並列タイトル等Hover Control Tests on Flying Test Bed for VTOL Aircraft
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-425
一般注記This paper describes hover control tests on the Flying Test Bed(FTB) which has been developed by the National Aerospace Laboratory to study problems associated with hovering and vertical takeoff and landing operations of VTOL aircraft. The tests were carried out in four steps. The first step was composed of three preliminary tests and five semi-constrained attitude control tests(roll and pitch) by remote controlled step-input. The second step was composed of twelve semi-constrained attitude control tests by two pilots(in two-and three-degree-of-freedom). The third step was composed of four tie-down tests with the crew. The last step was composed of two ground operation tests and five free flight tests by two pilots. The Semi-constrained attitude control tests showed good characteristics of the attitude control system including the automatic stabilization equipment of the FTB. Control stick travel was within 15％ of the half stroke respectively to maintain the neutral attitude. The tie-down tests showed that adverse effects of exhaust gas were not found in undercarriage temperature, surface winds, ground erosion and noxious fumes. Various maximum values in the free flight tests were as follows: height; 2.5m clear, vertical acceleration; 0.02g at climb, -0.03g at descent, 0.185g at touch down, attitude angle; 2.5deg in roll and pitch, yawing velocity; 1.75deg/s, flight time; 3 min 55s(total 12min 40s). The free flight hover control tests showed good control characteristics for force gradients, sensitivities, power, rate damping levels and overall effects on pilot feeling. The FTB remained within a height of ±0.3m and a level of ±0.5m in the 4～8m/s windy condition. It was conjectured that the FTB remained within a sphere of 0.1m in radius under windless condition. The ground effects were negligible for 0.5m height hover, takeoff and landing. The pilots evaluated roll and pitch control characteristics as excellent and the yaw and height control characteristics were comparable to current helicopters. FTB vibration on the ground was most noticeable an engine speed of 11,500 rpm, but it disappeared above this speed. During hover, rolling, pitching and vertical vibrations were noted, and their frequencies were 1.4, 0.8 and 0.2～0.3Hz respectively. The first two were regarded as induced vibration through the pilot as a mechanical element, and the last was regarded as vibration due to pilot control, but the pilot did not feel these vibrations.
資料番号: NALTR0425000
レポート番号: NAL TR-425
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44674&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース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