安定板を有する固体ロケットの操舵要求軽減法

Material type: 文書・図像類

Author: 大石, 晃ほか

Publisher: 航空宇宙技術研究所

Publication date: 1972-02

Material Format: Digital

Capacity, size, etc.: -

NDC: -

View All

Notes on use

Note (General)：: In this paper, are estimated the peak deflection angles and the total injectants required to control an aero-stable solid propellant rocket vehicle (t...

Search by Bookstore

Holdings of Libraries in Japan

This page shows libraries in Japan other than the National Diet Library that hold the material.

List of Cooperating Institutions and Databases

Please contact your local library for information on how to use materials or whether it is possible to request materials from the holding libraries.

other

JAXA Repository
Digital
You can check the holdings of institutions and databases with which 学術機関リポジトリデータベース（IRDB）（機関リポジトリ） is linked at the site of 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）.
JAXA Repository

Search by Bookstore

Bibliographic Record

You can check the details of this material, its authority (keywords that refer to materials on the same subject, author's name, etc.), etc.

Digital

Material Type: 文書・図像類
Title: 安定板を有する固体ロケットの操舵要求軽減法
Author/Editor: 大石, 晃
山中, 龍夫
冠, 昭夫
OOISHI, Akira
YAMANAKA, Tatsuo
KAMMURI, Akio
Author Heading: 大石, 晃
山中, 龍夫
冠, 昭夫
OOISHI, Akira
YAMANAKA, Tatsuo
KAMMURI, Akio
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1972-02
Publication Date (W3CDTF): 1972-02
Alternative Title: An Estimation of Deflection Requirements of An Aero-Stable Solid Propellant Rocket Vehicle
Periodical title: 航空宇宙技術研究所資料 = Technical Memorandum of National Aerospace Laboratory
No. or year of volume/issue: 216
Volume: 216
Pages: 36-
ISSN (Periodical Title): ISSN : 0452-2982
Text Language Code: jpn
Target Audience: 一般
Note (General): In this paper, are estimated the peak deflection angles and the total injectants required to control an aero-stable solid propellant rocket vehicle (the 1st stage) by SITVC (secondary injection thrust vector control) system. It is desirable to minimize those values under the given constraints; to minimize the aerodynamic load on the body, to minimize the flow rate capacity of the injection valves and to minimize the capacity of the injectants feed system. In order to realize the mini-mum deflection angles, the load relief auto-pilot method is used. A non-gravity-turn nominal trajectory is presented to reduce the effects of wind disturbance. The results of the computer simulation are discussed.
資料番号: NALTM0216000
レポート番号: NAL TM-216
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43799&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43799&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