2026-03-14T03:14:43Z https://jaxa.repo.nii.ac.jp/oai

oai:jaxa.repo.nii.ac.jp:00045133 2023-06-20T19:42:43Z 1887:1893 1896:1898:1913:1917

HMX添加コンポジット推進薬に関する基礎的研究とその実用化 The Fundamental Study of HMX Composite Propellant and its Practical Application. HMX推進薬研究会 HMX Propellant Research Group Synthetic research on HMX composite propellant is described, from the fundamental investigation of propellant burning mechanisms to the demonstration firing test of a full-scale apogee motor. First, the safety and physical properties were examined. By using a new bonding-agent between HMX and HTPB binder for HMX composite propellants, detonability was held in the same manner as the standard propellant without HMX, and some mechanical properties were improved. Second, burning experiments of various HMX/binder strands were made and from these results the mechanism of lowering the burning rate of HMX composite propellants was discussed. Third, firing tests of small-scale rocket motors were conducted under the atmospheric condition for obtaining fundamental combustion characteristics. An example of these characteristics is the absence of combustion instability. Finally, a full-scale (760mm dia.) spherical motor was tested by means of the high altitude test facility. The specific impulse under the vacuum condition was 2.90 KN・s/kg (296kgf・s/kg) at a nozzle expansion ratio of 70. 資料番号: NALTR0875000 レポート番号: NAL TR-875 航空宇宙技術研究所 National Aerospace Laboratory(NAL) 1985-09 jpn technical report https://jaxa.repo.nii.ac.jp/records/45133 0389-4010 航空宇宙技術研究所報告 Technical Report of National Aerospace Laboratory TR-875 875 54 https://jaxa.repo.nii.ac.jp/record/45133/files/naltr00875.pdf application/pdf 4.5 MB 2020-01-29