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In this article, a eutectic mixture was prepared by mixing 1‐methyl‐3,4,5‐trinitropyrazole (MTNP) and pentaerythritol tetranitrate (PETN) by a new method. The T−X phase diagram and H−X phase diagram were obtained by means of DSC analysis, and then the ratio of the eutectic was obtained. All systems displayed simple eutectic behavior. Energy‐dispersive X‐ray spectroscopy (EDS), X‐ray diffraction (XRD), Fourier transform infrared (IR) spectroscopy, and X‐ray photoelectron spectroscopy (XPS) were performed to characterize the structure of the eutectic. Thermodynamic analysis and TG‐MS tests were carried out to explore the thermal decomposition of the eutectic. Then, the mechanical sensitivity and thermal sensitivity of the raw materials and the eutectic were tested, and the detonation performance was also calculated. The results show that the compatibility of the components of the eutectic is not perfect because of the intermolecular forces between the raw materials. Thermal the decomposition products are mainly H2, H2O, N2, CO, NO, N2O and CO2 and a small amount of CH4. The eutectic has the characteristics of high energy and insensitivity and is expected to replace TNT‐based molten cast explosives.

This investigation was devoted to exploring the application performance of nano‐combustion catalyst CuCr2O4 in solid propellants. In this paper, raw CuCr2O4 and nano‐CuCr2O4 prepared by the mechanical grinding method were applied in solid propellants containing ammonium perchlorate (AP), which are ammonium perchlorate/ hydroxy‐terminated polybutadiene propellant (AP/HTPB) and ammonium perchlorate/composite modified double‐base propellant (AP/CMDB). And the scanning electron microscope, displacement volume method, thermogravimetric analysis, differential scanning calorimetry, and strand burner method were employed to characterize the performance of AP‐based solid propellants. The results show that the AP/HTPB propellant has fewer defects on the surface of it due to the presence of nano‐CuCr2O4, but it has no significant effect on the AP/CMDB propellant. Nano‐CuCr2O4 can also significantly increase the density of AP/HTPB propellant and AP/CMDB propellant to 1.736 g/cm3 and 1.633 g/cm3, respectively. Nano‐CuCr2O4 obviously advances the decomposition temperature of AP/HTPB propellant and AP/CMDB propellant, which also increases the apparent heat of decomposition. In addition, the burning rate of nano‐CuCr2O4‐AP/HTPB propellant and nano‐CuCr2O4‐AP/CMDB propellant increased to 1.60 mm/s and 3.23 mm/s, with an increase of 28.3 % and 26.3 %, respectively. Therefore, nano‐CuCr2O4 is expected to be widely used in solid propellants due to its excellent properties.

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