Observation of the boundary layer combustion flame of hybrid rocket

2015 Fiscal Year Final Research Report

• Project/Area Number: 26820369
• Research Category: Grant-in-Aid for Young Scientists (B)
• Allocation Type: Multi-year Fund
• Research Field: Aerospace engineering
• Research Institution: Chiba Institute of Technology (2015); Akita University (2014)
• Principal Investigator: Wada Yutaka 千葉工業大学, 惑星探査研究センター, 上席研究員 (20553374)
• Project Period (FY): 2014-04-01 – 2016-03-31
• Keywords: ハイブリッドロケット / 低融点燃料 / 高燃料後退速度 / 燃焼火炎観察 / 燃焼機構

Outline of Final Research Achievements

Hybrid rocket system is one of the most prospective next-generation space propulsion systems having low cost, high safety ability and green characteristics. High regression rate hybrid rocket fuel have been necessary for the large motor design. Low melting temperature fuel (LT fuel) such as a wax, was focused as high regression rate fuel. Small droplets of the liquefied fuel popping out from the burning surface of LT fuel were observed directly using slab motor at the atmosphere condition. However, the detail mechanism of small droplets generation is not known well. In this study, the double slab motor with observation windows for high pressure experiment was prepared and flame observation was succeeded using this experimental setup. Combustion flame of inert polymer fuel and low melting pint polymer fuels were observed and compared using CMOS camera and high speed camera at the high combustion pressure.

Free Research Field

航空宇宙工学，推進工学，燃焼工学