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| RDX Particle Size on Combustion Performance of a High-Energy Nitramine Propellant |
| Received:February 16, 2022 Revised:March 04, 2022 |
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| DOI：10.7643/issn.1672-9242.2022.03.008 |
| KeyWord:ultrafine RDX high-energy propellant propellant gas generation intensity combustion performance |
| Author | Institution |
| DOU Song-song |
Northwest Institute of Mechanical and Electrical Engineering, Xianyang , China |
| CAO Yong-jie |
Northwest Institute of Mechanical and Electrical Engineering, Xianyang , China |
| ZAHNG Ming-an |
Northwest Institute of Mechanical and Electrical Engineering, Xianyang , China |
| NIE Kui |
Northwest Institute of Mechanical and Electrical Engineering, Xianyang , China |
| ZHANG Wei-wei |
Northwest Institute of Mechanical and Electrical Engineering, Xianyang , China |
| ZHANG Wang |
Northwest Institute of Mechanical and Electrical Engineering, Xianyang , China |
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| Abstract: |
| To study the effect of RDX particle size on the normal, high and low temperature combustion performance of a high energy propellant (NP), a new high-energy nitramine propellant NPH was prepared by adding ultrafine RDX and ordinary RDX, with average particle size (D50) of 6 um and 40 um respectively on the basis of NP propellant formulation. The combustion properties of NP propellant and NPH propellant under normal, high and low temperature conditions were compared and analyzed through a closed bomb test. The results show that when the content of RDX in high-energy nitramine propellant is 10%, both particle size of RDX can reduce the initial gas generation intensity of NP propellant, but ultrafine RDX can effectively reduce the erosive combustion effect of NP propellant. Ordinary RDX reduces the intensity of gas generation and the gradual increase of combustion in the stable combustion section of NP propellant, which leads to the deterioration of propellant combustion performance. Ultrafine RDX reduces the intensity of high temperature gas generation in stable combustion section while increasing it at low temperature, which is beneficial to reduce the temperature coefficient of the propellant charge. Both particle sizes of RDX improve the structural stability of NP propellant and delays the splitting of propellant particles. The combustion split point of NPH propellant is higher than that of NP propellant from 0.77 to 0.83. The influence of temperature change on the combustion decomposition point of propellant is negligible. The research can provide a reference for the formulation design and optimization of high-energy nitramine propellant containing RDX. |
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