\u3cem\u3eBeaty\u3c/em\u3e and the Beast: A Prisoner’s Due Process Right to Notice of Changes to Execution Protocols

On May 25, 2011, in Beaty v. Brewer, the U.S. Court of Appeals for the Ninth Circuit held that a prisoner’s due process rights do not include the right to notice or to appeal a last-minute change to a state’s method of execution. In doing so, the court established a loophole, permitting states to avoid Eighth Amendment challenges to execution protocols by waiting until the final moment to amend them. This Comment argues that implicit within a prisoner’s right to challenge a state’s method of execution is a due process right to timely notice of changes to that method of execution

Space Storable Rocket Technology (SSRT) basic program

The Space Storable Rocket Technology Program (SSRT) was conducted to establish a technology for a new class of high performance and long life bipropellant engines using space storable propellants. The results are described. Task 1 evaluated several characteristics for a number of fuels to determine the best space storable fuel for use with LO2. The results indicated that LO2-N2H4 is the best propellant combination and provides the maximum mission/system capability maximum payload into GEO of satellites. Task 2 developed two models, performance and thermal. The performance model indicated the performance goal of specific impulse greater than or = 340 seconds (sigma = 204) could be achieved. The thermal model was developed and anchored to hot fire test data. Task 3 consisted of design, fabrication, and testing of a 200 lbf thrust test engine operating at a chamber pressure of 200 psia using LO2-N2H4. A total of 76 hot fire tests were conducted demonstrating performance greater than 340 (sigma = 204) which is a 25 second specific impulse improvement over the existing highest performance flight apogee type engines

The effects of competing commitments on the relationship between organisational stress and well-being

Faculty of Humanities School of Human and Community Development 0004529r Chazens2global.co.zaThis study aimed to investigate the nature of the relationship between organisational stress, in terms of individual’s emotional reactions to their jobs, and physical and psychological well-being. It then aimed to expand upon previous research in this area, by considering the effects of potential mediators such as job and family involvement on this relationship. In addition to this it aimed to explore the possible differences in the emotions at work, well-being and job and family involvement as experienced by individuals of different demographic groups. Questionnaires containing a biographical information sheet and four well-established measures, including the Job-Related Affective Well-Being Scale, the Well- Being Scale, as well as the Job Involvement Questionnaire and Family Involvement Scale, were distributed to the male and female employees at a large organisation in Johannesburg. This sampling method yielded a final sample of 249 respondents, consisting of 120 men and 129 women. The results of this study illustrated significant differences in the physical well-being of the men and women in the sample, with men reporting experiencing greater levels of positive physical well-being than their female counterparts. A significant difference was also demonstrated in the emotions at work experienced by the Black and White respondents of the study, with the Black individuals reporting more positive emotions at work than their White counterparts. In addition, the findings of this study indicated that there was a positive relationship between the constructs of emotions at work and physical and psychological well-being and that emotions at work mediated the relationships between job and family involvement and well-being

High temperature thrust chamber for spacecraft

A high temperature thrust chamber for spacecraft (20) is provided herein. The high temperature thrust chamber comprises a hollow body member (12) having an outer surface and an internal surface (16) defining the high temperature chamber (10). The body member (12) is made substantially of rhenium. An alloy (18) consisting of iridium and at least alloying metal selected of the group consisting of rhodium, platinum and palladium is deposited on at least a portion of the internal surface (16) of the body member (12). The iridium and the alloying metal are electrodeposited onto the body member (12). A HIP cycle is performed upon the body member (12) to cause the coating of iridium and the alloying metal to form the alloy (18) which protects the body member (12) from oxidation

Space Storable Rocket Technology program (SSRT). Option 1 program

The Space Storable Rocket Technology (SSRT) Option 1 Program was initiated in October 1991 after completion of the Basic Program. The program was restructured in mid-July 1992 to incorporate a Rhenium Technology Task and reduce the scope of the LO2-N2H4 engine development. The program was also extended to late February 1993 to allow for the Rhenium Technology Task completion. The Option 1 Program was devoted to evaluation of two new injector elements, evaluation of two different methods of thermal protection of the injector, evaluation of high temperature material properties of rhenium and evaluation of methods of joining the rhenium thrust chamber to the columbium injector and nozzle extension. In addition, critical experiments were conducted (Funded by Option 2) to evaluate mechanisms to understand the effects of GO2 injection into the chamber, helium injection into the main LO2, effect of the splash plate and effect of decreasing the aspect ratio of the 120-slot (-13a) element. The performance and thermal models were used to further correlate the test results with analyses. The results of the work accomplished are summarized

High Pressure Earth Storable Rocket Technology Program: Basic Program

The HIPES Program was conducted for NASA-LeRC by TRW. The Basic Program consisted of system studies, design of testbed engine, fabrication and testing of engine. Studies of both pressure-fed and pump-fed systems were investigated for N2O4 and both MMH and N2H4 fuels with the result that N2H4 provides the maximum payload for all satellites over MMH. The higher pressure engine offers improved performance with smaller envelope and associated weight savings. Pump-fed systems offer maximum payload for large and medium weight satellites while pressure-fed systems offer maximum payload for small light weight satellites. The major benefits of HIPES are high performance within a confined length maximizing payload for lightsats which are length (volume) constrained. Three types of thrust chambers were evaluated -- Copper heatsink at 400, 500 and 600 psia chamber pressures for performance/thermal; water cooled to determine heat absorbed to predict rhenium engine operation; and rhenium to validate the concept. The HIPES engine demonstrated very high performance at 50 lbf thrust (epsilon = 150) and Pc = 500 psia with both fuels: Isp = 337 sec using N2O4-N2H4 and ISP = 327.5 sec using N2O4-MMH indicating combustion efficiencies greater than 98%. A powder metallurgy rhenium engine demonstrated operation with high performance at Pc = 500 psia which indicated the viability of the concept