Propellants for variable flow ducted ramjet (VFDR) propulsion

This paper reviews the use of X-ray fluorescence spectrometry (XRFS) for non-destructive studies of valuable metallic objects in the fields of jewelry, archaeology and art, as well as its application in the analysis of coatings and solutions, due to the interest of these issues in jewelry manufacture. The general features of the technique as well as the most outstanding results obtained in the commented fields are described, taking into account the most important sources of error, mainly in the case of samples that have suffered corrosion processes.

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“…49). It can also be used to evaluate the development of the casting technology of the time [50][51][52].…”

Section: Authentication Studiesmentioning

confidence: 99%

X-Ray Fluorescence Analysis of Valuable Metals

Jurado-López¹,

Castro

2006

CAC

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Stochastic Equilibrium Analysis to Optimize Solid Propellant Combustion Gas Composition

Michalski,

Pudsey

2024

Journal of Propulsion and Power

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Solid fuel ducted rockets operate with two-stage combustion. The first stage generates burnt products from the combustion of a fuel-rich solid propellant. In the second stage, those combustion products react with air and are ejected through a nozzle to produce thrust. The combustion efficiency of such a device strongly influences its performance and depends on the composition of the rich-fuel-burnt pyrolysis products. This study investigates the sensitivity of carbon, hydrogen, oxygen, and nitrogen (CHON) solid fuels’ burnt product composition to the fuel properties, composition, and heat of formation. The calculations are performed assuming adiabatic, isobaric chemical equilibrium on synthetic species. Existing species’ properties constrain the properties of the synthetic species. The trends of formation of the main species observed in gas generators, i.e., [Formula: see text], [Formula: see text], CO, [Formula: see text], [Formula: see text], [Formula: see text], and solid carbon, are presented. The sensitivity of the molar concentration ratio [Formula: see text] of [Formula: see text] to [Formula: see text] to the oxygen balance and propulsive properties is compared with an example of gas generator propellants. Recommendations for the possible optimization of fuel composition are formulated. For blends of the existing CHON species reported in the literature, it is shown that improving [Formula: see text] is only possible by degrading the specific impulse.

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