Cyclische Diazastannylene. - XI : Ringe und Käfige mit Dimethylbis(methylamido)silan-Liganden am zweiwertigen Zinn

SnCl2 und (LiNMe)2SiMe2 (Me = CH3) reagieren unter Abspaltung von LiCl zu dem molekularen Polycyclus (Me2Si)3(NMe)5Sn2 (I) und zu polymerem (SnNMe)n (II). I kann auch durch Einwirkung von Dimethylbis(methylamino)-silan auf das stannylen Me2Si(NCMe3)2Sn dargestellt werden, wobei weiterhin der Käfig (Me2Si)(NMe)5Sn4 (III) entsteht, wenn ohne Lösungsmittel gearbeitet wird. Auf Grund von 1H-NMR-Spectren und einer Röntgenstrukturanalyse ergeben sich für I und III folgende Strukturen: das Molekülgerüst von I besteht aus einem Sn2N2-Vierring, der in 1,3-Position die Atomsequenz ---Si---N---Si--- und in 2,4-Position ---N—Si---N--- als Brücken trägt; III hat die Structur eines "Basketans\u27;: vier tetraedrisch ausgerichtete Zinnatome und vier Stickstoffatome bilden einen Würfel, in dessen eine Kante eine MeNSiMe2-Einheit eingeschoben ist. Die NMR-Spectren zeigen an, dass in III bei Zimmertemperatur in organischen Lösungsmitteln Bindungsfluktuationen auftreten

Construction of an optical test-bed for eLISA

In the planned eLISA mission a key part of the system is the optical bench that holds the interferometers for reading out the inter-spacecraft distance and the test mass position. We report on ongoing technology development for the eLISA optical system like the back-link between the optical benches and the science interferometer where the local beam is interfered with the received beam from the distant spacecraft. The focus will be on a setup to investigate the tilt-to-pathlength coupling in the science interferometer. To test the science interferometer in the lab a second bench providing a laser beam and a reference interferometer is needed. We present a setup with two ultra-stable low expansion glass benches and bonded optics. To suppress the tilt-to-pathlength coupling to the required level (few μm/rad) imaging optics are placed in front of the interferometer photo diodes

Cyclische Diazastannylene. - XXIV : Zur Umsetzung von (tert-Butylimino)stannylen mit Chlorwasserstoff

(tert-Butylimino)stannylen (1) reagiert mit Chlorwasserstoff zu [tBuN(H)-SnCl]2 (2a), tBuNH2 · SnCl2 (3) und tBuNH3 SnCl3 (4). Da die Trennung der kristallinen Produkte Schwierigkeiten macht, ist man auf Alternativsynthesen von 2a, 3 und 4 angewiesen. Me2Si[N(tBu)H][N(tBu)]SnX (6a: X = Cl, 6b: X = Br, 6c: X = I) stellt eine Ausgangsstufe dar, die mit tert-Butylamin zu 2a (X = Cl) und 2b (X = Br) quantitativ umgesetzt werden kann. 3 und 4 entstehen aus 2a u.a. durch HCl-Addition. 6a, b und c zeigen unterschiedliche 1H-NMR-Spektren in Abhängigkeit von der Temperatur, was auf eine intramolekulare Ligandenumordnung hinweist. Die Röntgenstrukturanalysen von 6a (orthorhombisch, Raumgruppe P112121), 3 (monoklin, P21/c, und triklin, P) und 4 (triklin, P) weisen 6a als Molekül mit einer intramolekularen Donor-Akzeptor-Bindung [Sn-N = 2.347(6) Å], 3 in beiden Modifikationen als Addukt von SnCl2 an tBuNH2 [Sn-N = 2.334(4) Å (monoklin) bzw. 2.338(4) Å (triklin)] und 4 als Ionenpaar tBuNH3 SnCl3- mit H-Cl-Brücken im Kristall aus [Sn-Cl = 2.542 (Mittelwert), C-N = 1.515(6) Å]

Novel C-35 terpenoids from the Panamarian liverwort Plagiochila Moritziana

A new class of C-35 terpenoids is described from Hepaticae: plagiospirolide A and plagiospirolide B, two novel heptacyclic spiro-terpenes were isolated from the Panamanian liverwort Plagiochila moritziana Lindbg. & Gott. Structures were determined by MS, extensive NMR studies and X-ray crystallographic analysis. The compounds may be biosynthesized by condensation of a sesquiterpenoid and a diterpenoid unit in a Diels-Alder like reaction

Test Results for a Non-toxic, Dual Thrust Reaction Control Engine

A non-toxic, dual thrust reaction control engine (RCE) was successfully tested over a broad range of operating conditions at the Aerojet Sacramento facility. The RCE utilized LOX/Ethanol propellants; and was tested in steady state and pulsing modes at 25-lbf thrust (vernier) and at 870-lbf thrust (primary). Steady state vernier tests vaned chamber pressure (Pc) from 0.78 to 5.96 psia, and mixture ratio (MR) from 0.73 to 1.82, while primary steady state tests vaned Pc from 103 to 179 psia and MR from 1.33 to 1.76. Pulsing tests explored EPW from 0.080 to 10 seconds and DC from 5 to 50 percent at both thrust levels. Vernier testing accumulated a total of 6,670 seconds of firing time, and 7,215 pulses, and primary testing accumulated a total of 2,060 seconds of firing time and 3,646 pulses

Ignition Characterization Test Results for the LO2/Ethanol Propellant Combination

A series of contracts were issued by the Marshall Space Flight Center (MSFC) of the National Aeronautics and Space Administration (NASA) under the auspices of the Exploration Systems Mission Directorate to develop and expand the maturity of candidate technologies considered to be important for future space exploration. One such technology was to determine the viability of incorporating non-toxic propellants for Reaction Control Subsystems (RCS). Contract NAS8-01109 was issued to Aerojet to develop a dual thrust Reaction Control Engine (RCE) that utilized liquid oxygen and ethanol as the propellants. The dual thrust RCE incorporated a primary thrust level of 870 lbf, and a vernier thrust level of 10 - 30 lbf. The preferred RCS approach for the dual thrust RCE was to utilize pressure-fed liquid oxygen (LOX) and ethanol propellants; however, previous dual thrust feasibility testing incorporated GOX/Ethanol igniters as opposed to LOX/Ethanol igniters in the design. GOX/Ethanol was easier to ignite, but this combination had system design implications of providing GOX for the igniters. A LOX/Ethanol igniter was desired; however, extensive LOX/Ethanol ignition data over the anticipated operating range for the dual thrust RCE did not exist. Therefore, Aerojet designed and tested a workhorse LOX igniter to determine LOX/Ethanol ignition characteristics as part of a risk mitigation effort for the dual thrust RCE design. LOX, encompassing potential two-phase flow conditions anticipated being present in real mission applications. A workhorse igniter was designed to accommodate the hll LOX design flowrate, as well as a reduced GOX flowrate. It was reasoned that the initial LOX flow through the igniter would flash to GOX due to the latent heat stored in the hardware, causing a reduced oxygen flowrate because of a choked, or sonic, flow condition through the injection elements. As LOX flow continued, the hardware would chill-in, with the injected oxygen flow transitioning from cold GOX through two-phase flow to subcooled LOX. permitted oxygen state points to be determined in the igniter oxidizer manifold, and gas-side igniter chamber thermocouples provided chamber thermal profile characteristics. The cold flow chamber pressure (P(sub c)) for each test was determined and coupled with the igniter chamber diameter (D(sub c)) to calculate the characteristic quench parameter (P(sub c) x D(sub c)), which was plotted as a function of core mixture ratio, m. Ignition limits were determined over a broad range of valve inlet conditions, and ignition was demonstrated with oxygen inlet conditions that ranged from subcooled 210 R LOX to 486 R GOX. Once ignited at cold GOX conditions, combustion was continuous as the hardware chilled in and the core mixture ratio transitioned from values near 1.0 to over 12.5. Pulsing is required in typical RCS engines; therefore, the workhorse igniter was pulse tested to verify the ability to provide the required ignition for a pulsing RCE. The minimum electrical pulse width (EPW) of the dual thrust RCE was 0.080 seconds