Burning Characteristics of the HMX/CL‐20/AP/Polyvinyltetrazole Binder/Al Solid Propellants Loaded with Nanometals

Self Cite

This study is devoted to the investigation of the energetic properties of two types of aluminized solid propellants with inert and active binders modified by additives of six different metal nanopowders. The substitution of an inert binder for the active one resulted in significant improvement of energetic properties. However, burning rate regulation become more complicated because the pressure exponent in burning rate law was increased as well. The DSC analysis revealed that the most significant catalytic effects were observed while using Zn, Cu, and Mo powders. Combustion of compositions based on an inert combustible binder and ammonium nitrate was studied in the pressure range 0.1–10.0 MPa. Due to the low combustion rate, no dispersion of burning aluminum particles was observed. During combustion, a single agglomerate of aluminum particles was formed, the mass of which was about 96 % of the initial aluminum mass in the formulation. A comparative analysis of nanosized metal additive effect on the propellant's combustion process was performed. It had been found that the activity of the metal nanopowders depends on the propellant formulation. It had been shown that Al and Zn did not affect the combustion rate of propellant with inert binder but they were effective in compositions with an active binder. Cu and Ni were found to be a good catalyst for the ammonium nitrate and active binder decomposition.

Section: Methodsmentioning

confidence: 99%

“…The scheme and detailed description of the equipment used is given in [29]. The approach for the experimental study of the combustion process was described in [29] as well. A cylindrical propellant sample was placed vertically and glued to a holder.…”

Section: Methodsmentioning

confidence: 99%

Characterization of Aluminum Powders: IV. Effect of Nanometals on the Combustion of Aluminized Ammonium Nitrate‐Based Solid Propellants

Gromov

Popenko

Sergienko

et al. 2021

Self Cite

“…The burning characteristics of the studied formulations were determined in the Vielle bomb. The approach to the experimental study of the combustion process was described in as well. A propellant cylindrical sample was placed vertically and glued to a holder.…”

Section: Methodsmentioning

confidence: 99%

“…The purpose of this article was to define and compare the influence of n‐Me and (n‐MeO+LiF) additives on the regularities of the combustion of the modern aluminized propellant. This work is following the preliminary study on the influence of nano‐metal additives on a modified propellant combustion. Here, the experimental data is given in the context of the comparison of balanced aluminized propellants loaded with μ‐Al, n‐Al, and other n‐Me, n‐MeO, and μ‐MeO.…”

Section: Introductionmentioning

confidence: 92%

Characterization of Aluminum Powders: III. Non‐Isothermal Oxidation and Combustion of Modern Aluminized Solid Propellants with Nanometals and Nanooxides

Gromov

Sergienko

Popenko

et al. 2020

Self Cite

Aluminum powders were comprehensively described as the prospective ingredients of the modern propellants. The paper also studied the influence of micro-and nanopowders of metals (μ-Me and n-Me) and metal oxides (μ-MeO and n-MeO) on the burning process of modern aluminized propellant with HMX, CL-20, AP, and active binder. The following metal additives were used: Al, B, Zn, Ni, Co, and Mo. The effect of the following oxides CoO, V 2 O 5 , MnO 2, and Fe 2 O 3 was studied together with LiF. The combustion tests of modified propellant compositions were carried out in the Vielle bomb in a pressure range 2-10 MPa. n-Me addition resulted in an increase in the burning rate by 10 % for n-B, by 30-40 % for n-Ni and n-Mo in the studied pressure range. The introduction of n-Cu caused a burning rate to increase fivefold. n-Zn additive resulted in increasing of the propellant burning rate by 130 % and 260 % at 4 and 10 MPa, respectively. It was probably caused by the catalytic activity of those metals in the gaseous phase. The effect of complex additive was observed to be insignificant for additives with μ-Co 3 O 4 , μ-V 2 O 5 , μ-Fe 2 O 3 and n-Fe 2 O 3 . The burning rate of propellant with n-CuO additive value was higher by a factor of 4 in comparison with the basic formulation in the studied pressure range.

“…An excellent solid propellant should have a high burning rate and a low‐pressure exponent. Many researchers have tried to improve the performance of propellants by changing the particle size distribution and the oxidant composition and adding the catalysts [8–10]. Among them, the most common and effective way is to add catalysts [11].…”

Section: Introductionmentioning

confidence: 99%

Preparation of Nano‐Spherical Cu‐en and Its Catalytic Study on the Performance of Solid Propellant

Song

Liu

Yang

et al. 2020

This paper mainly describes a nano‐spherical energetic catalyst Cu‐en. The result of particle size distribution shows that the D50 value of Cu‐en is 80.18 nm. The thermal decomposition process of RDX, AP, and NC is improved obviously after mixed with Cu‐en. Among them, the change of AP is the most significant, and its peaks of high‐temperature decomposition and low‐temperature decomposition degenerate into one decomposition peak. The thermal decomposition temperature of NC also decreased from 214.5 °C to 191.6 °C. In the range of 3–9 MPa, Cu‐en can significantly increase the burning rate of HTPB propellant and reduce the pressure exponent n from 0.684 to 0.459. According to the test data results of the CMDB propellant, the nano‐spherical Cu‐en prepared by the spray drying method has a stronger catalytic ability than the micro‐nano Cu‐en prepared by the high‐energy ball milling method.