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Hydrogen peroxide (H2O2) is a typical surface sterilization agent for packaging materials used in the pharmaceutical, food and beverage industries. We use the finite-elements method to analyze the conceptual design of an in-line thermal evaporation unit to produce a heated gas mixture of air and evaporated H2O2 solution. For the numerical model, the required phase-transition variables of pure H2O2 solution and of the aerosol mixture are acquired from vapor-liquid equilibrium (VLE) diagrams derived from vapor-pressure formulations. This work combines homogeneous single-phase turbulent flow with heat-transfer physics to describe the operation of the evaporation unit. We introduce the apparent heat-capacity concept to approximate the non-isothermal phase-transition process of the H2O2-containing aerosol. Empirical and analytical functions are defined to represent the temperature- and pressure-dependent material properties of the aqueous H2O2 solution, the aerosol and the gas mixture. To validate the numerical model, the simulation results are compared to experimental data on the heating power required to produce the gas mixture. This shows good agreement with the deviations below 10%. Experimental observations on the formation of deposits due to the evaporation of stabilized H2O2 solution fits the prediction made from simulation results.
Dimensionen 1-2019: Magazin der FH Aachen University of Applied Sciences - Wir sind FH Aachen!
(2019)
Inhaltsverzeichnis:
6 Wir sind FH!
8 Steigen Sie ein : Wir nehmen Sie mit auf eine Reise der Roboter und Maschinen
18 Grenzenlose Förderung : Das Stipendienprogramm geht in das zehnte Jahr
20 Marias neue Kleider : Wissenschaftler unterstützen die Domschatzkammer
24 Die Sprengstoffschnüffler : Fliegerbomben im Erdreich: Neues Verfahren auf Basis der Neutronenaktivierungsanalyse
26 Geschafft! : Erster marokkanischer Elektrotechnikstudent macht seinen Doppelabschluss an der FH Aachen
28 Maßgeschneidert : Dr. Denise Milinnus vom INB entwickelt digitale Biosensoren für die personalisierte Medizin
32 Auf Höhenflügen : Tobias Barth macht außergewöhnliche Luftaufnahmen
36 Über alle Berge : Talentscouting eröffnet neue Wege
38 Der etwas andere Reiseführer : FH-Studentinnen entwerfen Stadtplan für junge Menschen
42 Warum kommt mein Zug zu spät? : FH-Experten im Interview über Probleme und Lösungen der Schiene
48 Der Alina-Weg : Alina Richter promoviert bei der Volkswaren-Konzernforschung
51 Selbst ist die Frau : Die 31-jährige Meral Dural studiert erfolgreich Elektrotechnik am FH-Campus Jülich
52 An der Schnittstelle : INFORM-Professur für angewandte Mathematik und Informatik
53 Kopfnuss
54 Einmal scannen bitte : Forschungsprojekt am MASKOR-Institut wird vom Bund gefördert
56 Inspiriert vom Tier- und Pflanzenmeer : FH-Absolventin Lara Bispinck gewinnt "Future Impact Maker"
60 Schmusekurs mit dem Tiger : FH Aachen führt Kooperationsverbund mit taiwanesischen Hochschulen an
62 Impressum
Design and Development of a Novel Self-Igniting Microwave Plasma Jet for Industrial Applications
(2019)
20 years after the successful ground deployment test of a (20 m) 2 solar sail at DLR Cologne, and in the light of the upcoming U.S. NEAscout mission, we provide an overview of the progress made since in our mission and hardware design studies as well as the hardware built in the course of our solar sail technology development. We outline the most likely and most efficient routes to develop solar sails for useful missions in science and applications, based on our developed `now-term' and near-term hardware as well as the many practical and managerial lessons learned from the DLR-ESTEC Gossamer Roadmap. Mission types directly applicable to planetary defense include single and Multiple NEA Rendezvous ((M)NR) for precursor, monitoring and follow-up scenarios as well as sail-propelled head-on retrograde kinetic impactors (RKI) for mitigation. Other mission types such as the Displaced L1 (DL1) space weather advance warning and monitoring or Solar Polar Orbiter (SPO) types demonstrate the capability of near-term solar sails to achieve asteroid rendezvous in any kind of orbit, from Earth-coorbital to extremely inclined and even retrograde orbits. Some of these mission types such as SPO, (M)NR and RKI include separable payloads. For one-way access to the asteroid surface, nanolanders like MASCOT are an ideal match for solar sails in micro-spacecraft format, i.e. in launch configurations compatible with ESPA and ASAP secondary payload platforms. Larger landers similar to the JAXA-DLR study of a Jupiter Trojan asteroid lander for the OKEANOS mission can shuttle from the sail to the asteroids visited and enable multiple NEA sample-return missions. The high impact velocities and re-try capability achieved by the RKI mission type on a final orbit identical to the target asteroid's but retrograde to its motion enables small spacecraft size impactors to carry sufficient kinetic energy for deflection.
Improved efficiency prediction of a molten salt receiver based on dynamic cloud passage simulation
(2019)
Recent Unmanned Aerial Vehicle (UAV) design procedures rely on full aircraft steady-state Reynolds-Averaged-Navier-Stokes (RANS) analyses in early design stages. Small sensor turrets are included in such simulations, even though their aerodynamic properties show highly unsteady behavior. Very little is known about the effects of this approach on the simulation outcomes of small turrets. Therefore, the flow around a model turret at a Reynolds number of 47,400 is simulated with a steady-state RANS approach and compared to experimental data. Lift, drag, and surface pressure show good agreement with the experiment. The RANS model predicts the separation location too far downstream and shows a larger recirculation region aft of the body. Both characteristic arch and horseshoe vortex structures are visualized and qualitatively match the ones found by the experiment. The Reynolds number dependence of the drag coefficient follows the trend of a sphere within a distinct range. The outcomes indicate that a steady-state RANS model of a small sensor turret is able to give results that are useful for UAV engineering purposes but might not be suited for detailed insight into flow properties.