@techreport{oai:jaxa.repo.nii.ac.jp:00045151,
 author = {大和, 裕幸 and 内田, 忠夫 and 岡田, 典秋 and 小川, 敏雄 and 多田, 章 and YAMATO, Hiroyuki and UCHIDA, Tadao and OKADA, Noriaki and OGAWA, Toshio and TADA, Akira},
 month = {Dec},
 note = {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},
 title = {操縦系統機能試験におけるリミットサイクル},
 year = {1985}
}