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New Light Weight Ceramic Ablators (LCAs) were produced by using ceramic and carbon fibrous substrates impregnated with silicone and phenolic resins. Special infiltration techniques (patent pending) were developed to control the amount of organic resin in the highly porous fiber matrices, so that the final densities of LCAs range from 0.224 to 0.30 g/cu cm. This paper presents the thermal and ablation performance of the Silicone Impregnated Reusable Ceramic Ablators (SIRCA) in a simulated Mars entry heating environment. Testing was conducted in the Ames 60 MW Interaction Heating Facility (IHF) and 20 MW Aerodynamic Heating Facility (AHF). Test results show that the ablation characteristics of SIRCA are divided into three regimes: non-receding, surface coalescent, and receding. Four different Reusable Surface Insulation (RSI) substrates were used in the production of SIRCA to determine the effect of substrate compositions on the ablation performance. SIRCA with high-purity silica fibers generally performed better at high heating rates. Samples of SIRCA were tested at heating rates ranging from 45 to 550 W/sq cm and at stagnation pressures of 0.02 to 0.47 atm. Several samples were also tested at a heating environment simulating the Mars Aerocapturing mission, which generally consists of a low heating rate and a very high heat load. Material characterizations were also conducted to evaluate the material's mechanical, thermal, and optical properties. The effective thermal conductivity of SIRCA is comparable to that of the RSI substrates, and the emissivity of the charred SIRCA was measured to be about 0.92. Several samples of SIRCA were also exposed to the same heating condition for five cycles, and no additional significant mass loss or recession was observed. (Author) Abstract New Light Weight Ceramic Ablators (LCAs) were produced by using ceramic and carbon fibrous substrates impregnated with silicone and phenolic resins 1 . Special infiltration techniques (patent pending) were developed to control the amount of organic resin in the highly porous fiber matrices, so that the final densities of LCAs range from 0.224 to 0.30 g/cm 3 . This paper presents the thermal and ablation performance of the Silicone Impregnated Reusable Ceramic Ablators (SIRCA) in a simulated entry heating environment for Mars entry. Testing was conducted in the Ames 60 MW Interaction Heating Facility (IHF) and 20 MW Aerodynamic Heating Facility (AHF). Test results show that the ablation characteristics of SIRCA are divided into three regimes -non-receding, surface coalescent, and receding. Four different Reusable Surface Insulation (RSI) substrates were used in the production of SIRCA to determine the effect of substrate compositions on the ablation performance. SIRCA with high purity silica fibers generally performed better at high heating rates. Samples of SIRCA were tested at heating rates ranging from 45 to 550 W/cm 2 and at stagnation pressures of 0.02 to 0.47 atm. Several samples were also tested at a heating environment simulating the Ma...

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Sputum colour and volume cannot be used to predict the presence or absence of M. tuberculosis in sputum detected using Xpert. These sputum quality parameters cannot therefore be used to exclude sputum samples from testing for TB.

An aerocapture trajectory specific to the Mars 2001 mission scenario is presented with results of aerothermal and heatshield thermal protection system (TPS) mass estimates that are required to protect the spacecraft orbiter payload. Specifically, a point design of the Mars aerocapture vehicle was selected and, using an overshoot lifting trajectory, a full 3D aerothermal flowfield was simulated for selected trajectory points. The computational flowfield models were then directly used in a TPS mass sizing algorithm that estimated the overall TPS mass of the aerocapture vehicle forebody and afterbody heatshield and the thickness distributions. This analysis methodology has never been previously attempted for a 3D flowfield in a Mars aerocapture trajectory, and the results presented in this paper represent NASA-Ames' current capabilities to support the complex simulation challenges associated with aerocapture maneuvers at Mars. (Author) AbstractAn aerocapture trajectory specific to the Mars 2001 mission scenario is presented with results of aerothermal and heatshield thermal protection system (TPS) mass estimates that are required to protect the spacecraft orbiter payload. Specifically, a point design of the Mars aerocapture vehicle was selected and using an overshoot, lifting trajectory, a full 3D aerothermal flowfield was simulated for selected trajectory points. The computational flowfield models were then directly used in a TPS mass sizing algorithm that estimated the overall TPS mass of the aerocapture vehicle forebody and afterbody heatshield and the thickness distributions. This analysis methodology has never been previously attempted for a 3D flowfield in a Mars aerocapture trajectory and the results presented in this paper represent NASA Ames' current capabilities to support the complex simulation challenges associated with aerocapture maneuvers at Mars. Nomenclature L/D -lift-to-drag ratio m/C D A -ballistic coefficient, kg/m 2 -entry mass, kg -heating rate (non-ablating), W/cm--heat load (non-ablating), J/cm 2 -freestream Reynolds number, based on vehicle diameter s -distance from stagnation point, m V crd -entry velocity relative to atmosphere, km/s m q Q Re

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