空気吸込ロケット/ラムジェットを用いた宇宙輸送機の性能計算

Material type: 規格・テクニカルリポート類

Author: 工藤, 賢司ほか

Publisher: 航空宇宙技術研究所

Publication date: 1985-11

Material Format: Digital

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Note (General)：: 出版タイプ： NAPerformance of a composite engine combining air breathing reockets with ramjects was calculated over the flight ranges of Mach 1.2 ～ 7, altit...

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Material Type: 規格・テクニカルリポート類
Title: 空気吸込ロケット/ラムジェットを用いた宇宙輸送機の性能計算
Author/Editor: 工藤, 賢司
升谷, 五郎
鎮西, 信夫
KUDO, Kenji
MASUYA, Goro
CHINZEI, Nobuo
Author Heading: KUDO, Kenji
MASUYA, Goro
CHINZEI, Nobuo
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1985-11
Publication Date (W3CDTF): 1985
Alternative Title: Performance Calculation for a Space Launch Vehicle with Air Breathing Rockets/Ramjets
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-892
No. or year of volume/issue: 892
Volume: 892
Pages: 21-
ISSN (Periodical Title): ISSN : 0389-4010
Target Audience: 一般
Note (General): 出版タイプ： NA
Performance of a composite engine combining air breathing reockets with ramjects was calculated over the flight ranges of Mach 1.2 ～ 7, altitude 0 ～ 43 km. Based on the results of these calculations, the payload mass that could be injected into low earth orbits by a launch vehicle using such air breathing engines as a booster was estimated. The vehicle is unmanned, reusable, vertical-take-off-and-vertical-landing, having rocket engines in the base, and air breathing engines around it. The gross lift off mass of the vehicle is 155 t. The flight trajectory is generated by gravity turn only. For 200 km low earth orbit, the payload mass fraction is about 8.2％ of the gross lift off mass. Effects of various parameters used in the analysis on the payload mass fraction were also shown.
資料番号: NALTR0892000
レポート番号: NAL TR-892
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ