Download or read book MEASUREMENT OF THE BURNING SURFACE TEMPERATURES OF PROPELLANT COMPOSITIONS BY INFRARED EMISSION written by and published by . This book was released on 1962 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of determining the burning surface temperatures of solid propellant compositions by measurement of the infrared emission from the surface is described. Specific wavelengths, at which the solid emission is high and the gas emission is low, were selected for the measurements. Very weak fuel/NH4ClO4 powder mixtures, burning at atmospheric pressure, have a constant surface temperature of 495!15 C irrespective of the burning rate. Practical propellant compositions, containing rather more than stoichiometric proportions of fuel with NH4ClO4, give a similar temperature provided that the hot gas emission can be successfully eliminated, but interference from the gas leads to maximum measured temperatures of about 560 C. The average surface temperature of a double-base propellant increases with burning rate; temperatures range from 300 to 400 C at atmospheric pressure. Binder fuels currently used in composite propellants also have surface temperatures close to 500 C when burning in a diffusion flame with oxygen.

Download or read book Measurement of Double base Solid Propellant Surface Temperatures by Infrared Emission written by Cecil R. Rogers and published by . This book was released on 1969 with total page 372 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book XX Jornadas de Gen tica Luso Espa olas written by and published by . This book was released on 1984 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Measurement of the Temperature of Solid Propellant Surfaces During Ignition Transients by Infrared Radiometry written by Franklin J. Kosdon and published by . This book was released on 1965 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Measurement of Temperature Profiles in Burning Solid Propellant written by Richard C. STRITTMATER and published by . This book was released on 1966 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: A technique is presented for synchronizing a high speed motion picture record of a small thermocouple emerging from a burning surface with the temperature record from the thermocouple. Experimental results are presented which show the burning surface temperature of M13 double base propellant to be 535C at 200 psig. A heat loss analysis is presented which indicates that the thermocouples used in this study, and in fact, all thermocouples used in temperature profile measurement in burning solid propellants have given temperatures much too low. Suggestions are made for measurement technique which would yield more accurate results. (Author).

Download or read book Surface temperature Measurements of Solid Propellants During Ignition written by John A. Keller and published by . This book was released on 1967 with total page 125 pages. Available in PDF, EPUB and Kindle. Book excerpt: Surface temperatures were measured on ammonium perchlorate propellants during ignition by convective heating by use of an infrared radiation sensor. This study was conducted in a shocktube apparatus, and air or nitrogen was used for heating the propellant samples. Heat fluxes were in the range of 30 to 80 cal/sq cm/sec. Surface temperature histories measured on propellant samples with smooth blackened surfaces are in good agreement with predictions of a thermal ignition model that considers the key ignition reaction to be localized at the propellant surface. Surface roughness effects and sample transparency to thermal radiation result in difficulties in relating the infrared detector output to surface temperature. (Author).

Download or read book A Technique to Measure the Irradiance of a Burning Solid Propellant Surface written by Richard F. Felton and published by . This book was released on 1971 with total page 135 pages. Available in PDF, EPUB and Kindle. Book excerpt: A simple, reliable experimental technique has been developed to measure the irradiance of the burning surface of a solid propellant. It incorporates an optical lightpipe to transmit incident radiant energy to a radiation detector. The detector used for the majority of the development tests was a solid state silicon detector with a time constant of less than 500 microseconds. Tests were conducted mainly on metallized, composite and composite modified double base propellants. The metallic additive was aluminum; its percentage by weight varied from 8 percent to 17 percent. The pressure range investigated was 1 to 35 atmospheres with gaseous nitrogen used to pressurize and purge the combustion bomb. Burn rate measurements were made on short propellant samples using electrical timing wires to indicate the time it takes to burn a known length of propellant. (Author).

Download or read book On Propellant Surface Temperatures Derived from Calorimetry written by John A. Vanderhoff and published by . This book was released on 2001 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Propellant surface temperatures for double base (JA2) and nitramine (XM39) propellant samples burning at pressures from 0.8 to 4 MPa have been measured using two different calorimetric techniques. The methods differ in the way combustion is extinguished; one involves depressurization, and the other involves burning into an inert base. For the experiments based on depressurization, a main source of uncertainty was in determining the area of the combusting surface. Moreover, this technique was prone to a large number of unproductive runs. Most of the data presented here was obtained from experiments in which combustion was extinguished by burning into a PolyEtherEtherKetone (PEEK) base. This robust material has thermophysical properties similar to the propellants studied. At higher pressures (and mass regression rates), radiative heating made nonnegligible contributions to total heat input to the inert base. Thus, a multivariate least squares model was developed to describe a time-dependent radiative and conductive heat input, and it was used to fit the experimental temperature histories. Propellant surface temperatures, radiative fluxes, and optical absorption coefficients are obtained from the fit to the data. For the regions of low mass regression rates (

Download or read book A Technique to Measure the Irradiance of a Burning Solid Propellant Surface written by Richard Fieldhouse Felton (CAPT, USAF.) and published by . This book was released on 1970 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Spectroscopic Measurements of the Plume Beneath Counter burning Solid Propellant Flames written by Aren D. Haug and published by . This book was released on 2014 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: A safety analysis of aluminized solid rocket propellant burning at atmospheric pressure is desired. An attempt is made to simulate propellant levitating above a substrate due to the thrust generated by its plume using a motorized support apparatus. This study investigates the temperatures of the plume and burning aluminum droplets with varying substrates, propellant slug diameters, propellant formulations, and gap heights. Two spectrometers were used to collect broadband and narrowband spectral emissions from the plume underneath and immediately adjacent to the propellant-substrate gap. Spectral data were collected as the apparatus passed horizontally through the gap in order to characterize temperatures as a function of flame depth. The broadband spectra were fitted to a linearized Planck's function to estimate gas temperature for several values of emissivity, while the blue-green narrowband spectra were fitted to aluminum monoxide line strength files to calculate the temperature of the burning aluminum. Results indicate the aluminum monoxide flame temperature is generally hotter than the surrounding plume temperature. Calculated temperatures showed a generally flat trend as a function of depth from the center of the plume. Gas temperatures varied wildly and displayed no clear correlation with test variables. Post-test observations indicate that high-temperature chemical reactions within the substrate, phase changes, and the insulating effect of deposited alumina are likely causes for unpredictability.

Download or read book Determination of Combustion Gas Temperatures by Infrared Radiometry in Sooting and Nonsooting Flames written by Valerie J. Lyons and published by . This book was released on 1989 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flame temperatures in nonsooting and sooting environments were successfully measured by radiometry for premixed propane oxygen laminar flames stabilized on a water cooled, porous sintered bronze burner. The measured temperatures in the nonsooting flames were compared with fine wire thermocouple measurements. The results show excellent agreement below 1700 K, and when the thermocouple measurements were corrected for radiation effects, the agreement was good for even higher temperatures. The benefits of radiometry are (1) the flow is not disturbed by an intruding probe, (2) calibration is easily done using a blackbody source, and (3) measurements can be made even with soot present. The theory involved in the radiometry measurements is discussed, as well as the energy balance calculations used to correct the thermocouple temperature measurements. (mjm).

Download or read book The Measurement of the Temperature Profiles of Burning Solid Propellants by Microthermocouples written by Alberto J. Sabadell and published by . This book was released on 1963 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Studies of the temperature profile in the solid pre-heat zone and the gaseous combustion zone of burning solid propellants have been made. These temperature profiles have been obtained by allowing solid propellant strands to burn past very fine, embedded thermocouples. Techniques have been developed for the routine fabrication and handling of micro-thermocouples made from platinum-platinum 10% rhodium Wollaston wire with .0003 inch or finer diameter. Thermocouples with bead sizes no larger than 15 microns are cast into composite propellants or glued into double base propellants. With the propellant strand burning in cigarette fashion, the thermal wave passes over the thermocouple. The voltage vs. time trace thus obtained permits the determination of the temperature distribution in the combustion wave. Analysis of this curve gives a method for determining the surface temperature of the propellant. Temperature time records for composite and double base propellants have been obtained under a variety of conditions. (Author).

Download or read book Heat Flux and Infrared Spectral Measurements of Burning SRM Propellant Preprint written by and published by . This book was released on 2006 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt: On 23 August 2005 the Air Force Research Laboratory (AFRL) Propulsion Directorate at Edwards AFB conducted an open air burn of over 2000 kg of Titan IV solid rocket motor propellant. Multiple remote sensors were deployed to measure the heat flux and spectral emissions during the burn. The heat flux data was utilized to help determine the hazard classification for the propellant. An average normalized irradiance of 1.62 kW/m2 was obtained during a nominal portion of the burn and supports a classification of 1.4. A Fourier Transform Infrared (FTIR) spectrometer collected data over a spectral range of 1.4 - 14 micrometers. Those data show strong gaseous emissions from carbon dioxide, water, and hydrogen chloride as well as a continuum emission component due to the aluminum oxide particulates.

Download or read book On Propellant Surface Temperatures Derived from Calorimetry written by John A. Vanderhoff and published by . This book was released on 2001 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Propellant surface temperatures for double base (JA2) and nitramine (XM39) propellant samples burning at pressures from 0.8 to 4 MPa have been measured using two different calorimetric techniques. The methods differ in the way combustion is extinguished; one involves depressurization, and the other involves burning into an inert base. For the experiments based on depressurization, a main source of uncertainty was in determining the area of the combusting surface. Moreover, this technique was prone to a large number of unproductive runs. Most of the data presented here was obtained from experiments in which combustion was extinguished by burning into a PolyEtherEtherKetone (PEEK) base. This robust material has thermophysical properties similar to the propellants studied. At higher pressures (and mass regression rates), radiative heating made nonnegligible contributions to total heat input to the inert base. Thus, a multivariate least squares model was developed to describe a time-dependent radiative and conductive heat input, and it was used to fit the experimental temperature histories. Propellant surface temperatures, radiative fluxes, and optical absorption coefficients are obtained from the fit to the data. For the regions of low mass regression rates (

Download or read book The Sensitivity of Double Base Propellant Burning Rate to Initial Temperature written by Richard C. Strittmater and published by . This book was released on 1976 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Parr-Crawford, overlapping zone, model of double base propellant combustion, has been programmed for the fizz burning process. Burning rate, surface temperature, and maximum fizz zone temperature are measured at nominal range conditions (1 atm, 293 K) for a given propellant and used in the model to determine the pre-exponential factors in the two Arrhenius reaction rate equations. The values of these two factors are then held constant as initial temperature and pressure are varied. From these solutions, points on the curves of constant initial temperature (To) are plotted on a graph of the log burning rate (r) vs log pressure (p). From these graphs it can be observed from the slope and spacing of the lines whether a burning rate law of the form r = Co exp(oTo)pn can be used to systematize the model solutions; i.e., if the lines are straight and the vertical distance between lines is proportional to the difference in initial temperature, the n and o can be given constant values. In this equation, n is the burning rate exponent and is equal to the slope of the lines. If all the initial temperature dependence is concentrated in the exponential term, then o can be defined as the initial temperature sensitivity of the burning rate. Co then depends only on propellant composition.

Download or read book NBS Special Publication written by and published by . This book was released on 1972 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Burning Surface Temperature Measured with a Thermocouple written by Atsushi Ishihara and published by . This book was released on 2003 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: