Hard Start Proglem of the Apogee Engine for the ETS-VI

Material type: 文書・図像類

Author: 佐藤, 政裕ほか

Publisher: 航空宇宙技術研究所

Publication date: 1989-10

Material Format: Digital

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Note (General)：: A pressure-fed, full-blowdown, nitrogen tetroxide/hydrazine (NTO/N2H4) bipropellant apogee propulsion system has been selected for the engineering tes...

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Material Type: 文書・図像類
Title: Hard Start Proglem of the Apogee Engine for the ETS-VI
Author/Editor: 佐藤, 政裕
日下, 和夫
只野, 真
宮島, 博
小林, 秀之
SATO, Masahiro
KUSAKA, Kazuo
TADANO, Makoto
MIYAJIMA, Hiroshi
KOBAYASHI, Hideyuki
Author Heading: 佐藤, 政裕
日下, 和夫
只野, 真
宮島, 博
小林, 秀之
SATO, Masahiro
KUSAKA, Kazuo
TADANO, Makoto
MIYAJIMA, Hiroshi
KOBAYASHI, Hideyuki
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1989-10
Publication Date (W3CDTF): 1989-10
Alternative Title: ETS-VIアポジエンジンのハードスタートについて
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1036
No. or year of volume/issue: 1036
Volume: 1036
Pages: 16-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): A pressure-fed, full-blowdown, nitrogen tetroxide/hydrazine (NTO/N2H4) bipropellant apogee propulsion system has been selected for the engineering test satellite VI (ETS-VI) which will be launched by the H-II rocket. This report describes a hard start problem encountered during high altitude simulation tests of the engine, as well as a possible solution to the problem. The bipropellant valve had been designed for fuel-lead start. Regarding this problem, a survey was made of previous test data of the apogee engine. It became apparent that hard starts were observed only in altitude simulation tests, never in seal-level tests. Although a survey of the literature did not provide any conclusive results, we considered that an oxidizer-lead injection design might provide a possible solution to the problm. The proof-of concept experiments showed that the hard start in a vacuum environment was sufficiently suppressed by employing a 50-100 ms oxidizer-lead. Based on this test verification, modification of the bipropellant valve design has been implemented.
資料番号: NALTR1036000
レポート番号: NAL TR-1036
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45295&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45295&item_no=1&attribute_id=31&file_no=1
Access Restrictions: 限定公開
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