Flame-Holding Characteristics of a Hybrid Rocket using Pre-heated 60wt% Hydrogen Peroxide

As the number of micro-deep space probes launched by large rockets using the piggyback increases, the demand for safe, low-cost, re-ignitable, and high-thrust kick motors for efficient inter-orbit satellite transfer is expected to increase as well. Low-concentration hydrogen peroxide is the most suitable oxidizer for hybrid kick motors for micro-spacecraft in terms of safety, low cost, and ease of storage. However, it has difficulty in ignitability and flame holding due to its high water content. In this study, we considered a method to decompose low-concentration hydrogen peroxide by external heating using a heat exchanger before supplying it to a CAMUI-type fuel. A ground combustion experiment showed that flame holding was successfully achieved, however, there were vibrations in the combustion chamber pressure. In order to obtain the lower limit of the heating required for stable combustion, we plan to evaluate the flame holding limit and calculate the heat input to the hydrogen peroxide.