JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
48457000.pdf1.92 MB
title高速飛行実証(フェーズ2)に関する空力関連検討集
Other TitleDevelopment of air data sensor
エアデータセンサーの開発
The collections of studies concerning aerodynamic aspects of high speed flight demonstration phase 2
Author(jpn)上野 真; 廣谷 智成; 重見 仁; 柳原 正明; 若井 洋; 岩田 徹
Author(eng)Ueno, Makoto; Hirotani, Tomonari; Shigemi, Masashi; Yanagihara, Masaaki; Wakai, Hiroshi; Iwata, Toru
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部 風洞技術開発センター; 宇宙航空研究開発機構 総合技術研究本部; 富士重工業; 東京航空計器
Author Affiliation(eng)Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Fuji Heavy Industries Ltd.; Tokyo Aircraft Instrument Co. Ltd.
Issue Date2005-03-31
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication date2005-03-31
Languagejpn
AbstractThe High Speed Flight Demonstration (HSFD) Phase 2 is a flight test program designed to assist in the accumulation of technical expertise for the Japan's re-entry vehicle development. The main objective of the program is to acquire the transonic aerodynamic characteristics of re-entry type vehicles. The flight test vehicle was strung up to an altitude of 19 - 31 km using a stratospheric balloon and made a free flight after release. During the free flight, the aerodynamic characteristics were measured. Although the air data such as Mach number, angle of attack or sideslip angle are vital to analyze the aerodynamic data, it is difficult to acquire accurate air data in the transonic region because of the non-linearity due to the shock wave. In addition, because the flight tests were performed at a very high altitude, the dynamic pressure was very low and that made the air data acquisition more difficult. To achieve those severe requirements, an air data sensor (ADS) based on the principle of non-nulling 5-hole probe, which was originally developed for conventional airplanes, was adopted. Because the original probe could not achieve the requirements due to the severe flight conditions of the HSFD Phase 2, the precision augmentation was made by additional static pressure holes on the stem surface of the probe and succeeded to provide accurate air data. In this document, the development process and the system of the ADS of the HSFD Phase 2 are described.
高速飛行実証フェーズ2は宇宙往還機型機体の遷音速空力特性を取得することを主目的とする飛行実験である。この飛行実験では高高度気球を使用して吊り上げた機体を高度19〜31kmの非常に高い高度から滑空させることによって空力特性の取得を行う。しかし、音速近傍では衝撃波の発生に伴う非線形な空力現象のために高い精度のエアデータを取得することは困難である。さらに、この機体は高高度を飛行するため、地上に較べて極めて低い動圧の環境においても信頼性の高いエアデータを取得することが要求される。そこで、この高い要求に応えるために、汎用の5孔ピトー管方式のADSを基に、静圧孔の追加を行ってマッハ数精度を向上させることにより高高度・遷音速においても必要な精度を維持してエアデータを供給できるエアデータセンサー(ADS)の開発に成功した。本稿ではこのADSの開発過程とシステムについて述べる。
DescriptionJAXA Research and Development Report
宇宙航空研究開発機構研究開発報告
Keywordspitot tube; velocity measurement; aerodynamic characteristic; free flight; shock wave; reentry vehicle; transonic flight; measurement accuracy; numerical analysis; Mach number; elevation angle; sweep angle; static pressure; dynamic pressure; ピトー管; 速度計測; 空力特性; 自由飛行; 衝撃波; 再突入機; 遷音速飛行; 測定精度; 数値解析; マッハ数; 迎角; 横滑り角; 静圧; 動圧
Document TypeTechnical Report
JAXA Category研究開発報告
ISSN1349-1113
SHI-NOAA0048457000
Report NoJAXA-RR-04-043
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/27656


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