Hypergolic solid fuels and hydrogen peroxide oxidizers have attracted considerable attention for the development of safe hybrid rocket propulsion systems. In this study, a new approach was explored to develop a safe hypergolic hybrid propulsion system using industrial-grade hydrogen peroxide (similar to 70 wt%). Initially, the pro-pulsion performance of different hypergolic solid fuels with an industrial-grade hydrogen peroxide was calcu-lated using the NASA CEA code to find an appropriate propellant combination. The theoretical specific impulse of the hypergolic solid fuel was 27.8 % over hydrazine and 13.4 % over LMP-103S. Based on theoretical investigations, hypergolic solid fuels, named such as HSF-1 to HSF-10, were fabricated using molding and pressing methods. The ignition delay time was measured using the drop-test method. Interestingly, HSF-3 and HSF-4 exhibited very short ignition delay times of 4.92 and 8.75 ms, respectively, with industrial-grade hydrogen peroxide. In addition, the drop test results of hypergolic solid fuel with varying compression pressure in the pressing method confirmed that a pressure above the compressive strength of the binder shortens the ignition delay times deviation. Further, HSF was also ignited even at low concentration of IGHP (>40 wt%); opens the new area of research in combustion science. Overall, low-toxicity hypergolic solid fuels and industrial-grade hydrogen peroxide are promising alternatives to conventional toxic hypergolic propellants.