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- 島田 有三
- 日本大学理工学部航空宇宙工学科
書誌事項
- タイトル別名
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- c* Model Reference Adaptive Flight Control Systems
- c モデル キハンガタ テキオウ ヒコウ セイギョケイ
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In this paper, model reference adaptive control systems (MRACS) theory is applied to the design of an aircraft control augmentation system. The most attractive feature of MRACS over other adaptive control systems is that a parameter identification mechanism is not required at all. The problem considered here is to have the aircraft output cp* follow a model (c* model) output cm*, where the model is defined to meet a new handling qualities criterion, namely, c* criterion.<BR>First, an error equation of motion is derived from the model and aircraft equations. Then, the stability of the above error equation system is confirmed by LIAPUNOV'S direct method and the KALMAN-YACUBOVICH Lemma. The block diagram obtained in this manner contains the second order c* model, seven adaptive gains (variable) and three state variable filters which were employed by MONOPOLI to avoid error derivatives. The adaptive gain scheme is somewhat analogous to the well-known P-I type controller used in many classical applications. The adaptive control law employs the proportional plus integral of the product of the error and other signals which are filter outputs, plant output cp*, elevator deflection, etc.<BR>A digital computer simulation was performed at three flight conditions. The result proved that the present system has a great adaptability and that the cp* responses are satisfactory. However, normal acceleration response nz is poor at low airspeed, which fact indicates that c* criterion is not necessarily complete.
収録刊行物
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- 日本航空宇宙学会誌
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日本航空宇宙学会誌 27 (308), 481-489, 1979
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390282679484141312
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- NII論文ID
- 130003958329
- 20001198256
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- NII書誌ID
- AN00189072
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- ISSN
- 24241369
- 00214663
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- NDL書誌ID
- 2064271
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- 本文言語コード
- ja
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- データソース種別
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可