Investigation of regression rate under high-pressure in axial-injection end-burning hybrid rockets

Yushi Okutani, Yuji Saito, Masaya Kimino, Ayumu Tsuji, Kentaro Soeda, Harunori Nagata

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

This study is an investigation of preeminent fuel regression rate in Axial-injection End-burning hybrid rockets under high pressure conditions. The authors overcame a back firing problem at high pressure conditions by redesigning and optimizing the fuel port diameter. The fuel grain outer diameter was 38 mm and the port diameter was 0.4 mm. Firing tests were conducted using gaseous oxygen as oxidizer at chamber pressures range from 0.98 MPa to 1.44 MPa. The results of four static firing tests show that fuel regression rate increases as the chamber pressure increases, which is consistent with previous research results. Fuel regression rate reached approximately 12.6 mm/s at 1.44 MPa. The authors reformulated the relationship between fuel regression rate and chamber pressure based on the results of high chamber pressure region, and showed that the pressure exponent increased from 1.09 to 1.20.

Original languageEnglish
Title of host publication2018 Joint Propulsion Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105708
DOIs
Publication statusPublished - 2018
Externally publishedYes
Event54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018 - Cincinnati, United States
Duration: 2018 Jul 92018 Jul 11

Publication series

Name2018 Joint Propulsion Conference

Conference

Conference54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018
CountryUnited States
CityCincinnati
Period18/7/918/7/11

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering

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