First Nesting Record and Status Review of the Glossy Ibis in Nebraska

Glossy Ibis (Plegadis falcinellus) is believed to be a recent colonist from the Old World whose numbers have increased and range has expanded in North America over the past two centuries (Patten and Lasley 2000). Glossy Ibis range expansion has been described as involving periods of relative stability followed by periods of rapid increase (Patten and Lasley 2000). Prior to the 1980s, Glossy Ibis were primarily found in the southeastern United States and along the Atlantic Coast (Patten and Lasley 2000). In the mid to late 1980s, Glossy Ibis began to rapidly increase and expand into Texas. By the early 1990s they were increasingly reported in the Great Plains (Thompson et a1. 20 11), particularly along the front range of Colorado and New Mexico (Patten and Lasley 2000). In Nebraska, the first documented occurrence of Glossy Ibis was a single adult with 28 White-faced Ibis (Plegadis chihi) at Wilkins Waterfowl Production Area (WPA), Fillmore County, 24 April 1999 (Jorgensen 2001). Since the initial record, the number of reports of Glossy Ibis has increased. Glossy Ibis status was elevated from accidental to casual by the Nebraska Ornithologists’ Union Records Committee (NOURC) in 2005 (Brogie 2005). Only a few years later in 2014, its status was elevated again from casual to regular and NOURC no longer sought documentation for sightings (Brogie 2014). In 2015, Jorgensen observed this species nesting in the Rainwater Basin. Given the recent observation of nesting, the rapid increase in annual observations, along with field identification challenges as a result of similarity to and hybridization with the White-faced Ibis, the status of the Glossy Ibis in Nebraska is in need of clarification. Here, we provide observational details about the first confirmed nesting by the species in Nebraska, review all reports of Glossy Ibis and apparent Glossy × White-faced Ibis hybrids, and comment on this species’ overall status in the state

De-icing of the altitude wind tunnel turning vanes by electro-magnetic impulse

The Altitude Wind Tunnel at the NASA-Lewis facility is being proposed for a refurbishment and moderization. Two major changes are: (1) the increasing of the test section Mach number to 0.90, and (2) the addition of spray nozzles to provide simulation of flight in icing clouds. Features to be retained are the simulation of atmospheric temperature and pressure to 50,000 foot altitude and provision for full-scale aircraft engine operation by the exhausting of the aircraft combustion gases and ingestion of air to replace that used in combustion. The first change required a re-design of the turning vanes in the two corners downstream of the test section due to the higher Mach number at the corners. The second change threatens the operation of the turning vanes by the expected ice build-up, particulary on the first-corner vanes. De-icing by heat has two drawbacks: (1) an extremely large amount of heat is required, and (2) the melted ice would tend to collect as ice on some other surfaces in the tunnel, namely, the tunnel propellers and the cooling coils. An alternate de-icing method had been under development for three years under NASA-Lewis grants to the Wichita State University. This report describes the electro-impulse de-icing (EIDI) method and the testing work done to assess its applicability to wind tunnel turning vane de-icing. Tests were conducted in the structural dynamics laboratory and in the NASA Icing Research Tunnel. Good ice protection was achieved at lower power consumption and at a wide range of tunnel operations conditions. Recommendations for design and construction of the system for this application of the EIDI method are given

HAL/SM system software requirements specification

For abstract, see N76-14843

HAL/SM system functional design specification

The functional design of a preprocessor, and subsystems is described. A structure chart and a data flow diagram are included for each subsystem. Also a group of intermodule interface definitions (one definition per module) is included immediately following the structure chart and data flow for a particular subsystem. Each of these intermodule interface definitions consists of the identification of the module, the function the module is to perform, the identification and definition of parameter interfaces to the module, and any design notes associated with the module. Also described are compilers and computer libraries

Invariant Manifolds, the Spatial Three-Body Problem and Space Mission Design

The invariant manifold structures of the collinear libration points for the spatial restricted three-body problem provide the framework for understanding complex dynamical phenomena from a geometric point of view. In particular, the stable and unstable invariant manifold \tubes" associated to libration point orbits are the phase space structures that provide a conduit for orbits between primary bodies for separate three-body systems. These invariant manifold tubes can be used to construct new spacecraft trajectories, such as a \Petit Grand Tour" of the moons of Jupiter. Previous work focused on the planar circular restricted three-body problem. The current work extends the results to the spatial case

Flavor Delta(54) in SU(5) SUSY Model

We design a supersymmetric SU (5) GUT model using \Delta (54), a finite non-abelian subgroup of SU (3)f . Heavy right handed neutrinos are introduced which transform as three-dimensional repre-sentation of our chosen family group. The model successfully reproduces the mass hierarchical mass structures of the Standard Model, and the CKM mixing matrix. It then provides predictions for the light neutrino with a normal hierarchy and masses such that m{\nu},1 \approx 5\times10-3 eV, m{\nu}, 2 \approx 1\times 10-2 eV, and m{\nu},3 \approx 5 \times 10-2 eV. We also provide predictions for masses of the heavy neutrinos, and correc- tions to the tri-bimaximal matrix that fit within experimental limits, e.g. a reactor angle of -7.31o. A simple modification to our model is introduced at the end and is shown to also produce predictions that fall well within those limits.Comment: 22 page

Performance of silicon solar cell assemblies

Solar cell assembly current-voltage characteristics, thermal-optical properties, and power performance were determined. Solar cell cover glass thermal radiation, optical properties, confidence limits, and temperature intensity effects on maximum power were discussed