REKOMMENDATIONER FÖR INSATSER VID SJÄLVSKADEBETEENDE : Nationellt kvalitetsdokument för psykiatrin

Rekommendationer för insatser vid självskadebeteende är framarbetade inom ramen för Nationella självskadeprojektet som på uppdrag av regeringen och Sveriges kommuner och landsting (SKL) utvecklat och samordnat kunskap kring självskade- beteende generellt och psykiatrins insatser specifikt. Dokumentet är antaget av projektets styrgrupp, representanter från brukar-, anhörig- och intresseorganisationer samt SKL:s nationella nätverk för ledning och styrning.Rekommendationer för insatser vid självskadebeteende sammanfattar aktuell kunskap om effektiva insatser inom specialistpsykiatrin och baseras på aktuell forskning. I de fall då tillräcklig forskning saknas och konsensus funnits i program- gruppen, baseras rekommendationerna på klinisk erfarenhet och erfarenheter från personer med egen erfarenhet av självskadebeteende. Dokumentet uppdateras regelbundet och kompletteras med nyare rön samt redigeras med tanke på att öka användbarheten.Behovet av att arbeta utifrån en gemensam kunskapsbas är stort. Dokumentet ska bidra till en likvärdig vård över landet. Rekommendationerna utgör stommenför den vård som psykiatrin bör erbjuda personer med självskadebeteende.De implementeras lokalt och kompletteras med regionala planer/riktlinjer som specificerar hur rekommendationerna ska uppfyllas i den kliniska vardagen.Detta dokument har genomgående fokus på individen med självskade- beteende och tydliggör behov av rätt bemötande, riktad behandling, samordning och kontinuitet. Stommen utgörs av sju rekommendationer som till stor del utgår från NICE Quality Standards for Self harm (NICE, 2013) som sedan har kompletterats och anpassats till svenska förhållanden. Dokumentet syftar till:• Att vara ett beslutsstöd för ledningen inom den specialiserade psykiatrinvid utvecklingsinsatser för bättre vård.• Att verka för en likvärdighet i landet vad gäller vårdutbud och kvalitet.• Att stödja medarbetare inom psykiatrin i det dagliga arbetet.• Att stödja individer som söker vård genom att ge kunskap om vad somkan efterfrågas

Particle Size in Solid Rocket Motor Plume: New Experimental Method

Solid propellant rocket boosters release metal oxide particulate in the atmosphere, as a result of the combustion of the aluminum powder contained in the energetic material. The characterization of these particles is still an open question regarding the environmental impact of space launch activities. For this reason an innovative collection technique was conceived in the frame of the EMAP (Experimental Modelling of Alumina Particulate in Solid Booster) project, an activity financed by the European Space Agency. The method consists in an intrusive probe capable of quenching and capturing the particles exiting from the nozzle, thus enabling size measurement, chemical characterization, and morphology observation. This paper presents an overview of the activity and reports some preliminary results obtained from the initial particle size characterization

Web application for self-reporting of personal health data to electronic health records

Denna rapport behandlar ett arbete sju studenter som läste kursen TDDD96: Kandidatprojekt i programutveckling utförde under vårterminen 2019. Arbetets syfte var att utforska möjligheten att skicka in personlig hälsodata till Region Östergötland via en hemsida. För att åstadkomma detta utvecklades en webbapplikation, samt utfördes en utredning av openEHR:s datastrukturer och API för att kunna koppla applikationen till Region Östergötlands journalsystem. Resultatet blev en fungerande webbapplikation som hämtar data från hälsoplattformen Google Fit och skickar därefter in det till en journal via openEHR:s REST-API. Hälsodata som hämtats från Google Fit är data som samlats in med sensorer från mobiler och smartklockor såsom puls och antal steg. Denna rapport avser att ge en inblick i utvecklingsprocessen, beskriva de bakomliggande besluten, de problem som uppstått under projektets gång och dess lösningar, samt diskutera resultatet. Med i rapporten finns även de individuella kandidatrapporter medlemmarna i gruppen har skrivit, dessa hittas sist i dokumentet

Web application for self-reporting of personal health data to electronic health records

Denna rapport behandlar ett arbete sju studenter som läste kursen TDDD96: Kandidatprojekt i programutveckling utförde under vårterminen 2019. Arbetets syfte var att utforska möjligheten att skicka in personlig hälsodata till Region Östergötland via en hemsida. För att åstadkomma detta utvecklades en webbapplikation, samt utfördes en utredning av openEHR:s datastrukturer och API för att kunna koppla applikationen till Region Östergötlands journalsystem. Resultatet blev en fungerande webbapplikation som hämtar data från hälsoplattformen Google Fit och skickar därefter in det till en journal via openEHR:s REST-API. Hälsodata som hämtats från Google Fit är data som samlats in med sensorer från mobiler och smartklockor såsom puls och antal steg. Denna rapport avser att ge en inblick i utvecklingsprocessen, beskriva de bakomliggande besluten, de problem som uppstått under projektets gång och dess lösningar, samt diskutera resultatet. Med i rapporten finns även de individuella kandidatrapporter medlemmarna i gruppen har skrivit, dessa hittas sist i dokumentet

Particle size in srm plume: Assessment of collection method

The present work aims at giving an overview of the current experimental activity status of an intrusive technique for particles capturing in supersonic-high temperature flows for the use in solid rocket motors plume. The innovative technique was conceived in the EMAP (Experimental Modelling of Alumina Particulate in Solid Booster) framework, an initiative financed by the European Space Agency aiming at the characterization of the alumina exiting from rocket nozzles in terms of size, temperature, and spatial distribution. This kind of information are of paramount importance for the environmental impact assessment of space launch activity. Experimental tests are still ongoing and the present paper discusses some of the critical aspects, solutions, and open questions arising during the hot fire testing of this innovative intrusive technique

Experiments for Collection and Characterization of Particles Exiting from Solid Propellant Rocket Nozzles

Metals in solid propellants are used to improve specific impulse and increment the energy density. Their combustion generates condensed products that move along the motor chamber and are expelled through the nozzle. The discharge of liquid or solid particles across the gas dynamic nozzle of large boosters is not only a matter of specific impulse loss. Recent climatological studies are addressing possible short and long term environmental effects that may be attributed to space launch activity by large launchers. In this respect, the knowledge of plume content and, specifically, of physical, chemical, and morphological properties of the exhausted particulate is needed. In the frame of the EMAP (Experimental Modelling of Alumina Particulate in Solid Booster) project, an activity financed by the European Space Agency, the Space Propulsion Laboratory (SPLab) of Politecnico di Milano developed a collection method and an analysis protocol for the characterization of the particles contained in the rocket plume. The collection is performed by an intrusive probe capable of capturing the particles directly from the nozzle exit and quenching them. The post-collection protocol enables size measurement, chemical characterization, and morphology observation. In this paper an overview of the collection and analysis activity is presented, along with the final results that were achieved by analyzing the plume of different rocket motors

Experimental Modeling of Alumina Particulate in Solid Booster: Final Report

The ESA-EMAP project (Saile et al., 2019) is dedicated to the experimental modeling of alumina particulates in solid boosters. The motivation roots in the uncertainty regarding the impact of the alumina particles emitted by the solid rocket motors (SRMs) of European launch systems on the ozone depletion in the stratosphere. This uncertainty needs to be addressed in the face of the expected growth and significantly increased number of rocket launchers as predicted in studies associated with the new space era. For this reason, the ESA-EMAP project focused on the experimental investigation of the particle formation processes and the quantification of the corresponding flow conditions by means of sub-scale tests. The particle formation was assessed from the combustion chamber throughout the nozzle to its final state as it would be expected in the atmosphere. These tests were executed with a solid rocket motor (SRM) mimicking a launch system and operating under flight-realistic conditions with an ambient flow. As it can be seen in fig. 1, this task was accomplished by integrating the rocket motor into a subsonic wind tunnel nozzle of the ’Vertical Test Section Cologne’ (VMK). Numerous measurement techniques were applied to capture the flow conditions and formation of the particles. In detail, the high-speed schlieren measurements were applied to capture the density gradients and the topology of the jet. Spectroscopic measurement methods such as UV-Vis spectroscopy, Fourier transform infrared spectroscopy, alumina emission measurement shed light on the exhaust gas composition and temperature distribution of the jet. The velocity was captured by means of particle image velocimetry, direct image particle size determination, and laser-2-focus (fig. 2). The heat release from the jet was assessed with a Gardon gauge and infrared thermography. Finally, the particle size (fig. 5) was quantified by means of measurements with an aerodynamic particle sizer and rocket plume collector (Maggi et al., 2020). In summary, a vast data base on solid rocket exhaust plume was generated. At three different planes along the path line of the particles, there is now information available on the particle size, the particle velocity, the temperature distribution, the density gradient distribution, and the gas composition of the plume. That data base provides a foundation for further analytical explorations and provides the opportunity to validate models associated with the physics of solid rocket exhaust plumes

Overview to the ESA-EMAP Project: Characterization of SRM Plumes with Alumina Particulate in Subscale Testing

The current paper provides an overview of the ESAEMAP project. This project pursues activities regarding the experimental modeling of alumina particulates in solid boosters. The issue regards the particles residing in the atmosphere after the passage of a launch vehicle with solid rocket propulsion, which might contribute to local and overall ozone depletion. The question is to what extent since the particle size distribution left behind is essentially unclear. For this reason, the ESA-EMAP investigations focus on the characterization of the solid exhaust plume properties for well-defined combustion chamber conditions. Thus, details of the rocket motor assembly, of the developed solid propellant grains and of first measurement results are provided. The paper presents technical findings concerning the rocket motors and reveals aspects to the feasibility of the applied measurement techniques

Characterization of SRM plumes with alumina particulate in subscale testing

The current paper provides an outline and first results of the ESA-EMAP project. This project pursues activities regarding the experimental modeling of alumina particulates in solid boosters (EMAP). The issue regards the particles residing in the atmosphere after the passage of a launch vehicle with solid rocket propulsion, which might contribute to local and overall ozone depletion. The question is to what extent since the particle size distribution left behind is essentially unclear. For this reason, the ESA-EMAP investigations focus on the characterization of the solid exhaust plume properties for well-defined combustion chamber conditions. Thus, details of the rocket motor assembly, of the developed solid propellant grains, and of first measurement results are provided. The paper presents technical findings concerning the rocket motors and reveals aspects to the feasibility of the applied measurement techniques