| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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|
タイトル |
摂動行列誘導系のシミュレーションと評価 |
| 言語 |
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|
言語 |
jpn |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
|
資源タイプ |
technical report |
| その他のタイトル（英） |
|
|
その他のタイトル |
Study of Simulation and Evaluation of Perturbation-matrix Guidance Systems |
| 著者 |
新宮, 博公
大月, 正男
山脇, 功次
森本, 隆
SHINGU, Hirokimi
OTSUKI, Masao
YAMAWAKI, Koji
MORIMOTO, Takashi
|
| 著者所属 |
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航空宇宙技術研究所計測部 |
| 著者所属 |
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航空宇宙技術研究所計測部 |
| 著者所属 |
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|
元・航空宇宙技術研究所計測部 |
| 著者所属 |
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元・航空宇宙技術研究所計測部 |
| 著者所属（英） |
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en |
|
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Instrumentation and Control Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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|
en |
|
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Instrumentation and Control Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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|
en |
|
|
Former Instrumentation and Control Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
|
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Former Instrumentation and Control Division, National Aerospace Laboratory(NAL) |
| 出版者 |
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出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
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出版者 |
National Aerospace Laboratory(NAL) |
| 書誌情報 |
航空宇宙技術研究所報告
en : Technical Report of National Aerospace Laboratory TR-446
巻 446,
p. 44,
発行日 1976-03
|
| 抄録（英） |
|
|
内容記述タイプ |
Other |
|
内容記述 |
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. |
| ISSN |
|
|
収録物識別子タイプ |
ISSN |
|
収録物識別子 |
0389-4010 |
| 資料番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALTR0446000 |
| レポート番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL TR-446 |
naltr00446.pdf (2.7 MB)
