Heat Transfer and Chemical Kinetics in the Ignition of Solid Propellants

Roth, Judith; Wachtell, G. P.

doi:10.1021/i160001a011

Cited by 17 publications

(3 citation statements)

References 2 publications

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“…The penetrators (and entire launch package) were fired at a velocity of ∼1.2 km/s using approximately 170 g of type M2 propellant. The approximate composition of the M2 propellant as reported by Roth and Watchtell is shown in Table 1 [ 12 ]. In all 12 tests, the penetrators completely perforated all of the thin mild steel plates and were caught in the thick RHA block.…”

Section: Methodsmentioning

confidence: 99%

Characterization and Cytotoxic Assessment of Ballistic Aerosol Particulates for Tungsten Alloy Penetrators into Steel Target Plates

Machado

Murr

Suro

et al. 2010

IJERPH

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The nature and constituents of ballistic aerosol created by kinetic energy penetrator rods of tungsten heavy alloys (W-Fe-Ni and W-Fe-Co) perforating steel target plates was characterized by scanning and transmission electron microscopy. These aerosol regimes, which can occur in closed, armored military vehicle penetration, are of concern for potential health effects, especially as a consequence of being inhaled. In a controlled volume containing 10 equispaced steel target plates, particulates were systematically collected onto special filters. Filter collections were examined by scanning and transmission electron microscopy (SEM and TEM) which included energy-dispersive (X-ray) spectrometry (EDS). Dark-field TEM identified a significant nanoparticle concentration while EDS in the SEM identified the propensity of mass fraction particulates to consist of Fe and FeO, representing target erosion and formation of an accumulating debris field. Direct exposure of human epithelial cells (A549), a model for lung tissue, to particulates (especially nanoparticulates) collected on individual filters demonstrated induction of rapid and global cell death to the extent that production of inflammatory cytokines was entirely inhibited. These observations along with comparisons of a wide range of other nanoparticulate species exhibiting cell death in A549 culture may suggest severe human toxicity potential for inhaled ballistic aerosol, but the complexity of the aerosol (particulate) mix has not yet allowed any particular chemical composition to be identified.

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Section: Methodsmentioning

confidence: 99%

Characterization and Cytotoxic Assessment of Ballistic Aerosol Particulates for Tungsten Alloy Penetrators into Steel Target Plates

Machado

Murr

Suro

et al. 2010

IJERPH

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“…In lieu of this, the use of equation (12) will be illustrated for the ignition of M2 double base propellant. The experimental surface ignition data of Roth and Wachtell (1962) is used to evaluate the surface ignition time, f,g, as a function of heat flux. It has been shown (Andersen, 1971) that the surface ignition equations (2)-{6) will describe this data using E = 47,850 cal/mole, and ZQ = 1.4 (10") cal/gm sec.…”

Section: Application To Experimental Datamentioning

confidence: 99%

Model of Transient Ignition to Self-Sustained Burning

Andersen¹

1972

Combustion Science and Technology

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A model of ignition that culminates in self-sustained burning is presented. It assumes total ignition time to consist of the time for initiation of the adiabatic surface reaction plus the time to subsequently establish selfsustained (steady) burning. An approximate expression for the non-steady burning time is developed, and theories of the surface reaction time are available. II is demonstrated that under appropriate conditions either or both time terms may contribute to or control the total ignition time. The theory is illustrated for M2 propellant, and it is shown that the effects of pressure and igniter heat flux on the computed characteristics of ignition time and ignition energy are consistent with those obtained by Beyer and Fishman. It is also shown that the developed model agrees in form with the ignition energy expression determined experimentally by Jones, and explains the semi-empirical expression developed by Lewis and von Elbe to describe the minimum ignition energy of gases.

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“…This may have been due to a partial decomposition of the propellant without the formation of flame. 11 is known that the gentle heating by a flameless ignition source can cause nitrocellulose and some nitrocellulose-containing propellants to decompose without the formation of flame in a fizz-type of burning (Churchill et al, 1956;Roth and Wachtell, 1962). The decomposition reaction proceeds in a smoldering-like manner.…”

mentioning

confidence: 99%

Projectile Impact Ignition Characteristics of Propellants II. Single, Double and Triple Base Propellants

Andersen¹,

Irwin²,

Louie³

1979

Combustion Science and Technology

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An investigation of the projectile impact sensitivities of single, double and triple base propellants is described. The tests were conducted by firing different diameter, flat-ended brass projectiles into small cylinders of the propellant at various velocities and observing the impact reaction by appropriate sensors. It is shown that at large projectile diameters the impact velocity threshold for inducing detonation in the propellants is higher than for inducing burning (sustained ignition); whereas at small diameters the induced reaction is only detonation. These results are similar to those obtained earlier on a deflagratable composite explosive. They support the general validity of a previously postulated model, which was based on the view that the ignition and reaction buildup in an impacted propellant are independent processes.

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Heat Transfer and Chemical Kinetics in the Ignition of Solid Propellants

Cited by 17 publications

References 2 publications

Characterization and Cytotoxic Assessment of Ballistic Aerosol Particulates for Tungsten Alloy Penetrators into Steel Target Plates

Characterization and Cytotoxic Assessment of Ballistic Aerosol Particulates for Tungsten Alloy Penetrators into Steel Target Plates

Model of Transient Ignition to Self-Sustained Burning

Projectile Impact Ignition Characteristics of Propellants II. Single, Double and Triple Base Propellants

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