To address the thermal safety pain points of hydroxylamine perchlorate (HAP)-based liquid propellants in the aerospace engineering scenarios, pure HAP and its aviation kerosene blend (HAP-AK) were taken as the research objects, and a systematic case study was carried out on its thermal safety characteristics and multi-physics hazard evolution law through a multi-scale experimental platform. It was shown that the incorporation of aviation kerosene significantly increased the hazard level of the propellant system. The critical impact energy I 50 and critical friction load L 50 of HAP-AK were reduced by 32.8% and 57.9% respectively compared with pure HAP. The critical temperature of thermal explosion ( T C ) of both systems presented an obvious mass-dependent characteristic, which decreased from 87 °C (10 g sample) to 81 °C (30 g sample). The initial self-heating onset temperature ( T 0 ) and thermal runaway trigger temperature ( T 1 ) of the two systems were basically the same, while the maximum thermal runaway temperature ( T 2 ) of HAP-AK was 36.16 °C higher than that of pure HAP. In addition, both systems showed excellent resistance to electrostatic spark and transient flame ignition, while HAP-AK presented more violent deflagration intensity and higher shock wave overpressure under the same initiation conditions. In this study, the systematic thermal safety parameter database and multi-physics hazard boundary for the HAP-AK system were established, and direct, quantitative data support was provided for the thermal safety design, thermal hazard control and risk management of HAP-based propellant systems in aerospace engineering.
Wang et al. (2026) studied this question.