2024 年 61 巻 9 号 p. 557-564
Solid propellants are widely used as solid fuels for rockets. Composite propellants are solid propellants that consist of oxidizer powders, binder, burning catalyst, metal fuel, and other additives. Propellants with a high burning rate that generate a large quantity of combustion gases in a short period of time are required to realize high-performance rocket motors. Propellants with a low burning rate generate low thrust, and for example, are used as a gas generator for controlling vehicle flight. Therefore, many studies have been focused on the development of propellants with wide range of burning rates. Ammonium perchlorate (AP) and ammonium nitrate (AN) have commonly been used as a propellant oxidizer. The drawbacks of AN are mitigated by the advantages of AP and vice versa, and therefore, the burning characteristics of AN/AP propellants including both AN and AP as oxidizers have been investigated.
