{'fraction_non_alphanumeric': 0.012526096033402923, 'fraction_numerical': 0.0041753653444676405, 'mean_word_length': 5.10828025477707, 'pattern_counts': {'":': 0, '<': 0, '<?xml version=': 0, '>': 0, 'https://': 0, 'lorem ipsum': 0, 'www.': 0, 'xml': 0}, 'pii_count': 0, 'substrings_counts': 0, 'word_list_counts': {'cursed_substrings.json': 0, 'profanity_word_list.json': 0, 'sexual_word_list.json': 0, 'zh_pornsignals.json': 0}}
Testing of a novel propulsion system for micro air vehicles

Abstract The Combustion and Environment Group of the Propulsion and Performance Department at the Defence Evaluation and Research Agency proposed a bipropellant (H2O2 and hydrocarbon fuel) hybrid rocket-turbine engine for micro air vehicle (MAV) propulsion. A prototype bipropellant system was designed, built and tested to assess the full benefits of the rocket part of this type of engine. The operating parameters of the prototype engine were compared with predictions obtained in an earlier feasibility study. A considerable amount of knowledge on the usage and performance of H2O2 has been gained from these experiments. The test results show good agreement with predictions made in the feasibility study. Heat loss from the nozzle and ignition of the fuel are identified to be major problems which must be overcome before the engine can be developed into a viable propulsion system for MAVs.