摂動行列誘導系のシミュレーションと評価

Material type: 文書・図像類

Author: 新宮, 博公ほか

Publisher: 航空宇宙技術研究所

Publication date: 1976-03

Material Format: Digital

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Note (General)：: A method of evaluating guidance precision in p-matrix guidance systems is described and an example of calculated values of guidance errors is shown. T...

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Material Type: 文書・図像類
Title: 摂動行列誘導系のシミュレーションと評価
Author/Editor: 新宮, 博公
大月, 正男
山脇, 功次
森本, 隆
SHINGU, Hirokimi
OTSUKI, Masao
YAMAWAKI, Koji
MORIMOTO, Takashi
Author Heading: 新宮, 博公
大月, 正男
山脇, 功次
森本, 隆
SHINGU, Hirokimi
OTSUKI, Masao
YAMAWAKI, Koji
MORIMOTO, Takashi
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1976-03
Publication Date (W3CDTF): 1976-03
Alternative Title: Study of Simulation and Evaluation of Perturbation-matrix Guidance Systems
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-446
No. or year of volume/issue: 446
Volume: 446
Pages: 44-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): A method of evaluating guidance precision in p-matrix guidance systems is described and an example of calculated values of guidance errors is shown. The simulation method necessary for the design of IMU(Inertial Measurement Unit) used for guidance is discussed systematically and the configuration of simulation programme, the model of vehicle mission, the method of determining the various parameters of guidance and control system, and the calculation techniques of the guidance errors are explained. The evaluation is done by using four types of perturbation-matrix guidance systems, which are called α-guidance systems and contain strapdown IMU. The hardware configuration of each system is different. The differences in the performance capability among these guidance systems are compared and investigated quantitatively through digital simulation. This study forms a more explicit conclusion about the following two design concepts through numerical evaluations of the guidance abilities in α-1, 2, 3, 4 guidance systems. One concept is that the required precision of IMU should be determined by comparing the guidance errors due to the deviations of vehicle parameters with those due to the errors of IMU components. The other is that the guidance system should be designed with the freedom to choose a system which closely meets the mission requirements in order to minimize the possibility of over-designing.
資料番号: NALTR0446000
レポート番号: NAL TR-446
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44696&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44696&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