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Non-ferrous Metals Precision Casting Shape Accuracy in Terms of Ceramic Moulds Anisotropic Material Properties

Biernacki R., Haratym R., Kwapisz J.

Archives of Foundry Engineering

2013

Vol. 13, iss. 1 spec.

5--8

Shape accuracy analysis of aluminum alloy castings was made in function of ceramic mould properties. Taken it to account was anisotropy of those properties, including influence of ceramic mould properties on the porosity of castings. Ceramic moulds strains, which occur in sintering phase, were evaluated with taking into account the design and production process.

Nowa metoda ciągłego pomiaru szybkości palenia stałego paliwa rakietowego za pomocą kamery termowizyjnej

Miszczak M., Panas A. J., Świderski W.

Pomiary Automatyka Kontrola

2009

R. 55, nr 11

950-953

W pracy zaprezentowano możliwości wykorzystania anizotro-powych właściwości grafitu pirolitycznego do pomiaru nową metodą liniowej szybkości palenia stałych paliw rakietowych. Przedstawiono wyniki porównawczych badań doświadczalnych spalania stałego paliwa rakietowego w tulei z grafitu pirolitycznego i miedzi, które zostały potwierdzone modelowaniem numerycznym. Podstawową zaletę proponowanej metody należy upatrywać w stworzeniu możliwości ciągłej obserwacji procesu palenia tego rodzaju materiałów.

In this paper there is presented a new method for continuous burning rate measurement of cylindrical grain of solid, homoge-neous propellant whose main components are nitrocellulose and nitroglycerine. The propellant was initiated to burn from one side (end burning propellant) by a CO2 laser beam. The propellant grain was situated in the tube made from pyrolytic graphite (pyrographite). The rocket propellant burning rate was determined on a basis of recording the burning front/zone movement on the pyrographite tube external surface by an IR camera. The continuous recording of the burning front/zone was possible thanks to application of unique, very high anisotropy of heat conductivity in pyrographite in its crystallographic perpendicular directions i.e. along crystallographic plane - the plane of deposition of hexagonal graphite crystallographic net and along crystallographic axis being vertical to the above plane. The continuous recording of the burning front displacement was also possible due to direct contact of the propellant grain side surface to the internal cylindrical surface of the pyrographite tube possessing higher coefficient of heat transfer along its radius than to longtitudal axis direction. Suitability of pyrographite for measurements of solid rocket propellant burning rate was shown by comparing application of tubes of anisotropic and isotropic properties of heat conductivity, i.e. made from pyro-graphite and copper, respectively. The results of comparative experimental investigations by burning the solid rocket propellant grains inserted in pyrographite and copper tubes were confirmed by the results of numerical modeling. The main advantage of the presented method is possibility of continuous thermal observation of burning process of the above mentioned materials.