The unitized system of the thrust and electrical power units for the spacecraft operation under the low temperature conditions

2006 Fiscal Year Final Research Report Summary

• Project/Area Number: 15360455
• Research Category: Grant-in-Aid for Scientific Research (B)
• Allocation Type: Single-year Grants
• Section: 一般
• Research Field: Aerospace engineering
• Research Institution: Japan Aerospace Exploration Agency
• Principal Investigator: KAWAGUCHI Junichiro Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Professor (10169691)
• Co-Investigator(Kenkyū-buntansha): TOKUDOME Shinichiro Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Assistant professor (30280556) ; HABU Hiroto Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Assistant professor (60353421)
• Project Period (FY): 2003 – 2006
• Keywords: fuel cell / integrated / propulsion engine / spacecraft

Research Abstract

Through the research for the melting point of the thrusting materials, the 30 weight % content of HA to the fuel revealed to be maximum. The firing condition of the fuel could be optimized. The double layer liquid flow and the condition of the catalyst effects the reactivity of the material under low temperature conditions. Thus, the performance of the thrusting system using the above liquid will have to be tested.
When the applicability of the liquid to the electrical sub-system is considered, low content of carbon is preferable. Furthermore, the safety control of the liquid fuel must be discussed. HA is one of the common material which can be handled as the normal chemical compound. The effect of the contamination of HA to the liquid fuel should be discussed in future.