Performance of solid propulsion fuels under simulated deep space exploration conditions

Abstract

Solid-state propulsion technology for deep space exploration has emerged as a research priority. We independently designed and constructed a solid propellant ignition test system to simulate low temperature and low pressure environments (temperature range: −55 ℃ to 20 ℃; pressure range: 0.01 atm to 1 atm). The reaction process was thermodynamically simulated using CEA software. Experimental and simulation results were analyzed through advanced data processing algorithms, including image recognition and thermodynamic modeling. The results of the study show that the ignition delay time t_ig of the solid propellant increases by 1.05 s, the burning rate r decreases by 0.33 mm/s, and the expansion velocity of the flame zone on the surface of solid propellant (burning surface expansion rate) u decreases by 1.22 mm²/s when the temperature decreases from 13 ℃ to −55 ℃. When the pressure was reduced from 1 atm to 0.3 atm, the ignition delay time t_ig increased by 2.74 s, 2.10 s, and the burning rate r decreased by 0.60 mm/s, 0.45 mm/s for 20 ℃ and −40 ℃ temperatures, respectively. Furthermore, ignition failure occurs under sufficiently low pressures, and the critical pressure threshold for ignition failure increases with decreasing ambient temperature. These findings provide valuable guidance for the application of solid propellants in deep space exploration.