2026-03-09T09:00:57Z https://jaxa.repo.nii.ac.jp/oai

oai:jaxa.repo.nii.ac.jp:00045151 2023-06-20T21:44:26Z 1887:1893 1896:1898:1913:1917

操縦系統機能試験におけるリミットサイクル An Analysis of the Limit Cycle Observed in the Functional Mockup Test of the NAL QSTOL Research Aircraft 大和, 裕幸 内田, 忠夫 岡田, 典秋 小川, 敏雄 多田, 章 YAMATO, Hiroyuki UCHIDA, Tadao OKADA, Noriaki OGAWA, Toshio TADA, Akira The Quiet STOL research aircraft under development at NAL is equipped with the Stability and Control Augmentation System (abbreviated SCAS). When the SCAS Pitch CWS mode is engaged in flight simulation tests using the control system functional mockup, a small limit cycle is observed. In this paper, the method of describing functions is used to analyze this problem, because nonlinearities in the mechanical linkages and the power actuator play an important role in sustaining the limit cycle. To construct a mathematical model of the control system, nonlinear elements are employed so that the model responses may accord with functional mockup test results including the frequency response. Through both the test and the analysis, it is shown that the present method is an effective tool for analyzing the limit cycle. And it is also clarified that the limit cycle observed is not so annoying to the pilot and is within the limits of the MIL specifications for sustained oscillation. 資料番号: NALTR0893000 レポート番号: NAL TR-893 航空宇宙技術研究所 National Aerospace Laboratory(NAL) 1985-12 jpn technical report https://jaxa.repo.nii.ac.jp/records/45151 0389-4010 航空宇宙技術研究所報告 Technical Report of National Aerospace Laboratory TR-893 893 21 https://jaxa.repo.nii.ac.jp/record/45151/files/naltr00893.pdf application/pdf 8.3 MB 2020-01-29