Abstract
Through the analysis and calculation to the flow field in the solid rocket motor using high‐burning‐rate propellant, the authors believe that the existence of pressure difference between the inside and outside of the propellant tube causes the propellant crack. In this paper, the design method to eliminate the pressure difference is discussed. The theoretical results were certified by the experimental results.
| Original language | English |
|---|---|
| Pages (from-to) | 11-15 |
| Number of pages | 5 |
| Journal | Propellants, Explosives, Pyrotechnics |
| Volume | 20 |
| Issue number | 1 |
| DOIs | |
| Publication status | Published - Feb 1995 |
| Externally published | Yes |
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Wang, D. A., Wang, N. F., & Qin, G. M. (1995). Research on the Crack Mechanism of High‐Burning‐Rate Propellant in the solid rocket motor. Propellants, Explosives, Pyrotechnics, 20(1), 11-15. https://doi.org/10.1002/prep.19950200104