Burning Rate of Solid Propellant Ingredients, Part 2: Determination of Burning Rate Temperature Sensitivity

Study of the CL-20 flame structure using probing molecular beam mass spectrometry

“…In our case, the reinforcement prevented the accumulation of a carbonaceous residue on the burning surface. At p = 1.0 MPa, the formation of a foamy carcass was not observed and the CL-20 burning rate equal to 4.6 mm/sec coincided with the data of [5,6]. At p = 0.5 and 1.0 MPa, the measurement accuracy of the CL-20 burning rate was ±10%.…”

“…A detailed description of the synthesis of CL-20 and its main characteristics are given in [3,4]. Measurements of the burning rate of CL-20 have been performed [5,6], and the thermal stability and thermal decomposition have been studied [1,[7][8][9][10][11][12][13]. However, in the literature there are no data on the chemical structure of the CL-20 flame and there is only paper devoted to its thermal structure [5].…”

Combustion and thermal decomposition of HNIW and HTPB/HNIW propellants with additives

“…Atwood et al [12][13][14] investigated the combustion of HNIW and the HNIW-based composite propellant. It was concluded that the burning rate of HNIW was ϳ2 times that of HMX under the same conditions.…”

Cast composite solid propellants with different combustion stabilizers

“…This fitting should be with a minimal disturbance of the natural shape of the burning rate curve. Over the small ranges of pressure, a power law fit in equation (1) may be adequate [6].…”

“…The value of temperature sensitivity of the propellant is very important for defining and predicting the ballistic performance and it is expressed as the percent change in burning rate per degree change in the propellant temperature. The first requirement is to obtain a set of burning rate data at various initial temperatures and pressures [6].…”