Re-Entry

Objective Studies have examined social accountability in medical education in Iran, while no studies have deeply focused on social determinants of health, specifically for rehabilitation sciences. On the other hand, the University of Social Welfare and Rehabilitation Sciences has made significant contributions to the development of rehabilitation in Iran. This study investigates the educational need for integrating social determinants of health within rehabilitation education in Iran. Materials & Methods The study was conducted using qualitative content analysis. The study participants consisted of 33 individuals, including students and academic faculty members of rehabilitation departments and members of relevant non-governmental organizations. The data collection method involved focused group discussions to explore the participants' experiences. The Elo and Kyngäs process was employed using MAXQDA software, version 2018 to analyze the data. Results The results revealed the main and core category of requirements for integrating the social determinants of health approach into rehabilitation education, as well as two subcategories: Educational content requirements and environmental and educational setting requirements. Students' educational content requirements were classified into knowledge (including social determinants of health knowledge, the international classification of functioning, disability and health framework, various rehabilitation fields, ethical principles and patients' rights, etc.), skills (including life skills, teamwork, communication and empathy, teaching, advocacy, etc.) and attitudes (including comprehensive and holistic perspective, etc.). Environmental and educational setting requirements were divided into three subcategories: Fundamental and general requirements, theoretical education setting and clinical education setting. Conclusion This study identified educational program requirements while ensuring the necessary knowledge, attitudes, and skills essential for realizing this approach. It also identified the educational environment for delivering basic, theoretical, and clinical education.

Concerns about "emerging missile states" have spurred development of a system to defend the US from small-scale ballistic missile attacks. But the planned system could be compromised by simple countermeasures, and the security costs of deployment could be high.

Introduction: Generally every organization's success relies on its employees' efforts as well as their job satisfaction. Identifying the factors leading to job satisfaction among faculty members could be useful in increasing their satisfaction and motivation for efficient educational and research activities. This study was conducted to determine job satisfaction rate among faculty members of University of Social Welfare and Rehabilitation Sciences. Methods: This was a descriptive cross-sectional study performed on 94 faculty members of Tehran University of Social Welfare and Rehabilitation Sciences in the year 2008. Data was gathered through a researcher-made questionnaire and analyzed by SPSS software using mean, standard deviation, and Principal Component Analysis. Results: The mean and standard deviation of faculty members' job satisfaction was 72.6 ± 16.91 out of 135. The mean and Standard deviation for the domains under investigation were as follows:

Introduction: Generally every organization's success relies on its employees' efforts as well as their job satisfaction. Identifying the factors leading to job satisfaction among faculty members could be useful in increasing their satisfaction and motivation for efficient educational and research activities. This study was conducted to determine job satisfaction rate among faculty members of University of Social Welfare and Rehabilitation Sciences. Methods: This was a descriptive cross-sectional study performed on 94 faculty members of Tehran University of Social Welfare and Rehabilitation Sciences in the year 2008. Data was gathered through a researcher-made questionnaire and analyzed by SPSS software using mean, standard deviation, and Principal Component Analysis. Results: The mean and standard deviation of faculty members' job satisfaction was 72.6 ± 16.91 out of 135. The mean and Standard deviation for the domains under investigation were as follows:

Background Prisoner’s addiction is one of the major problems in many countries which imposes very high medical costs and social harm to communities. This study investigated the pattern of substance use and related factors in male prisoners in one of the prisons in southeastern Iran. Methods This cross-sectional study was carried out in 2016. The study population was inmates of a prison in southeast Iran. Sampling was carried out randomly according to the list of prisoners. Data were collected using a form and were analyzed with statistics software SPSS. Findings More than four-fifths (75.3%) of the subjects consumed at least one substance (alcohol, tobacco and other drugs), 74.4% were smoking, 73.2% used a narcotic substance, and about one-fifth (19.3%) reported drinking alcohol. With a frequency of 62.0%, opium was the most frequently utilized narcotic substance. Poppy juice (31.6%), cannabis (29.8%), crystal (16.9%) and tramadol (16.9%) were the next frequent substances used. A pe...

Reentry space vehicles face extreme conditions of heat §ux when interacting with the atmosphere at hypersonic velocities. Stagnation point heat §ux is normally used as a reference for Thermal Protection Material (TPS) design; however, many critical phenomena also occur at o¨-stagnation point. This paper adresses the implementation of an o¨stagnation point methodology able to duplicate in ground facility the hypersonic boundary layer over a §at plate model. The ¦rst analysis using two-dimensional (2D) computational §uid dynamics (CFD) simulations is carried out to understand the limitations of this methodology when applying it in plasma wind tunnel. The results from the testing campaign at VKI Plasmatron are also presented.

Modelling gas dispersion in mechanically ventilated building is a challenge for safety engineers. A leak in such an infrastructure can generate two different consequences: toxic effect or blast effect after a flammable vapour cloud ignition. In both case, it is important to be able to predict the gas behaviour using numerical tools in order to be able to design adapted ventilation systems. Gaseous products are generally stored under pressure that induces high velocity in case of release from the tank or following a line rupture. Considering this important pressure, the jet zone is a highly complex zone with a Mach number higher than 1 that induces shock waves. These waves correspond to discontinuity of the flow. After this jet zone, a transition region (air entrainment) is observed and can be characterised by the beginning mixture of the gas with air. This also corresponds to an expansion of the jet diameter inducing a velocity decrease. Finally, after this zone, the flow becomes go...

This work provides catalytic recombination coefficients () on water-cooled copper calorimeters at 350 K. Measurements are obtained on probes of different sizes, tested in a plasma wind tunnel at stagnation point configuration. Despite pressure and surface temperature are the same among the probes, different catalytic activities are observed. This fact is not consistent with -models implemented in CFD solvers, which assume catalytic recombination of first order. A dimensional analysis shows that data is consistent with theoretical work of Rosner, and that different levels of gaseous recombination can influence the empirical determination of .

The paper deals with a microsatellite and the related deployable recovery capsule. The aero-brake is folded at launch and deployed in space and is able to perform a de-orbiting controlled re-entry. This kind of capsule, with a flexible, high temperature resistant fabric, thanks to its lightness and modulating capability, can be an alternative to the current "conventional" recovery capsules. The present authors already analyzed the trajectory and the aerodynamic behavior of low ballistic coefficient capsules during Earth re-entry and Mars entry. In previous studies, aerodynamic longitudinal stability analysis and evaluation of thermal and aerodynamic loads for a possible suborbital re-entry demonstrator were carried out in both continuum and rarefied regimes. The present study is aimed at providing preliminary information about thermal and aerodynamic loads and longitudinal stability for a similar deployable capsule, as well as information about the electronic composition of the plasma sheet and its possible influence on radio communications at the altitudes where GPS blackout could occur. Since the computer tests were carried out at high altitudes, therefore in rarefied flow fields, use of Direct Simulation Monte Carlo codes was mandatory. The computations involved both global aerodynamic quantities (drag and longitudinal moment coefficients) and local aerodynamic quantities (heat flux and pressure distributions along the capsule surface). The results verified that the capsule at high altitude (150 km) is self-stabilizing; it is stable around the nominal attitude or at zero angle of attack and unstable around the reverse attitude or at 180 deg angle of attack. The analysis also pointed out the presence of extra statically stable equilibrium trim points.

China’s spectacular economic growth in the last decade has been accompanied by its impressive performance in the areas of space, missiles and warship building. Among the more remarkable of these has been its development of an Anti-Ship Ballistic Missile (ASBM), which according to experts, is intended to deter or target US aircraft carriers. Western media and naval sources reacted with concern bordering on alarm to the reports of the development of the ASBM. There were also skeptics who strongly doubted China’s capability to design and engineer such a missile along with the sophisticated technical infrastructure that its operation requires. However in May 2010 when a senior US Admiral declared that in his view the Chinese ASBM had reached “Initial Operational Capability

This new series focuses on the theory and practice of strategy. Following Clausewitz, strategy has been understood to mean the use made of force, and the threat of the use of force, for the ends of policy. This series is as interested in ideas as in historical cases of grand strategy and military strategy in action. All historical periods, near and past, and even future, are of interest. In addition to original monographs, the series will from time to time publish edited reprints of neglected classics as well as collections of essays.

The XJet is a small-scale system developed at NASA Ames Research Center for aerothermal testing of instrumentation integrated into NASA thermal protection systems. This test environment is designed to act as a screening testbed for thermal protection system-related design. Similar to an arc jet test facility, the XJet generates a convective heating flow by flowing gas past an electrical arc created between two electrodes. Physically, the XJet consists of a plasma-cutting torch mounted inside a vacuum chamber. Experiments have been performed to characterize the operational envelope of the XJet. These experiments have measured cold-wall absorbed heat fluxes between 12-128 W/cm 2. Other experiments performed include the examination of a new advanced thermal sensor's response when exposed to the XJet's plasma flow. Data gathered from XJet experimentation is being used to better understand instrumentation and TPS integration performance

Exposure to seismic hazard in mines is controlled through various evacuation, exclusion and re-entry procedures. The aim of exposure management procedures is to tactically reduce the safety risk by removing personnel from work areas during periods of elevated seismic hazard. Given that risk assessment is based on exposure, the design of exposure management procedures must also be risk-based. In practice, the decision to re-enter a workplace after an exclusion is generally only made based on an assessment of the seismic hazard, often using previously defined levels of tolerable seismic activity rates. The definition of tolerable seismic hazard, in the context of re-entry, is seldom quantitatively assessed based on risk. In order to move towards a comprehensive seismic risk management strategy, design methodologies must be able to quantify the impact of different exclusion and re-entry practices on risk. The appropriate re-entry practice can then be selected given the defined risk-based design acceptance criteria. There is still a long way to go before the risk-based design framework for exposure management procedures is complete. This paper reviews the current state of design of exposure management controls in the context of risk and discusses several important areas for further research.

European Commission, ESA has developed and launched a capsule that re-entered the Earth’s atmosphere protected by an inflatable heat shield. During the same mission, the newly developed Russian Fregat upper stage was also returned to Earth using the same technology. The last phase of the descent in both cases was performed with no parachute, allowing substantial savings in launch volume and mass. Obvious future applications for this new re-entry technology include International Space Station sample return, the delivery of networks of small stations to the Martian surface, and the return to Earth of launcher upper stages. r bulletin 103 — august 2000

1 Assistant Professor, Department of social work, University of Social Welfare and Rehabilitation Sciences, Tehran, Iran. 2 Lecturer, Department of social work, University of Social Welfare and Rehabilitation Sciences, Tehran, Iran. 3 Director of Counseling and Social Work of the Law Enforcement Force of Islamic Republic of Iran. 4 Assistant Professor, Department of Social work, University of Allame Tabatabai, Tehran, Iran. 5 Ph.D Student of Social Work, University of Social Welfare and Rehabilitation Sciences, Tehran, Iran. Journal of Police Medicine Original Article

An air data sensor (ADS) system is one of the key components in space transports. It can provide precious information on the pressure and the Mach number data that cannot be obtained from internal motion sensors. When a spaceship or a reentry vehicle is cruising at a very high altitude, the ADS will suffer problem of the time-delay in its pressure signals that propagates through a thin pressure tube. In this study, the time delay of the pressure propagation inside a thin tube under a low-pressure environment is evaluated based on the direct-simulation Monte-Carlo (DSMC) method. A CFD analysis based on axisymmetric Navier-Stokes equations is also conducted to evaluate the contribution of rarefied gas effects to the pressure propagation speed. These results are compared with experimental results. Based on the DSMC and CFD analyses, the time constant for the pressure change is determined to be around 0.013 seconds whereas the experimental results yielded 0.12 seconds when the pressure at the exit of the tube increases for about 20 to 40 Pa starting from 30 Pa. These results suggest that the propagation delay observed in the flight test of the atmospheric-entry capsule descending at an altitude of 79 km with Mach-4.5 flight velocity was partly caused by the rarefied gas effect.

Objective The re-entry of offenders to the community after their imprisonment is a sensitive and important stage and should always be considered by governmental and non-governmental organizations. The proper transition from prison to the community occurs when rehabilitation and social reintegration programs are developed and implemented based on the real needs of individuals. Social work is one of the professions that can help the judicial system with this issue. Many graduates of this profession provide social work services to prisoners and their families. Therefore, it is necessary to identify effective operational solutions in accordance with the conditions of the country and formulate a specific framework. This study aims to prepare a guideline for specialized social work intervention for community re-entry of offenders with a history of violence against individuals. Materials & Methods In this study, a qualitative approach was used to prepare the specialized guideline. First, the initial barriers and facilitators of successful community re-entry for offenders with a history of violence against individuals were prepared using thematic analysis. Then, based on the protocols of the social work process, the initial draft was developed. Next, at a focus group discussion session with faculty members and experts, the draft was reviewed and improved. To assess its applicability, we used the Appraisal of Guidelines for Research and Evaluation (AGREE) tool. Results Intertwined concerns, protective shields, welfare/economic security, social support, and achieving relative independence were identified as the five dimensions of successful community re-entry. The specialized social work interventions were presented after approval in four main stages: preparation for the case plan, development of the case plan, interventions and actions, and monitoring and review of interventions. The results of evaluation by AGREE tool showed an overall acceptable average of 7.85% (82.9% for scope and purpose, 88.1% for stakeholder involvement, 85.6% for rigor of development, 83% for clarity of presentation, 84.9% for applicability, and 89.8% for editorial independence). The users of this guideline are social workers and other professions related to prisons and training and security organizations, especially after-release care centers. Conclusion Investing in rehabilitation programs for prisoners is one of the best and most cost-effective ways to prevent the reoccurrence of violence, which not only has beneficial effects on those concerned but also promotes public safety. This issue becomes important when social reintegration and rehabilitation programs are developed based on scientific approaches and perspectives. Future studies on the effectiveness of the developed guideline, considering the local conditions, can help identify the effective factors of re-entry to the community in newly released prisoners. The skills and capabilities of social workers in presenting specialized interventions and establishing professional and inter-organizational communication, supporting rules and programs, motivation, and enthusiasm of the offender to change can all contribute to the success of this guideline in achieving the defined goals.

Space vehicles that make an entry through the atmosphere of a planet suffer tremendously because of extreme heating of the vehicle. The design of thermal protection systems for space vehicles involves multidisciplinary topics and is a very critical stage of space vehicles. The qualification of thermal protection systems on ground is very important for a safe space flight and the protection of critical payloads. At von Karman Institute, several ground facilities are used for the characterisation and qualification of thermal protection systems and materials. Infrared thermography is one of the most important measurement techniques used to monitor surface temperature and heat flux imposed on the thermal protection material, thus enabling the researchers to analyse the structural and thermal behaviour of tested materials.

Spacecraft, returning back to Earth, experience a very harsh environment during the encounter with the particles of the atmosphere. One of the major issues of the atmospheric entry is the extreme aerodynamic heating and the exothermic chemical reactions due to the gas-surface interaction at hypersonic free stream velocities. There is a constant effort by the space agencies to increase the understanding of the re-entry flight dynamics to optimize the spacecraft and especially its thermal protection system design. During the design process, ground tests and numerical tools are extensively used for their low cost and controlled environment abilities. However, real flight tests are indispensable for ground test and numerical tools validation. Due to high costs, such missions are rarely launched and thus there is an increasing interest in small affordable entry probes. Such platforms, once matured enough, may serve as an easily accessible tool to produce experimental data. It is the aim ...

My wish is that the reader enjoys this dissertation and that it brings him/her a better understanding on Gas-Surface Interaction (GSI) phenomena. Nonetheless, this journey through the VKI doctoral program has been long, and I wouldn't be able to address this topic without acknowledging people that were by my side during this research, because without them this thesis would not have been possible: A big thank to Olivier Chazot for giving me the opportunity to develop my thesis in the Plasmatron facility. His office was always open and ready for discussion. A special mention to his telephone, most of the time ringing during each one of our conversations. Also to Roberto Flores, director of this thesis in UPC, who allowed me to keep in contact with my university. Following the experimental nature of this dissertation, I would like to mention also the contribution made by Pascal Collin. He did an excelent job running the Plasmatron and installing the probes. I will always remember his desperation when water leaks appear when making the vacuum in the chamber. I thank also the rest of the Plasmatron team: Bernd Helber and Damien Le Quang as radiation experts, and Işil Şakraker as advisor for calorimetric measurements. Many CFD simulations appear in this dissertaion. For that, the advice of Vincent Van Der Haegen, my office mate, has been extremely useful to achieve a converged solution. Also, the flight extrapolation technique developed here deserves my gratitude to Fabio Pinna, whose expertise in CFD helped me to improve my IXV simulations and achieve the "Pinna Certification". I really enjoyed working with them. Other VKI colleagues I want to mention are Alessandro Turchi, who helped me understand many aspects of GSI phenomena, Francesco Panerai who set the basis to develop this dissertation, and Georgios Bellas-Chatzigeordis to whom I encourage to continue with the catalytic model development and implementation in VKI numerical tools. Last but not least, special thanks to my family. They encouraged me to pursue a doctorate degree and supported me in the most difficult moments.

Part II involves reconnecting (after a period of quarantine and self-imposed isolation), albeit gingerly, with others and with oneself.  I treat doctors who, for example, are still stressed to the max; they figure out how to curtail a sense of failure and inadequacy.  Some patients apply for jobs remotely, perfecting a screen persona.  They let go of old assumptions about what they “should” be, and think in terms of what is possible. This is not a lowering of their sights; rather, it is a cultivation of peripheral vision. Such resilience requires hope, a version of the possible. Possibility turns out to be a complicated term.  If it replaces old certainties, it still allows us to consider the future from a new, unaccustomed angle of approach.  There are no guarantees, but neither are doors to the future entirely shut.  We simply have to adapt.  Ultimately, the chapter concerns where and how to set limits, and how to enforce them.  Many of my patients have never faced such questions so directly or with such psychologically potent consequences.

High conservative safety margins, applied to the design of spacecraft thermal protection systems for planetary entry, need to be reduced for higher efficiency of future space missions. Ground testing of such protection systems is of great importance during the design phase. This study covers a methodology for simulating the complex hypersonic entry aerothermochemistry in a plasma wind tunnel for a given spacecraft geometry without any assumption on axisymmetry or bluntness. A demonstration of this proposed methodology is made on the Qubesat for Aerothermodynamic Research and Measurements on AblatioN, QARMAN mission, which is a rectangular reentry CubeSat with a cork-based ablative thermal protection system in the front unit. The reacting boundary-layer profiles of the hypersonic entry probe compare well with the ones developing at the stagnation region of the plasma test model, defined with the proposed flight-to-ground duplication method.

The objective of the EXPERT re-entry flight project is to obtain data on critical aerothermodynamic phenomena by means of dedicated payloads integrated onto its thermal protection system. These data will be used to validate the tools for Aerodynamic data basing and Aerothermodynamic design of thermal protection systems of hypersonic cruise and reentry spacecrafts. Validation of design tools really means understanding of the uncertainties associated with the use of ground based hypersonic facilities, with the level of validation of the physical models embedded into the numerical codes employed for the numerical reconstruction of these windtunnel experiments , its flight extrapolation as well as with the qualification of the sensors integrated into the thermal protection system. Within this paper, the objectives of the different measurement assemblies and their designs are reviewed. The theoretical tools and experimental facilities related to the flight experiments are presented.

The proliferation of Ballistic Missiles throughout the world, fed by worldwide high-technology market for smart submunitions, poses a new substantial threat in the tactical domain, a forerunner to an emerging family of smart missiles and unmannedair vehicles. The interest in the issue, and in countermeasures, is common to all defense communities, but conflicting interests of operational, military, political and industrial nature-obscure a rational assessment. The analysis presented here uses technology and market trends, and gross features of missiles and air-defense systems, to conclude that an extended air defense, countering the whole new threat arsenal, is possible and imperative.

SHARK is a 20kg capsule launched on March the 26th 2010 from Kiruna with the European sounding rocker Maxus-8. During the ascent parabola, the capsule was released and successfully executed its 15 minutes ballistic flight and then re-entered in the atmosphere from a 700km altitude. The capsule has been recovered on July the 1 st and all data have been acquired. All the instrumentation worked nicely and the data acquisition continued even after the landing, confirming the robustness of the design.

We recently received-via a third party-a critique of our report, Countermeasures. 2 The critique, written by Uzi Rubin and titled "Comments on the UCS Report on Countermeasures," is dated 18 July 2000. Rubin states that his study was "considerably less exhaustive" than the countermeasures report and was done by "a small team of experienced missile engineers." Rubin's critique has not been published, but instead has been distributed informally in the United States.

With the induction of new weapon systems in South Asia, notably BMDs, the region would gradually become prone to risk of war especially due to unresolved disputes, notably Kashmir. The sporadic events of violence and state terrorism in Indian Held Kashmir, as have been witnessed in past few months, pose serious threat to a major chuck of the entire world population. Due to mutual hostility and suspicion, role of international community, especially the major powers, would remain critical in facilitating the bilateral peace between the South Asian nuclear rivals or else possibility of a nuclear exchange between India and Pakistan would keep the populace of this region hostage to the nuclear radiation effects around the globe.

With its first successful Ballistic Missile Defence (BMD) test on November 27, 2006, India joined the BMD club that includes countries like the U.S., Russia, China, Japan and Israel. 1 The timely interception of one Prithvi surface-to-surface ballistic missile by another modified Prithvi could not be devoid of various implications, perceived diversely across the region. Before coming to the real implications, it is pertinent to give an account of the BMD technology, its functioning, development and shortcomings in the present day.

A simplified model for heterogeneous catalysis is presented. A theoretical expression of the recombination coefficient has been obtained by means of an analogy with gas-phase kinetics, whereby desorption is assumed similar to final product formation following decomposition of the activated compound. The constants of the model are defined by fitting experimental data. The method devised is particularly useful when detailed physical modeling approaches are unrealizable, namely when material characteristics are unknown. This model has been applied to PM1000, the material planned for the ESA EXPERT capsule external skin. The expression of the recombination coefficient has been interpolated using the experimental data provided by the Centre National de la Recherche Scientifique in France and the von Karman Institute in Belgium, implemented in the Centro Italiano Ricerche Aerospaziali computational fluid dynamics code, and tested for typical reentry conditions. Its application to the EXPERT capsule reentry problem shows that it appears to work well and is promising. Results confirm the importance of realistically modeling catalytic recombination on thermal protection systems, both in terms of wall heat flux and chemical composition of the airstream near the surface. In particular, the heat flux predicted is much lower than in the case of fully catalytic surface, indicating that, at the points of the EXPERT trajectory chosen, PM1000 seems to have poor catalytic activity.

The article deals with the aerothermal analysis of a sample-return hy-personic capsule reentering on Earth from an interplanetary exploration mission. The main objective of the work is to estimate the heat flux distribution on the cap-sule surface and to perform one-dimensional thermal analyses for its ablative heat shield. After a short review of sample-return missions, the numerical models im-plemented are described and the computational results, obtained along a feasible reentry trajectory, are presented and discussed. Particular attention has been paid to compare the convective stagnation point heat fluxes obtained by means of Com-putational Fluid Dynamic (CFD) analyses with the ones computed with engineer-ing correlations. A further comparison between CFD and with Direct Simulation Monte Carlo (DSMC), in order to investigate the air rarefaction effects, is reported. The article shows an overall satisfactory agreement between engineering corre-lation and numerical results and al...

Expanded perlite is widely used in construction and manufacturing industry mainly due to its good thermal and acoustical insulating properties. Nevertheless, the currently applied expansion technology has some disadvantages, which affect the product quality and limit the range of its applications. To overcome these drawbacks a new expansion process has been designed based on the use of a vertical electrically heated expansion furnace. The knowledge and control of the conditions inside the furnace is very important to optimize the product properties and the furnace performance. The main parameters affecting expanded perlite properties are the expansion temperature and retention time. Both parameters can change through the proper adjustment of the furnace wall temperature and air feeding rate. The aim of this work is the application of a Computational Fluid Dynamics (CFD) approach to study the temperature and air velocity profiles inside the furnace in order to understand and optimise...

We recently received-via a third party-a critique of our report, Countermeasures. 2 The critique, written by Uzi Rubin and titled "Comments on the UCS Report on Countermeasures," is dated 18 July 2000. Rubin states that his study was "considerably less exhaustive" than the countermeasures report and was done by "a small team of experienced missile engineers." Rubin's critique has not been published, but instead has been distributed informally in the United States.

This paper presents the experimental system which has been designed to measure vacuum ultraviolet (VUV) optical emission spectra. It has been tested at the plasma wind tunnel PWK1 at the Institute of Space Systems. The setup, its calibration and qualification are reported. Wind tunnel experiments have been conducted with a local mass-specific enthalpy of 68.4 MJ/kg and a stagnation pressure of 24.4 hPa. The radiation is collected through a magnesium fluoride window mounted close to the stagnation point of a sample. The received light is redirected to the spectrometer with a series of mirrors in an evacuated light path. The spectral range between 116 -197 nm was investigated. The lower limit is due to the transmission of the window material. Measurements with a cooled copper and a carbon preform material sample are presented. The measured VUV spectra feature atomic nitrogen and oxygen lines for both the copper and the material sample. Atomic carbon lines are present in the case of the material sample.

An instrumented aircraft and ground-based observing campaign was mounted to measure the radiation from the hypervelocity (11.0 km/s) reentry of the Genesis Sample Return Capsule prior to landing on the Utah Test and Training Range on September 08, 2004. The goal was to validate predictions of surface heating, the physical conditions in the shock layer, and the amount and nature of gaseous and solid ablation products as a function of altitude. This was the first hypervelocity reentry of a NASA spacecraft since the Apollo era. Estimates of anticipated emissions were made. Erroneous pointing instructions prevented us from acquiring spectroscopic data, but staring instruments measured broadband photometric and acoustic information. A surface-averaged brightness temperature was derived as a function of altitude. From this, we conclude that the observed optical emissions were consistent with most of the emitted light originating from a gray body continuum, but with a surface averaged temperature of 570 K less than our estimate from the predicted heat flux. Also, the surface remained warm longer than expected. We surmise that this is on account of conduction into the heat shield material, ablative cooling, and finite-rate wall catalycity. Preparations are underway to observe a second hypervelocity reentry 12.8 km/s) when the Stardust Sample Return Capsule returns to land at U.T.T.R. on January 15, 2006. Nomenclature A = projected surface area (in m 2 ) BB λ (T) = Planck curve * Mission Scientist, SETI Institute, no AIAA member † Program manager, NASA Ames Research Center, AIAA Member Associate Fellow American Institute of Aeronautics and Astronautics 1 44th AIAA Aerospace Sciences Meeting and Exhibit (Reno, Nevada. 9 -12 Jan 2006 ) c = speed of light = 2.99793 x 10 8 m/s C d = drag coefficient D = the distance to the SRC (in m) h = Planck constant = 6.62620 x 10 -34 J s k = Boltzmann's constant = 1.38062 x 10 -23 J/K λ = wavelength (m) MAC = Multi-Instrument Aircraft Campaign ρ = air density SRC = Sample Return Capsule T = temperature Introduction HE Genesis Sample-Return-Capsule (SRC) Entry Observing campaign ("Hyperseed MAC") aimed to deploy spectrographic, imaging, and infrasound instruments to derive the physical conditions during reentry of the Genesis Sample-Return-Capsule. 1 These data can be used for the evaluation of aerothermal heating and material response models, 2 shock layer radiation models, Thermal Protection System (TPS) performance, accident investigations, and for studies of the delivery of organic compounds for the origin of life by small-asteroid impacts. 3

In this study we investigate the interaction of pyrolysis gas from an ablating material with different, high-temperature gases present in the thermal boundary layer formed over the material in a plasma test facility. We present information on the impact of pyrolysis gas on the heat flux, the thermo-chemistry and the flow pattern at the stagnation point in the near surface region. A parallel investigation of pyrolysis using a simulation probe is also presented. The simulation probe provides a steady CO 2 gas flow into the oncoming plasma flow through a porous graphite plug to mimic the release of gas through the charred layer of an actual ablator. Tests are performed in pure N 2 , air and CO 2 plasma flows. All experiments are conducted in the 30 kW Inductively Coupled Plasma (ICP) Torch Facility at the University of Vermont. Data are presented for varying gas injection velocities and plasma chamber pressures and the results are compared with tests of a phenolicimpregnated carbon ablator (PICA).

This project proposes a centralized algorithm to design cooperative allocation strategies and guidance laws for air defense applications. Scenarios in naval and ground context have been defined for performance analysis by comparison to a benchmark target allocation policy. The cooperative target allocation algorithm is based on the following features: No Escape Zones (differential game NEZ) computation to characterize the defending missile capturability characteristics; In Flight (re) Allocation (IFA algorithm, late committal guidance) capability to deal with target priority management and pop up threats; capability to generate and counter alternative target assumptions based on concurrent beliefs of future target behaviors, i.e. Salvo Enhanced No Escape Zone (SENEZ) algorithm. The target trajectory generation has been performed using goal oriented trajectory extrapolation techniques. The target allocation procedure is based on minimax strategy computation in matrix games.

Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instruction, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188) Washington DC 20503.

Distributed Weighted Engagement Scheme (DWES) that is being incorporated in the Aegis system, has been successfully
tested. The DWES is an algorithm that helps in the coordinated engagement decision making involving multiple
Aegis equipped Destroyers deployed in a theatre. The algorithm decides, based on the geometry of the BMD nodes and the target position at any  given time, on the node that could have the best shot against the incoming warhead.

The article deals with the aerothermal analysis of a sample-return hypersonic capsule reentering on Earth from an interplanetary exploration mission. The main objective of the work is to estimate the heat flux distribution on the capsule surface and to perform one-dimensional thermal analyses for its ablative heat shield. After a short review of sample-return missions, the numerical models implemented are described and the computational results, obtained along a feasible reentry trajectory, are presented and discussed. Particular attention has been paid to compare the convective stagnation point heat fluxes obtained by means of Computational Fluid Dynamic (CFD) analyses with the ones computed with engineering correlations. A further comparison between CFD and with Direct Simulation Monte Carlo (DSMC), in order to investigate the air rarefaction effects, is reported. The article shows an overall satisfactory agreement between engineering correlation and numerical results and also presents a preliminary dimensioning of the capsule ablative heat shield at the stagnation point.

The study and the experimental evaluation of aerospace materials is actually one of the most challenging and money demanding issues in the aerospace science. In particular the development of thermal protections materials (TPM) can be considered as a relevant goal. For this reason in 2010 Italian Air Force tasked (ItAF) Aero Sekur S.p.A. to develop a thermometric facility (Ground Support Equipment -GSE) able to test specimens of thermal protection materials immersed inside an high speed hot gas flux ejected by aircraft turbine. This ItAF facility has been successfully tested with the support of Flight Test Center of ItAF located in Pratica di Mare near Rome. The facility is able to evaluate flux enthalpy by measuring gas speed, stagnation point and free stream temperatures as well as front and back temperatures in the specimen in order to evaluate the evolution of the thermal flux versus the time. The GSE has been firstly designed to test ablative materials, nevertheless it can be used also for testing different thermal protections materials as those used for hot structures (combustion chambers, nozzles, thermo-structural protections for hypersonic flight). The expected main advantages of this experimental method are: the reduction of the costs compared to arc jet and plasma tunnels, to be quick to use, flexible and adaptable to several applications with negligible impact in the test set up configuration. The drawbacks are mainly concerning the representativeness of the environment mainly for what the ablative materials are concerning, even if the enthalpies which can be achieved are sufficient to activate pyrolysis and to start ablation, therefore the method is considered effective whenever a comparison in performance of different materials is needed. The test was concerning specimens of Silicone elastomer ablative material. The max front temperature achieved on the specimens was 1100 °C in a gas flux having speeds up to 270 m/sec (M=0.4). The specimen started the ablation process which extended to about 1 mm of its exposed surface. The GSE could potentially be used also to assess other materials performance used for aircraft support/protections.