Influence of Catalysis and Oxidation on Slug Calorimeter Measurements in Arc Jets

Arc jet tests play a critical role in the characterization and certification of thermal protection materials and systems (TPS). The results from these arc jet tests feed directly into computational models of material response and aerothermodynamics to predict the performance of the TPS in flight. Thus the precise knowledge of the plasma environment to which the test material is subjected, is invaluable. As one of the environmental parameters, the heat flux is commonly measured. The measured heat flux is used to determine the plasma enthalpy through analytical or computational models. At NASA Ames Research Center (ARC), slug calorimeters of a geometrically similar body to the test article are routinely used to determine the heat flux. A slug calorimeter is a thermal capacitance-type calorimeter that uses the temperature rise in a thermally insulated slug to determine the heat transfer rate, see Figure 1(left). Current best practices for measuring the heat flux with a slug calorimeter are described in ASTM E457 - 96. Both the calorimeter body and slug are made of Oxygen Free High Conductivity Copper, and are cleaned before each run

Uncertainty Analysis of Coaxial Thermocouple Calorimeters Used in Arc Jets

Recent introduction of Coaxial Thermocouple type calorimeters into the NASA Ames arc jet facilities has inspired an analysis of 2D conduction effects internal to this type of calorimeter. The 1D finite slab inverse analysis (which is typically used to deduce the heat transfer to the calorimeter) relies on the assumption that lateral conduction (i.e., 2D effects) is negligible. Most calorimeter bodies have a spherical nose, which in itself is a violation of the 1D finite slab analysis assumption. Secondly most calorimeters experience a variation in heating across the face of the body which is also a violation of the 1D finite slab analysis assumption. It turns out that these two effects tend to cancel each other to some extent. This paper shows the extent to which error exists in the analysis of the Coaxial Thermocouple type calorimeters, and also offers analysis strategies for reducing the errors

Orbiter Return-To-Flight Entry Aeroheating

The Columbia accident on February 1, 2003 began an unprecedented level of effort within the hypersonic aerothermodynamic community to support the Space Shuttle Program. During the approximately six month time frame of the primary Columbia Accident Investigation Board activity, many technical disciplines were involved in a concerted effort to reconstruct the last moments of the Columbia and her crew, and understand the critical events that led to that loss. Significant contributions to the CAIB activity were made by the hypersonic aerothermodynamic community(REF CAIB) in understanding the re-entry environments that led to the propagation of an ascent foam induced wing leading edge damage to a subsequent breech of the wing spar of Columbia, and the subsequent breakup of the vehicle. A core of the NASA hypersonic aerothermodynamics team that was involved in the CAIB investigation has been combined with the United Space Alliance and Boeing Orbiter engineering team in order to position the Space Shuttle Program with a process to perform in-flight Thermal Protection System damage assessments. This damage assessment process is now part of the baselined plan for Shuttle support, and is a direct out-growth of the Columbia accident and NASAs response. Multiple re-entry aeroheating tools are involved in this damage assessment process, many of which have been developed during the Return To Flight activity. In addition, because these aeroheating tools are part of an overall damage assessment process that also involves the thermal and stress analyses community, in addition to a much broader mission support team, an integrated process for performing the damage assessment activities has been developed by the Space Shuttle Program and the Orbiter engineering community. Several subsets of activity in the Orbiter aeroheating communities support to the Return To Flight effort have been described in previous publications (CFD?, Cavity Heating? Any BLT? Grid Generation?). This work will provide a description of the integrated process utilized to perform Orbiter tile damage assessment, and in particular will seek to provide a description of the integrated aeroheating tools utilized to perform these assessments. Individual aeroheating tools will be described which provide the nominal re-entry heating environment characterization for the Orbiter, the heating environments for tile damage, heating effects due to exposed Thermal Protection System substrates, the application of Computational Fluid Dynamics for the description of tile cavity heating, and boundary layer transition prediction. This paper is meant to provide an overall view of the integrated aeroheating assessment process for tile damage assessment as one of a sequence of papers on the development of the boundary layer transition prediction capability in support of Space Shuttle Return To Flight efforts

Evidence of Standing Waves in Arc Jet Nozzle Flow

No abstract availabl

A Photometric and Spectroscopic Study of Dwarf and Giant Galaxies in the Coma Cluster - IV. The Luminosity Function

A large spectroscopic survey is constructed of galaxies in the Coma cluster. The survey covers a wide area (1 deg$^2$) to deep magnitudes (R ~ 19.5), covering both the core (high density) and outskirts (intermediate to low density) of the cluster. The spectroscopic sample consists of a total of 1191 galaxies, of which, 760 galaxies are confirmed members of the Coma cluster. A statistical technique is developed to correct the spectroscopic sample for incompletness. The corrected sample is then used to construct R-band luminosity function (LF) spanning a range of 7 magnitudes (-23 < M_R < -16) both at the core and outskirts of the cluster. Dependence of the LF on local environment in Coma is explored. The LFs are found to be the same, within the errors, between the inner and outer regions and close to those from recent measurements for field galaxies. The total B-band LF for the Coma cluster, fitted to a Schecter form is also measured and shows a dip at M(B) = -18 mag., in agreement with previous studies. The implications of this feature are discussed. The LF is studied in B-R color intervals and shows a steep faint-end slope for red (B-R > 1.35) galaxies, both at the core and outskirts of the cluster. This population of low luminosity red galaxies has a higher surface density than the blue (B-R < 1.35) star-forming population, dominating the faint-end of the Coma cluster LF. It is found that relative number of high surface brightness galaxies is larger at the cluster core, implying destruction of low surface brightness galaxies in dense core environment.Comment: 42 pages, 11 Figures. Accepted for publication in Ap.

Overview of Heatshield for Extreme Entry Environment Technology (HEEET) Project

The objective of the Heatshield for Extreme Entry Environment Technology (HEEET) projects is to mature a 3-D Woven Thermal Protection System (TPS) to Technical Readiness Level (TRL) 6 to support future NASA missions to destinations such as Venus and Saturn. Destinations that have extreme entry environments with heat fluxes up to 5000 watts per square centimeter and pressures up to 5 atmospheres, entry environments that NASA has not flown since Pioneer-Venus and Galileo. The scope of the project is broad and can be split into roughly four areas, Manufacturing/Integration, Structural Testing and Analysis, Thermal Testing and Analysis and Documentation. Manufactruing/Integration covers from raw materials, piece part fabrication to final integration on a 1-meter base diameter 45-degree sphere cone Engineering Test Unit (ETU). A key aspect of the project was to transfer as much of the manufacturing technology to industry in preparation to support future mission infusion. The forming, infusion and machining approaches were transferred to Fiber Materials Inc. and FMI then fabricated the piece parts from which the ETU was manufactured. The base 3D-woven material consists of a dual layer weave with a high density outer layer to manage recession in the system and a lower density, lower thermal conductivity inner layer to manage the heat load. At the start of the project it was understood that due to weaving limitations the heat shield was going to be manufactured from a series of tiles. And it was recognized that the development of a seam solution that met the structural and thermal requirements of the system was going to be the most challenging aspect of the project. It was also recognized that the seam design would drive the final integration approach and therefore the integration of the ETU was kept in-house within NASA. A final seam concept has been successfully developed and implemented on the ETU and will be discussed. The structural testing and analysis covers from characterization of the different layers of the infused material as functions of weave direction and temperature, to sub-component level testing such as 4-pt bend testing at sub-ambient and elevated temperature. ETU test results are used to validate the structural models developed using the element and sub-component level tests. Given the seam has to perform both structurally and aerothermally during entry a novel 4-pt bend test fixture was developed allowing articles to be tested while the front surface is heated with a laser. These tests are intended to establish the system's structural capability during entry. A broad range of aerothermal tests (arcjet tests) are being performed to develop material response models for predicting the required TPS thickness to meet a mission's needs and to evaluate failure modes. These tests establish the capability of the system and assure robustness of the system during entry. The final aspect of the project is to develop a comprehensive Design and Data Book such that a future mission will have the information necessary to adopt the technology. This presentation will provide an overview and status of the project and describe the status of the tehnology maturation level for the inner and outer planet as well as earth entry sample return missions

The theory of unconventional warfare win, lose, and draw

Clausewitz states that "The defensive form of warfare is intrinsically stronger than the offense" and to defeat 'the stronger form of warfare' "an army's best weapon is superior numbers." Given these two facts, how do special operations forces defeat numerically superior forces fighting in the defense? William H. McRaven's book, Spec Ops, lays out a theory of special operations and six principles that are "applicable across the spectrum of special operations" (McRaven, 1995, p. 3). McRaven's thesis postulates that numerically inferior forces can obtain Relative Superiority for short duration through the use of the six principles of special operations. McRaven's thesis is focused on the direct component of special operations. The theory, arguably, does not cover the full range of special operations; specifically it fails to address the indirect component of special operations, Unconventional Warfare. Given that the defense is the superior form of warfare and numbers count, the question emerges, how can a sponsored insurgent organization or resistance movement defeat the state, which begins with an opening advantage of vastly superior numbers and already in the defense posture? The answer may be found on the flip side of McRaven's Theory of Relative Superiority, or more accurately, the Indirect Theory of Relative Superiority. Indirect Relative Superiority is achieved when a counter state gains and maintains a decisive advantage over a state in an armed political struggle. We hypothesize that numerically inferior forces can obtain Relative Superiority over time through the use of six principles of Indirect Offensive Operations: Security, Networking, Purpose, Indoctrination, Influence, and Agility.http://archive.org/details/theoryofunconven109453858US Army (USA) author.Approved for public release; distribution is unlimited

Cyphenothrin Flea and Tick Squeeze-On for Dogs: Evaluation of Potential Health Risks Based on the Results of Observational Biological Monitoring

<div><p>An observational biomonitoring study was conducted involving adults and children in households that purchased and applied a cyphenothrin-containing spot-on product for dogs as part of their normal pet care practices. The 3- to 6-yr-old children had greater exposure than the adult applicators in the same house, 3.8 and 0.6 μg/kg body weight, respectively. The mean measured values in children were 13-fold lower than those estimated using the U.S. Environmental Protection Agency (EPA) current standard operating procedures (SOP) for pet products (assuming 5% dermal absorption), although the maximum absorbed dosage of one child on one day was equivalent to the default value derived from the SOPs. With regard to potential human health risks, it can be concluded that despite the inherent conservatism in both the exposure and toxicology data, the margins of exposure (MOE) were consistently greater than 100 for average, 95th percentile, and maximum exposures. More specifically, the results of this study demonstrated that the MOE were consistently greater than 1,000 for mean exposures and exceeded 100 for 95th percentile and maximum measured exposures, which clearly indicates a reasonable certainty of no harm when using the cyphenothrin spot-on products. It is also noteworthy that Sergeant’s spot-on products containing cyphenothrin currently sold in the United States have lower weight percentages of active ingredient and lower applied amounts than those used by all but two of the participant households in this study. </p></div