USAP 1989 Cruise IV R/V Polar Duke, Cruise Report

This is a report for the 1989 R/V Polar Duke scientific cruise, PD IV-89 (also known as PD8904), around the Antarctic Peninsula. The cruise collected single-channel seismic data, piston cores, and heatflow data.National Science Foundation's Office of Polar ProgramsInstitute for Geophysic

Bright Half Life Assistant Director

My Theatre Arts thesis project was working as an assistant director (AD) on the play “Bright Half Life,” alongside my director/professor, Dana Resnick. This play ran from August 29 through September 1 at the beginning of the Fall 2018 semester in the Strub Theatre at LMU. For this project I was expected to perform a number of duties and responsibilities. The other assistant director and I were present at every production meeting, rehearsal, and performance to assist our director in establishing, creating, and guiding her vision for the play into life. We all met with the designers for the show’s set, lights, sound, and costumes to collaborate on what physical stimuli to bring together in order to exemplify the feelings we believed the show to hold. The other AD and I were also expected to work together on a script analysis of the play in order to expand our knowledge on the show and focus on many details within the story. This expansive research helped our team work through many of the questions that arose during the rehearsal process regarding the story and the characters’ intentions. Because of the presence of two AD’s, we could each split off with the two student-actors in the show and run lines with them individually, which was beneficial because of the women’s presence onstage for the entire 80-minute run-time, sharing a plethora of lines. By the end of the project, when the rehearsal process and performances were finished, I had successfully played my part in helping to put up a full-length, mainstage play within the theatre department, and I learned innumerable lessons in directing, leading, and general theatre experience that I had not previously had the opportunity to learn

Dynamic training devices in CRM training

Pilot training effectiveness and flying safety of a seasonal tour flight company are described. The change from single pilot to two pilot operated twin otters is examined. The use of the ATC 810 training device, its possibilities and training capacity is outlined. Problem areas which may arise, emergency system and pilot/passenger interaction are analyzed

If It Wasn’t Documented, It Wasn’t Done: Implementing Nursing Skills Documentation

Students carry out nursing skills in the lab setting. Documentation reinforces the execution and comprehension of the skill performed. Nurses are required to document skills performed in the clinical setting (Mollart et al., 2020). Therefore, it is essential to have students\u27 chart upon completing a nursing skill as a portion of their performance. Students completed charting on paper and have progressed to electronic charting in google docs

Ignition characterization of LOX/hydrocarbon propellants

The results of an evaluation of the ignition characteristics of the gaseous oxygen (Gox)/Ethanol propellant combination are presented. Ignition characterization was accomplished through the analysis, design, fabrication and testing of a spark initiated torch igniter and prototype 620 lbF thruster/igniter assembly. The igniter was tested over a chamber pressure range of 74 to 197 psia and mixture ratio range of 0.778 to 3.29. Cold (-92 to -165 F) and ambient (44 to 80 F) propellant temperatures were used. Spark igniter ignition limits and thruster steady state and pulse mode, performance, cooling and stability data are presented. Spark igniter ignition limits are presented in terms of cold flow pressure, ignition chamber diameter and mixture ratio. Thruster performance is presented in terms of vacuum specific impulse versus engine mixture ratio. Gox/Ethanol propellants were shown to be ignitable over a wide range of mixture ratios. Cold propellants were shown to have a minor effect on igniter ignition limits. Thruster pulse mode capability was demonstrated with multiple pulses of 0.08 sec duration and less

SOS: Survey of Skills in Prelicensure Nursing Programs

A survey of nursing faculty was conducted for this exploratory study on the skills taught in their nursing program, along with the evaluation methods utilized. Students\u27 competence is verified in various forms, including traditional skills checks, peer evaluation, or video recording (Kemery & Morrell, 2020; Sterling-Fox et al., 2020). Other skills may be demonstrated and practiced and not formally validated

Testing of fuel/oxidizer-rich, high-pressure preburners

Results of an evaluation of high pressure combustion of fuel rich and oxidizer rich LOX/RP-1 propellants using 4.0 inch diameter prototype preburner injectors and chambers are presented. Testing covered a pressure range from 8.9 to 17.5 MN/square meters (1292 to 2540 psia). Fuel rich mixture ratios ranged from 0.238 to 0.367; oxidizer rich mixture ratios ranged from 27.2 to 47.5. Performance, gas temperature uniformity, and stability data for two fuel rich and two ozidizer rich preburner injectors are presented for a conventional like-on-like (LOL) design and a platelet design injector. Kinetically limited combustion is shown by the excellent agreement of measured fuel rich gas composition and C performance data with kinetic model predictions. The oxidizer rich test results support previous equilibrium combustion predictions

High performance N2O4/amine elements: Blowapart

The mechanisms controlling hypergolic propellant reactive stream separation (RRS) were studied and used to develop design criteria for injectors free from both steady state RSS and cyclic propellant stream separation. This was accomplished through the analysis of single element injectors using N204/MMH propellants; the injectors were representative of the space shuttle orbit maneuvering engine and space tug applications. A gas phase/surface reaction mechanism which controls RSS was identified. Injector design criteria were developed, which defined a critical chamber pressure for those operating conditions above which RSS occurs. It was found that the amount of interfacial surface area at impingement is controlled by injector hydraulics

Low cost training aids and devices

The need for advanced flight simulators for two engine aircraft is discussed. Cost effectiveness is a major requirement. Other training aids available for increased effectiveness are recommended. Training aids include: (1) audio-visual slides; (2) information transfer; (3) programmed instruction; and (4) interactive training systems

Transients influencing rocket engine ignition and popping Interim report

Engine design and operating parameters studied for effects on rocket engine ignition and poppin