| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
|
|
タイトル |
汎用飛行シミュレーション・プログラム(FSPK-I) 第1部:プログラムの内容 |
| 言語 |
|
|
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 |
General Purpose Flight Simulation Program(FSKP-I) Part 1:Contents of the Program |
| 著者 |
坂東, 俊夫
渡辺, 顯
BANDO, Toshio
WATANABE, Akira
|
| 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（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) |
| 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-702
巻 702,
p. 50,
発行日 1982-02
|
| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
In developing an aircraft, appropriate flight simulation tests are indispensable during the course of the design. The airworthiness of an aircraft is concerned with such main subjects as flight characteristics, including stall at high angle of attack, failure of engines and automatic flight control systems, encounter with strong atmospheric disturbances as well as the design and performance tests of advanced automatic flight control systems. These are design problems caused by large aircraft motion and strong non-linear aerodynamic characteristics, which could only be made clear by simulation tests. The FSPK-I(Flight Simulation Program of Koh-gi-ken)is a simulation program which simulates acculately the above mentioned large non-linear aircraft motion and is intended as an integrated design tool in the development of an aircraft. We have repeatedly used this program since 1977 in the simulation tests for National Aerospace Laboratory’s Quiet-STOL experimental aircraft to demonstrate it’s effectiveness and have looked as well as to the improvement of it’s accuracy and applicability. The FSPK-I has the following characteristics, advantages and limitations. 1)AS operation is based on the fixed point method, the objective aircraft is limited to a medium subsonic aircraft of moderate motion. 2)In the preceding scope, the program has a high general applicability. 3)In the aerodynamic model of the program, the empenage contributions with its non-linearity are independently calculated. 4)The effect of aircraft motion on engine failure can be accurately evaluated by an engine failure conversion coefficient. 5)The program has an automatic trim capability to start the simulation at any flight point. 6)Independent calculation for control response and gust response etc, are possible by cutting off the cockpit signal. 7)A fixed based cockpit is a prerequiste for the program. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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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: NALTR0702000 |
| レポート番号 |
|
|
内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL TR-702 |
naltr00702.pdf (3.1 MB)
