低騒音STOL実験機「飛鳥」の飛行試験による着陸形態の検討

Material type: 文書・図像類

Author: STOLプロジェクト推進本部飛行試験室ほか

Publisher: 航空宇宙技術研究所

Publication date: 1991-05

Material Format: Digital

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Note (General)：: 「飛鳥」は,進入着陸時に良好な操縦性を有するとのパイロット所見が得られたが,進入着陸時の迎え角及びピッチ姿勢角が高過ぎるために迎角余裕が少ないこと,下方視界の確保が困難であること,主車輪接地後ブレーキ操作開始迄の空走秒時が長いこと,更に,エンジン故障時の復行形態においては,形態移行の秒時が長く復行能...

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Material Type: 文書・図像類
Title: 低騒音STOL実験機「飛鳥」の飛行試験による着陸形態の検討
Author/Editor: STOLプロジェクト推進本部飛行試験室
Flight Test Team STOL Research Aircraft Project Group
Author Heading: STOLプロジェクト推進本部飛行試験室
Flight Test Team STOL Research Aircraft Project Group
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1991-05
Publication Date (W3CDTF): 1991-05
Alternative Title: Evaluation of Landing Configuration by Flight Test of the Quiet STOL Experimental Aircraft ASKA
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1113
No. or year of volume/issue: 1113
Volume: 1113
Pages: 10-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Subject Heading: Flight Test; Powered-Lift; Upper Surface Blowing; STOL; Approach; Landing; Go Around; Alpha Sweep Tests
Target Audience: 一般
Note (General): 「飛鳥」は,進入着陸時に良好な操縦性を有するとのパイロット所見が得られたが,進入着陸時の迎え角及びピッチ姿勢角が高過ぎるために迎角余裕が少ないこと,下方視界の確保が困難であること,主車輪接地後ブレーキ操作開始迄の空走秒時が長いこと,更に,エンジン故障時の復行形態においては,形態移行の秒時が長く復行能力が不足すること,復行中の迎角余裕が著しく少ないこと等の問題点を有することが判明した。これらの問題点を解決し,より有好な着陸及び復行形態を見いだすために,USBフラップ角,外側フラップ角及びBLCの効果を評価するためのαスイープ試験及び進入着陸時の操縦性を評価する着陸試験を実施した。本報告書では,飛行試験による着陸及び復行形態選定の経過及び最終的に決まったSTOL着陸及び復行形態の評価に関して報告する。
During the design phase of National Aerospace Laboratory (NAL) Short Take-Off and Landing (STOL) experimental aircraft, ″ASKA″, the landing configuration was determined to be a 40deg Upper Surface Blowing (USB) flap angle and a 65deg outboard flap angle, whereas the design phase go around configuration was specified as a 20deg USB flap angle, a 65deg outboard flap angle, and leading edge Boundary Layer Control (BLC) off. Based on the results of α sweep tests and landing evaluations, it was determined that the design landing configuration had a small α-margin and high pitch attitude which produced poor downward viewing during approach and landing. The α-margin of the design go around configuration was also respectively small. Subsequently, flight tests were conducted to determine new configurations for landing and go around, and using these test results, a 60deg USB flap angle was selected for the landing configuration and a 30deg USB flap angle was for the go around one. A 65deg outboard flap angle with all BLC on was also decided for both configurations. The process of determining these final configurations using flight tests and evaluuations is discussed.
資料番号: NALTR1113000
レポート番号: NAL TR-1113
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ