The SLAC Polarized Electron Source

The SLAC PES, developed in the early 1990s for the SLC, has been in continuous use since 1992, during which time it has undergone numerous upgrades. The upgrades include improved cathodes with their matching laser systems, modified activation techniques and better diagnostics. The source itself and its performance with these upgrades will be described with special attention given to recent high-intensity long-pulse operation for the E-158 fixed-target parity-violating experiment.Comment: 6 pages, 4 figures, Workshop on Polarized Electron Sources and Polarimeters (PESP 2002), September 4-6, 2002, Danvers, M

SLAC's polarized electron source laser system for the E-158 parity violation experiment

SLAC E158 is an experiment to make the first measurement of parity violation in Moller scattering. The left-right cross-section asymmetry in the elastic scattering of a 45-GeV polarized electron beam off unpolarized electrons in a liquid hydrogen target will be measured to an accuracy of better than 10-8, with the expected Standard Model asymmetry being approximately 10-7. An intense circularly polarized laser beam for the polarized electron source is required with the ability to quickly switch between left and right polarization states with minimal left-right asymmetries in the parameters of the electron beam. This laser beam is produced by a unique SLAC-designed, flash-lamp pumped, Ti:Sapphire laser. We present this laser system design and initial results from recent commissioning runs

A five-year hedonic price breakdown for desktop personal computer attributes in Brazil

The purpose of this article is to identify the attributes that discriminate the prices of personal desktop computers. We employ the hedonic price method in evaluating such characteristics. This approach allows market prices to be expressed as a function, a set of attributes present in the products and services offered. Prices and characteristics of up to 3,779 desktop personal computers offered in the IT pages of one of the main Brazilian newspapers were collected from January 2003 to December 2007. Several specifications for the hedonic (multivariate) linear regression were tested. In this particular study, the main attributes were found to be hard drive capacity, screen technology, main board brand, random memory size, microprocessor brand, video board memory, digital video and compact disk recording devices, screen size and microprocessor speed. These results highlight the novel contribution of this study: the manner and means in which hedonic price indexes may be estimated in Brazil

SLAC's polarized electron source laser system for the E-158 parity violation experiment

SLAC E158 is an experiment to make the first measurement of parity violation in Moller scattering. The left-right cross-section asymmetry in the elastic scattering of a 45-GeV polarized electron beam off unpolarized electrons in a liquid hydrogen target will be measured to an accuracy of better than 10-8, with the expected Standard Model asymmetry being approximately 10-7. An intense circularly polarized laser beam for the polarized electron source is required with the ability to quickly switch between left and right polarization states with minimal left-right asymmetries in the parameters of the electron beam. This laser beam is produced by a unique SLAC-designed, flash-lamp pumped, Ti:Sapphire laser. We present this laser system design and initial results from recent commissioning runs

Assessment of an Increased-Fidelity Aeroelastic Experiment for Free Flying Wing Response to Gust Excitation

The paper proposes a methodology for increased-fidelity aeroelastic testing in a wind tunnel environment to improve the correlation between the aeroelastic response measured in a wind tunnel experiment and the aeroelastic response observed on an aircraft in flight. The focus of the current study is to assess the potential of the proposed methodology to improve load and response predictions by emulating the motion of a free flying aircraft at the root of the wing. For this purpose a numerical aeroelastic model of a free flying aircraft is used to obtain a reference aeroelastic response to gust excitation. The model is reduced to obtain an aeroelastic model comprising only the main wing of the aircraft which is clamped at the root as if it would be mounted in a wind tunnel. The wing is then subjected to five different motion profiles emulating the free flight to a various degree. The considered motion profiles are clamped boundary condition, heave-pitch motion of a free flying aircraft, motion profile following the angle of attack of the aircraft, and two modified heave-pitch motion profiles which match the angle of attack and the aerodynamic loads in the wind tunnel with those in free flight. The study shows that the considered motion profiles can significantly improve the correlation between the wind tunnel experiment and free flight. However, the effectiveness of each motion profile strongly depends on the gust length which indicates that the optimum motion profile depends on the gust length. Finally, the paper presents a conceptual design of a wind tunnel demonstrator to serve as a proof-of-concept for the proposed methodology.Aerospace Structures & Computational Mechanic

Timing jitter measurements at the SLC electron source

The SLC thermionic gun and electron source produce a beam of up to 15 /times/ 10/sup 10/ /sub e//minus/ in a single S-band bunch. A 170 keV, 2 ns FWHM pulse out of the gun is compressed by means of two subharmonic buncher cavities followed by an S-band buncher and a standard SLAC accelerating section. Ceramic gaps in the beam pipe at the output of the gun allow a measure of the beam intensity and timing. A measurement at these gaps of the timing jitter, with a resolution of <10 ps, is described. 3 refs., 5 figs

Design of morphing wing for aerodynamic performance considering the wing flexibility effects

This paper provides an insight into ongoing research aimed at designing a morphing wing with the ability to continuously adapt its aerodynamic shape. The wing is targeted at a general purpose unmanned aerial vehicle. The morphing wing concept outlined in the paper is based on continuous camber changes of the wing leading and trailing edges, allowing optimal performance in different flight regimes. The aeroelastic tailoring method is used to design the load carrying structure of the wing in order to define the optimal stiffness and strength of the structure, which are considered as fixed in subsequent design steps. The research proposes a novel modular design approach that combines aerodynamic shape optimisation and aeroelastic considerations for designing morphing wing surfaces.Group Sodj