Micro-space-probes are ideal platforms for future deep space exploration missions because multiple micro-space-probes can piggyback together on most existing Earth launch vehicles. If the piggyback destination is GTO, the microsatellite can escape from the earth's gravity to go into deep space with only 700 m/s of additional acceleration. Low-concentration (60wt%) hydrogen peroxide has favorable storage characteristics as an oxidizer for in-space hybrid rocket propulsion but has unfavorable ignition and flame holding characteristics due to its high-water content. In this study, separate tests for ignition and flame holding were attempted using 60wt% hydrogen peroxide as an oxidizer and high-density polyethylene as fuel in a CAMUI-type configuration. A Pt catalyst, pressurized chamber, and low flow-rate oxidizer bypass line were used to promote ignition. The results of visualization experiments show that ignition was achieved, but flame holding was not achieved, probably due to an excessive oxidizer flow rate.