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By DLR-contact, sample return missions to the large main-belt asteroid “19, Fortuna” have been studied. The mission scenario has been based on three ion thrusters of the RIT-22 model, which is presently under space qualification, and on solar arrays equipped with triple-junction GaAs solar cells. After having designed the spacecraft, the orbit-to-orbit trajectories for both, a one-way SEP mission with a chemical sample return and an all-SEP return mission, have been optimized using a combination of artificial neural networks with evolutionary algorithms. Additionally, body-to-body trajectories have been
investigated within a launch period between 2012 and 2015. For orbit-to-orbit calculation, the launch masses of the hybrid mission and of the all-SEP mission resulted in 2.05 tons and 1.56 tons, respectively, including a scientific payload of 246 kg. For the related transfer
durations 4.14 yrs and 4.62 yrs were obtained. Finally, a comparison between the mission scenarios based on SEP and on NEP have been carried out favouring clearly SEP.
Computational aeroelastic analysis and design of the HIRENASD wind tunnel wing model and tests
(2007)
We propose a simple parametric OSSD model that describes the variation of the sail film's optical coefficients with time, depending on the sail film's environmental history, i.e., the radiation dose. The primary intention of our model is not to describe the exact behavior of specific film-coating combinations in the real space environment, but to provide a more general parametric framework for describing the general optical degradation behavior of solar sails.
A procedure for the evaluation of the failure probability of elastic-plastic thin shell structures is presented. The procedure involves a deterministic limit and shakedown analysis for each probabilistic iteration which is based on the kinematical approach and the use the exact Ilyushin yield surface. Based on a direct definition of the limit state function, the non-linear problems may be efficiently solved by using the First and Second Order Reliabiblity Methods (Form/SORM). This direct approach reduces considerably the necessary knowledge of uncertain technological input data, computing costs and the numerical error. In: Computational plasticity / ed. by Eugenio Onate. Dordrecht: Springer 2007. VII, 265 S. (Computational Methods in Applied Sciences ; 7) (COMPLAS IX. Part 1 . International Center for Numerical Methods in Engineering (CIMNE)). ISBN 978-1-402-06576-7 S. 186-189
Since fluid-structure interaction within the finite-element method is state of the art in many engineering fields, this method is used in voice analysis. A quasi two-dimensional model of the vocal folds including the ventricular folds is presented. First results of self-sustained vocal fold oscillation are presented and possibilities as well as limitations are discussed.
Proceedings of the International Conference on Material Theory and Nonlinear Dynamics. MatDyn. Hanoi, Vietnam, Sept. 24-26, 2007, 8 p. In this paper, a method is introduced to determine the limit load of general shells using the finite element method. The method is based on an upper bound limit and shakedown analysis with elastic-perfectly plastic material model. A non-linear constrained optimisation problem is solved by using Newton’s method in conjunction with a penalty method and the Lagrangean dual method. Numerical investigation of a pipe bend subjected to bending moments proves the effectiveness of the algorithm.
Adaptive logistics : information management for planning and control of small series assembly
(2007)
Innovative interplanetary deep space missions, like a main belt asteroid sample
return mission, require ever larger velocity increments (∆V s) and thus ever
more demanding propulsion capabilities. Providing much larger exhaust velocities than chemical high-thrust systems, electric low-thrust space-propulsion
systems can significantly enhance or even enable such high-energy missions. In
1995, a European-Russian Joint Study Group (JSG) presented a study report
on “Advanced Interplanetary Missions Using Nuclear-Electric Propulsion”
(NEP). One of the investigated reference missions was a sample return (SR)
from the main belt asteroid (19) Fortuna. The envisaged nuclear power plant,
Topaz-25, however, could not be realized and also the worldwide developments
in space reactor hardware stalled. In this paper, we investigate, whether such
a mission is also feasible using a solar electric propulsion (SEP) system and
compare our SEP results to corresponding NEP results.
Near-Earth asteroid (NEA) 99942 Apophis provides a typical example for the evolution of asteroid orbits that lead to Earth-impacts after a close Earth-encounter that results in a resonant return. Apophis will have a close Earth-encounter in 2029 with potential very close subsequent Earth-encounters (or even an impact) in 2036 or later, depending on whether it passes through one of several less than 1 km-sized gravitational keyholes during its 2029-encounter. A pre-2029 kinetic impact is a very favorable option to nudge the asteroid out of a keyhole. The highest impact velocity and thus deflection can be achieved from a trajectory that is retrograde to Apophis orbit. With a chemical or electric propulsion system, however, many gravity assists and thus a long time is required to achieve this. We show in this paper that the solar sail might be the better propulsion system for such a mission: a solar sail Kinetic Energy Impactor (KEI) spacecraft could impact Apophis from a retrograde trajectory with a very high relative velocity (75-80 km/s) during one of its perihelion passages. The spacecraft consists of a 160 m × 160 m, 168 kg solar sail assembly and a 150 kg impactor. Although conventional spacecraft can also achieve the required minimum deflection of 1 km for this approx. 320 m-sized object from a prograde trajectory, our solar sail KEI concept also allows the deflection of larger objects. For a launch in 2020, we also show that, even after Apophis has flown through one of the gravitational keyholes in 2029, the solar sail KEI concept is still feasible to prevent Apophis from impacting the Earth, but many KEIs would be required for consecutive impacts to increase the total Earth-miss distance to a safe value
Interplanetary trajectories for low-thrust spacecraft are often characterized by multiple revolutions around the sun. Unfortunately, the convergence of traditional trajectory optimizers that are based on numerical optimal control methods depends strongly on an adequate initial guess for the control function (if a direct method is used) or for the starting values of the adjoint vector (if an indirect method is used). Especially when many revolutions around the sun are re-
quired, trajectory optimization becomes a very difficult and time-consuming task that involves a lot of experience and expert knowledge in astrodynamics and optimal control theory, because an adequate initial guess is extremely hard to find. Evolutionary neurocontrol (ENC) was proposed as a smart method for low-thrust trajectory optimization that fuses artificial neural networks and evolutionary algorithms to so-called evolutionary neurocontrollers (ENCs) [1]. Inspired by natural archetypes, ENC attacks the trajectoryoptimization problem from the perspective of artificial intelligence and machine learning, a perspective that is quite different from that of optimal control theory. Within the context of ENC, a trajectory is regarded as the result of a spacecraft steering strategy that maps permanently the actual spacecraft state and the actual target state onto the actual spacecraft control vector. This way, the problem of searching the optimal spacecraft trajectory is equivalent to the problem of searching (or "learning") the optimal spacecraft steering strategy. An artificial neural network is used to implement such a spacecraft steering strategy. It can be regarded as a parameterized function (the network function) that is defined by the internal network parameters. Therefore, each distinct set of network parameters defines a different network function and thus a different steering strategy. The problem of searching the optimal steering strategy is now equivalent to the problem of searching the optimal set of network parameters. Evolutionary algorithms that work on a population of (artificial) chromosomes are used to find the optimal network parameters, because the parameters can be easily mapped onto a chromosome. The trajectory optimization problem is solved when the optimal chromosome is found. A comparison of solar sail trajectories that have been published by others [2, 3, 4, 5] with ENC-trajectories has shown that ENCs can be successfully applied for near-globally optimal spacecraft control [1, 6] and that they are able to find trajectories that are closer to the (unknown) global optimum, because they explore the trajectory search space more exhaustively than a human expert can do. The obtained trajectories are fairly accurate with respect to the terminal constraint. If a more accurate trajectory is required, the ENC-solution can be used as an initial guess for a local trajectory optimization method. Using ENC, low-thrust trajectories can be optimized without an initial guess and without expert attendance.
Here, new results for nuclear electric spacecraft and for solar sail spacecraft are presented and it will be shown that ENCs find very good trajectories even for very difficult problems. Trajectory optimization results are presented for 1. NASA's Solar Polar Imager Mission, a mission to attain a highly inclined close solar orbit with a solar sail [7] 2. a mission to de ect asteroid Apophis with a solar sail from a retrograde orbit with a very-high velocity impact [8, 9] 3. JPL's \2nd Global Trajectory Optimization Competition", a grand tour to visit four asteroids from different classes with a NEP spacecraft
Dr.-Ing. Martin Wolf ; Dipl.-Kaufm. Daniel Ulbrich , Dr. Pecher und Partner Ingenieurgesellschaft mbH, München. 31 S. (S. 139-168). Beitrag zum 1. Aachener Softwaretag in der Wasserwirtschaft < 1, 2007, Aachen>. Zusammenfasung [der Autoren] Die öffentlichen Kanalnetze Deutschlands stellen mit einem Wert von rd. 330 Mrd. € ein enormes Anlagevermögen dar. Auf Grund des oft schlechten Zustandes und geringer Ausgaben zur Instandhaltung und Erneuerung ist zu erwarten, dass durch die gegenwärtige Sanierungspraxis eher ein Substanzwertverzehr des Kanalnetzes als ein Substanzwerterhalt im Sinne des Generationenvertrages erzielt wird. Für einen nachhaltigen Betrieb und Erhalt der Kanalnetze sind deshalb Sanierungsstrategien erforderlich, die neben den technischen und gesetzlichen Anforderungen auch den mittel- und langfristigen Substanzwertverlauf berücksichtigen. Dieser wird beeinflusst vom erforderlichen oder durchgeführten Sanierungsumfang, Art und Zusammensetzung der ausgewählten Maßnahmen sowie der zeitlichen Abfolge der Sanierungsmaßnahmen. Erheblichen Einfluss auf den Substanzwertverlauf hat zudem die Berücksichtigung der hydraulischen Verhältnisse sowie der optisch nicht sichtbaren Undichtheiten. Entsprechend ist es erforderlich, die tatsächlich vorhandenen Defizite zu ermitteln und die Sanierungsmaßnahmen sowie eine Strategie zur Umsetzung zu erarbeiten. Da sich gezeigt hat, dass alleine die Einhaltung der technischen und gesetzlichen Anforderung für einen Substanzwerterhalt nicht ausreicht, muss die geplante Strategie im Dr.-Ing. Martin Wolf 139 von 170 Decision-Support-System kokas zur Sanierungsplanung und Strategieentwicklung 1. Aachener Softwaretag in der Wasserwirtschaft Hinblick auf die nachhaltige Wertentwicklung überprüft und ggf. Anpassungen vorgenommen werden. Kurzfristig erzielte Einsparungen durch reduzierten Schadensumfang oder einseitige Maßnahmenwahl ermöglichen zwar im günstigsten Fall, die Anforderungen einzuhalten, gehen jedoch zwangsläufig zu Lasten des Substanzwertes und führen mittel- und langfristig zu einer Verschärfung der Kosten- und Gebührensituation. Der monetäre, am konkreten Sanierungsaufwand orientierte Substanzwertansatz ermöglicht dabei, technische und kaufmännische Gesichtspunkte praxisnah zu verknüpfen und den bestmöglichen Ausgleich zwischen den gegenläufigen Zielen Substanzwerterhalt und Gebührenkonstanz zu finden.
Flow separation is a phenomenon that occurs in all kinds of supersonic nozzles sometimes during run-up and shut-down operations. Especially in expansion nozzles of rocket engines with large area ratio, flow separation can trigger strong side loads that can damage the structure of the nozzle. The investigation presented in this paper seeks to establish measures that may be applied to alter the point of flow separation. In order to achieve this, a supersonic nozzle was placed at the exit plane of the conical nozzle. This resulted in the generation of cross flow surrounding the core jet flow from the conical nozzle. Due to the entrainment of the gas stream from the conical nozzle the pressure in its exit plane was found to be lower than that of the ambient. A Cold gas instead of hot combustion gases was used as the working fluid. A mathematical simulation of the concept was validated by experiment. Measurements confirmed the simulation results that due to the introduction of a second nozzle the pressure in the separated region of the conical nozzle was significantly reduced. It was also established that the boundary layer separation inside the conical nozzle was delayed thus allowing an increased degree of overexpansion. The condition established by the pressure measurements was also demonstrated qualitatively using transparent nozzle configurations.
Der Internally Commutated Thyristor (ICT) : ein neuartiger GCT mit integrierter Ausschalteinheit
(2007)
"[...] Der erste Teil des Vortags konzentriert sich auf die bei Ericsson gemachten Erfahrungen. Welche Muster wurden identifiziert, für welche Tests wurden sie eingesetzt. Wie werden diese Muster verwendet, wie werden sie beschrieben und spezifiziert. Und schließlich, wie entsteht eine Art Standardisierung, in der das Wissen über diese Muster als Organisationswissen zur Verfügung steht.
Im zweiten Teil des Vortrags werden die bei Ericsson gemachten Erfahrungen verallgemeinert. Die bei Ericsson verwendeten Muster werden auf allgemeine Strukturen übertragen (z.B. Client-Server). Es wird gezeigt, wie die Zuordnung von Testverfahren auf Netzwerkmuster auch in anderen Domänen verwendet wird und welche Vorteile sich damit erzielen lassen."
Quelle: http://www.qs-tag.de/fileadmin/software-qs-tag/public/2007/abstract_jacobs.shtml