JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
62047000.pdf6.89 MB
titleOverview of the JAXA Helicopter Research Activity
Author(jpn)齊藤, 茂; 田辺, 安忠; 小曳, 昇
Author(eng)Saito, Shigeru; Tanabe, Yasutada; Kobiki, Noboru
Author Affiliation(jpn)宇宙航空研究開発機構航空本部事業推進部(JAXA); 宇宙航空研究開発機構航空本部機体システム研究グループ(JAXA); 宇宙航空研究開発機構航空本部機体システム研究グループ(JAXA)
Author Affiliation(eng)Program Management and Integration Department, Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA); Aircraft Systems Research Group, Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA); Aircraft Systems Research Group, Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA)
Issue Date2013-10-31
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発資料
JAXA Research and Development Memorandum
Start page1
End page23
Publication date2013-10-31
AbstractIn JAXA, study of the aerodynamic performance/dynamics and aeroacoustics for helicopter has been conducted by two approaches. One is the theoretical approach using the comprehensive code such as the Local Momentum Theory/prescribed wake model and numerical simulation approach such as 3D Euler/Navier Stokes code so far. The other is experimental approach using low speed wind tunnel such as JAXA low speed wind tunnel (5.5m width x 6.5m height test section). In the theoretical approach, the comprehensive code named LMT has applied to investigate several kinds of helicopters such as single, tandem and coaxial type helicopters. Also this is used to investigate the dynamic effect of a helicopter by atmospheric gust and tip vortex generated from a large scale jet airplane. To develop the CFD code, Euler formulation is mainly applied to investigate the flow field around a helicopter rotor, especially to capture the tip vortex generated from blade tip region. In the code, the SLAU scheme was applied to capture the more precise vortex system generated from blade root region, usually the flow speed around a root of a blade is much lower compared with the outer region of blade. The effect of elastic deformation of a blade has also been included in this code to obtain the more precise aerodynamic characteristics. In the experimental approach, the JAXA Multi-purpose Rotor Test Stand (JMRTS) with 2m rotor diameter has been constructed to investigate the aerodynamic/aeroacoustic performance of a helicopter. The active devices such as an active flap have been installed on a rotor blade and tested to evaluate the device performance on the aerodynamics/aeroacoustics. JAXA has conducted several kinds of helicopter research so far. For example, the study of dynamic response of helicopter which penetrates into the tip vortices generated from a large airplane such as Jumbo Jet, the study of performance of wind turbine with elastic blade, the study of the performance of Advanced Turbo Prop with single rotating propeller or counter rotating propeller, the dynamic response of helicopter in auto-rotation flight, the study of aerodynamic performance of tandem rotor in yawed flight and the study of the aerodynamic performance of coaxial rotor. Since 2008, the design of a real-sized low noise helicopter rotor blade with the JAXA developed active flap system has started in order to validate the effect of an active flap system. Within the three years, the conceptual design, the engineering study including analytical dynamic evaluation and the bench tests evaluating static, dynamic and endurance performances have been completed. This paper described the overview of the helicopter research activities in JAXA. It includes the explanation of theoretical analysis code which has been developed for examples, Local Momentum Theory and CFD code and wind tunnel test stand. Various examples of results will be described in this paper.
Description形態: カラー図版あり
Physical characteristics: Original contains color illustrations
KeywordsHelicopter research activity; LMT; BVI noise; CFD; Wind tunnel test stand; Control; Fire-fighting helicopter
Document TypeTechnical Report
JAXA Category研究開発資料
NASA Subject CategoryAircraft Design, Testing and Performance
Report NoJAXA-RM-13-012E

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