a combination of simple sweep theory and a buffet onset boundary of a given seed aircraft (alternatively, any other aircraft could be used as seed aircraft if the buffet onset boundary is available). Aim is to estimate the buffet onset boundary of a target geometry already at the conceptual design stage. The method should be described, programed in Excel, and applied. Wherever possible, the results should be compared with real aircraft characteristics. Master Thesis Ausland SS16
17.03.16
Helios
SS16 nein J DS
Kevin Catrysse Cruise Speed Reduction (CSR) - Aerodynamic, Flight Mechanic, and Economic Effects I have explained the basics here. Various of our studies show also Direct Operating Costs (DOC) reduction due to CSR. See how an optimized A320 could benefit in this dissertation. See also our publications about the slow flying Smart Turboprop: here and here. Authors looked also with more detail at the effects caused by CSR applied in the air transportation network e.g. here. Task is to make a full Internet review of CSR and to put all the arguments for and against CSR in a concise and logical sequence. Master Thesis Ausland SS16
17.03.16
Helios
SS16 nein J DS
Clara Simón García Aircraft Simulation and Analysis with HOPSAN-NG The simulation program HOPSAN in its new version (HOPSAN-NG) allows a wide range of simulations from the aircraft hydraulic system, via aircraft dynamics up to the simulation of a whole aircraft mission based on pre-defined way points. According to the developers (who will support us) this should allow an evaluation of the aircraft including its fuel consumption and many more other details. The task is to verify this claim and to judge HOPSAN for its suitability as an analysis tool in aircraft design. Bachelor Thesis Ausland SS16
17.03.16
Helios
SS16 nein J DS
Mia Eder G. Corning's Airplane Design Methodology As early as 1953 Gerald Corning, professor at the University of Maryland, devised a method for his students for the layout of subsonic passenger aircraft. Starting from requirements and ending at Direct Operating Costs. The method is given in his book Supersonic and subsonic airplane design (published by the author, in 1953 and 1960) in Chapter II. Task is to put the method in a clear and easy understandable sequence, to update some of the parameters to current technology levels, and to make the method available in form of a spreadsheet. Project Inland --- --- nein J DS
Karim Drews Bulk or Containerized Loading of Narrow-Body and Wide-Body Aircraft - What to Prefer? Airlines have the choice if they want to use container to load baggage or if suitcases are stored one by one in the cargo compartment. Cargo is mostly loaded in container. Smaller aircraft do not offer containerized loading. MD90 and Dash8 aircraft may operate with bulk baggage container. Wide-body aircraft use mostly the LD-3 type container. The narrow-body Airbus A320 can accommodate LD-3 container with reduced height. Hence some interline compatibility is offered between narrow- and wide-body aircraft. Container allow a quicker turn around of the aircraft leading to a higher utilization and potentially reducing Direct Operation Costs (DOC). Nevertheless, container add weight that reduces payload. Container require additional investment leading to depreciation and additional costs. In the end the preferred choice is a trade-off between depreciation, payload, and turn around time respectively turn around costs. See also: SKYbrary. This task may lead to an exchange of ideas with Etihad Airways. Project Inland --- --- nein J DS
Tim Haß Eco Lables for Aircraft *.pdf Bachelor Thesis Inland SS15
05.06.15
Helios
05.08.15 nein J DS
Johann Metzger Analyse des Sinkfluges von Germanwings 4U9525 I started with calculations of the Airbus A320's flight based only on a few points in time during the descent. A more detailed calculation will include more time steps, investigate more parameters (wind speed), and put everything in a comprehensive table. This table will be based on elementary data from FlightRadar24 or other available data at the time of writing. It will calculate depending parameters and compare these with published data. The result will be a set of parameters consistently describing the descent of 4U9525 also including parameters of the aircraft's aerodynamics and flight modes according to the autopilot logic and Fly-by-Wire flight control laws. Projekt Inland --- --- nein J DS
Aqib Khan Fuel Consumption during Extreme Long and Short Flights The average fuel consumption expressed in kg/100 km is relatively high for very long flights, but also for very short flights. Plotting fuel consumption versus flight distance we expect to get a typical "bath tub curve". This curve should be analyzed and discussed. Bachelor Thesis Ausland SS15
26.06.15?
E-Mail, Korn
07/15 nein J DS
Deepam Mishra Using OpenVSP for Aircraft Design OpenVSP is a tool from NASA. Task is to check OpenVSP Version 3.0 for new features and compatibility with OpenVSP Version 2.0. Advanced features should be used in trials as far as possible. Bachelor Thesis Ausland SS15
26.06.15?
E-Mail, Korn
07/15 nein J DS
Kinga Budziak Aerodynamic and Flight-Dynamic Analysis with Athena Vortex Lattice (AVL) The program Athena Vortex Lattice, AVL should be applied to calculate the induced drag of a box wing aircraft depending on the variation of selected parameters. AVL should also be tried out on the estimation of stability and control parameters. Project Ausland SS15
24.06.15
E-Mail, Korn
07/15 nein J DS
Raghu Nandan Singh Optimization of Very Light Aircraft (VLA) Summarize requirements for these aircraft form certification standards as they influence prelimianry aircraft design. Select an example aircraft from this class and optimize its design by modifying already existing software from the project SAS. Master Thesis Ausland SS15
24.06.15
E-Mail, Korn
07/15 nein J DS
Aday Pérez Reyes The Aviation Fuel and the Passenger Aircraft for the Future - Batteries Possibilities (or impossibilities) to operate an aircraft meeting requirements similar to an A320 with batteries and electrical motors. Master Thesis Ausland WS14/15
19.11.2014
E-Mail, Korn
02/2015 nein J DS
Leon Dib The Aviation Fuel and the Passenger Aircraft for the Future - Hydrogen Possibilities to operate an aircraft meeting requirements similar to an A320 with hydrogen Master Thesis Ausland WS14/15
19.11.2014
E-Mail, Korn
02/2015 nein J DS
Ramachandran Karunanidhi The Aviation Fuel and the Passenger Aircraft for the Future - Bio Fuel, Synthetic Fuel Analysis of the advantages and disadvantages of using alternative fuels in air transportation. Master Thesis Ausland WS14/15
19.11.2014
E-Mail, Korn
02/2015 nein J DS
Ramachandran Karunanidhi Aviation Fuel for the Future - Methane Hydrate Possibilities of using methane hydrate as the source of energy for air transportation. Project Ausland WS14/15
11/2014
Helios
05/2015 nein J DS
Tom Alisch Alternativen zur Hilfsgasturbine (APU) Die Option ohne APU zu fliegen generiert Vorteile beim Flugzeuggewicht und den Wartungskosten des Systems. Es bedeutet aber gleichfalls eine gesteigerte Abhängigkeit der Bodenversorgung mit Sekundärenergie. Projekt Inland WS14/15
21.10.14
Helios
21.04.15 nein J DS
Hairul Nahar Bin Nasir Empennage Sizing with the Tail Volume Coefficient - Basic Statistics Projektbericht wurde nicht abgegeben. Projekt Ausland WS14/15
18.11.14
E-Mail, Korn
18.05.15 nein J DS
Sayin, Aytac Empennage Sizing with the Tail Volume Coefficient - Basic Statistics Projektbericht wurde nicht abgegeben. Projekt Ausland WS14/15
19.11.2014
E-Mail, Korn
19.05.15 nein J DS
Muhamad Shafeez Shaharan Interactive Cabin and Fuselage Layout with PreSTo *.pdf Bachelor Thesis Inland WS14/15
23.10.2014
Helios
23.01.15 nein J DS
Joshua Brechlin Induced Drag of Box Wing Aircraft - Variation of Aspect Ratio, Sweep and Taper Ratio Projektbericht wurde nicht abgegeben. Projekt Inland WS13/14
03.12.13
11.07.14 V nein J DS
Veselin Pavlov Aircraft 3D-Modeling with OpenVSP-Connect NASA offers the tool Open Vehicle Sketch Pad (OpenVSP). OpenVSP-Connect from AERO at Hamburg University of Applied Sciences Hamburg is an interface tool between any Excel based aircraft design tool and OpenVSP. OpenVSP-Connect is an Excel based tool which uses Visual Basic Macros. It needs 46 aircraft (geometry) parameters in order to provide a 3D visualization of a designed aircraft. The software never asks for a parameter without suggesting one first or giving a value by default. First objective is to improve OpenVSP-Connect such that it can be used as a self-contained tool which estimates all necessary 46 parameters from an hand full of requirements to visualize an aircraft. Second objective is to show how to incorporate OpenVSP-Connect in any already existing tool chain. In this way OpenVSP-Connect should also provide the missing link between any other aircraft design tool made by the AERO, i.e. Aircraft Preliminary Sizing Tool (PreSTo) and OpenVSP. Project Ausland SS14
05.05.14
Helios
11.07.14 nein J DS
Maxime van Loo Aircraft Wing Design with the Open Software PreSTo *.pdf Master Thesis Ausland SS14
19.06.14
E-Mail, Korn
11.07.14 nein J DS
Johan Peterson An Optional APU for Passenger Aircraft *.pdf Project Ausland SS14
19.06.14
E-Mail, Korn
11.07.14 nein J DS
Sowmya Thyagarajan Mass Estimation with the LTH/DLR-Method The German Aerospace Center (DLR) has published a simple, parametric method in the German Aeronautical Handbook (Luftfahrt Technisches Handbuch - LTH) to estimate the mass of major aircraft components. The method is called: "Large Civil Jet Transport (MTOM > 40t), Statistical Mass Estimation, MA401". The project compares the method with the one given in "Torenbeek" with respect to approach and accuracy. Project Ausland SS14
19.06.14
E-Mail, Korn
11.07.14 nein J DS
Zubin Mistry Aircraft Design with VAMPzero Comment on the theory of the method and work an example. Download from http://vampzero.sourceforge.net Project Ausland SS14
19.06.14
E-Mail, Korn
07.07.14 nein J DS
Elena García Llorente Conceptual Design Optimization of Passenger Box Wing Aircraft in Biplane Layout *.pdf Master Thesis Ausland WS13/14
01.10.13
E-Mail, Korn
17.02.14 nein J AJ/DS
Mia Eder Parabelflüge mit Kleinflugzeugen *.pdf Projekt Inland SS13
27.03.13
23.12.13 VV nein J DS
Karim Drews Grundlagen zur Triebwerksintegration mit statistischen Betrachtungen *.pdf Projekt Inland SS13
21.03.13
05.01.14 VV nein J DS
Roberto Segovia García Turboprop Aircraft Design Optimization - Tool Development *.pdf Master Thesis Ausland SS13
30.08.13 nein J AJ/DS
Elien Verheire Systematic Evaluation of Alternative Box Wing Aircraft Configurations *.pdf
For visualisation:
Open VSP
Bachelor Thesis Ausland SS13 12.07.13 nein J PB/DS
Joeri Heinemann Preliminary Sizing - Part 25, Part 23, VLA and UL Aircraft *.pdf Master Thesis Ausland SS13 12.07.13 nein J DS
Martin Fekete Induced Drag of Box Wing Aircraft - Variation of Decalage and Vertical Separation *.pdf Project Ausland SS13 12.07.13 nein J RC/DS
Haider Riaz Induced Drag of Box Wing Aircraft - Variation of Dihedral --- Project Ausland SS13 12.07.13 nein J RC/DS
Benjamin Hochart Integraton of the Wing Module into the PreSTo Suite --- Project Ausland SS13 12.07.13 nein J RC/DS
Elena Behrendt Bodenabfertigung eines BWB --- Projekt --- --- 29.04.13 nein J DS
Michel Pinck Dimensionierung der Fenster und Frachttore von Passagierflugzeugen *.pdf Projekt --- --- 23.03.13 nein J DS
Luis Salord Losantos Estimating E_max for Turboprop Aircraft *.pdf Memo --- --- 13.07.12 nein J AJ
Hoa Ly Life-Cycle Assessment of Commercial Aircraft – A Review of Methods and Tools *.pdf Project --- --- 13.07.12
(22.09.12)
nein J AJ
Jeroen Verstraete Creating a Life-Cycle Assessment of an Aircraft *.pdf Project --- --- 13.07.12
(26.09.12)
nein J AJ
Nishant Bhanot Modeling of a Turboprop Driven Aircraft using PlaneMaker for Flight Simulation with X-Plane *.pdf Project --- --- 20.07.12 nein J AJ
Sameer Ahmed Family Concepts of Box Wing Aircraft *.pdf Project --- --- 10.08.12 nein J DaS
Ricardo Caja Calleja Flight Dynamics Analysis of a Medium Range Box Wing Aircraft *.pdf Master Thesis --- --- 30.06.12 nein J DaS
Ricardo Caja Calleja Flight Dynamics Model of a Box Wing Aircraft using JSBSim *.pdf Project --- --- 24.10.12 nein J DaS
Jeremy Bouten Using X-Plane for Analyzing Aircraft Performance *.pdf Project --- --- 13.07.12
(22.09.12)
nein J DaS
Tayfun Süle Programmierung einer Schnittstelle zwischen PreSTo and CATIA *.pdf Projekt --- --- 15.07.11 V nein J DS

* In-/Ausland:
Inland: Studierender ist regulär an der HAW Hamburg eingeschrieben.
Ausland: Studierender ist Gaststudent aus dem Ausland. Hier gibt es andere Abläufe im Fakultäts Service Büro (FSB).

** Anmeldedatum:
Projekte sind teilweise ohne Anmeldedatum in Helios. Anmeldedatum ist daher das Datum der E-Mail-Bestätigung von Frau Korn.

*** Abgabedatum:
Abgabe für Projekte ist 6 Monate nach Ausgabe des Themas von mir (nicht etwa 6 Monate nach Anmeldung in Helios). V: Termin unter Berücksichtigung der gewährten Verlängerung.
Abgabe für Bachelorarbeiten ist 3 Monate nach Anmeldung in Helios (regulär) oder 2 Monate nach Anmeldung in Helios (Bachelorarbeit getrennt von Praktikum).
Abgabe für Masterarbeiten ist 6 Monate nach Anmeldung in Helios.

**** VH:
Vereinbarung unterschrieben? Anmeldung in HELIOS?     J: ja     N: nein     N-H: nein, aber bereits in HELIOS     N-V: nein, aber Vereinbarung bereits unterschrieben

***** Bew.:
Bewertung:     J: ja     N: nein

Tutor:
AJ:    Andreas Johanning
DaS:  Daniel Schiktanz
DS:   Dieter Scholz
PB:   Priyanka Barua
RC:   Ricardo Caja
TS:   Tahir Sousa

Die Stundenabrechnung für im SS angemeldete Arbeiten erfolgt im darauf folgenden WS.
Die Stundenabrechnung für im WS angemeldete Arbeiten erfolgt im darauf folgenden SS.


STAND:  12. 09. 2017
AUTOR:  Prof. Dr. Scholz
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home  Flugzeugbau
home  Department Fahrzeugtechnik und Flugzeugbau
home  Fakultät Technik und Informatik
home  Hochschule für Angewandte Wissenschaften Hamburg