著者
飯島 朋子 小林 宙 西沢 啓 山崎 宏二
出版者
一般社団法人 日本航空宇宙学会
雑誌
日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日
vol.65, no.7, pp.201-207, 2017-07-05 (Released:2017-07-05)
参考文献数
24

宇宙航空研究開発機構(JAXA)では,独自に開発した航空機用電動推進システム技術を飛行実証するため,FEATHER(Flight demonstration of Electric Aircraft Technology for Harmonized Ecological Revolution)と呼称する研究事業を2012年~2015年にかけて実施した.当研究事業を実施するにあたり,国土交通省航空局から電動航空機の試験飛行許可取得が必須であるが,電動航空機の耐空性基準が存在しなかった.そこで航空局との調整の下,電動推進システムを動力滑空機に搭載するためのJAR(Joint Aviation Requirement)-22のガイドライン・CS(Certification Specification)-22の特別要件と現行の耐空性審査項目から,本件が準拠すべき安全性基準の選定と修正を行い,基準への適合性を保証するための推進システム設計及び試験等による各種証明に取り組んだ.本稿では実証試験機や飛行場の選定も含め,各種システムの適合性証明に至るまでの電動航空機の試験飛行許可取得プロセスについて,ノウハウを国内で共有する観点で概説した.
著者
加藤 寛一郎
出版者
一般社団法人 日本航空宇宙学会
雑誌
日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日
vol.35, no.399, pp.229-236, 1987-04-05 (Released:2010-12-16)
参考文献数
1

Flight path is calculated for the 1971 mid-air collision at Shizukuishi. The calculation is based on the flight-data-recorder records taken from the Government accident report. The crash point thus obtained shows fairly large discrepancy to the wreckage distribution. This paper reports about the contradiction and a new interpretation is given to the flight after the collision.
著者
鈴木 宏二郎 田辺 義慶 山田 和彦 越野 勝一郎 本郷 素行
出版者
一般社団法人 日本航空宇宙学会
雑誌
日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日
vol.48, no.561, pp.549-553, 2000-10-05 (Released:2019-04-11)
参考文献数
8
被引用文献数
1

The supersonic aerodynamic characteristics of lifting bodies with blunt thick delta configuration at high angles of attack are experimentally investigated by using the transonic and supersonic wind tunnels. The results show that the lift-to-drag ratio at the trimmed attack angle can be enhanced by the use of the bent nose and body flaps. Significant temporal nonperiodic fluctuation of the aerodynamic force is observed in the narrow freestream range around the Mach number 1. 5 and attack angle 25 deg. The high speed Schlieren pictures reveal that the intermittent breakdown of the leeward vortex pair causes such unsteadiness. This fluctuation can be abbreviated by the combination of the bent nose and the body flaps located on the upper surface of the body.
著者
堀越 二郎
出版者
一般社団法人 日本航空宇宙学会
雑誌
日本航空学会誌 (ISSN:00214663)
巻号頁・発行日
vol.15, no.158, pp.78-90, 1967-03-05 (Released:2009-07-09)
参考文献数
8

The author conceived that "control force vs. response" should be extended to "control force and displacement vs. response" in order to assure average pilots of safer, easier, and more precise flying of airplanes with wide speed range. Stick displacement per response varies inversely proportional to speed squared, unless dynamic pressure effect is compensated. The author tried to realize this concept by a deliberate reduction of elevator control system stiffness, which would almost ideally shift upward and flatten the curves of stick displacement per response vs. speed over a wide range of speed. Proper pilot-airplane matching is most seriously needed in longitudinal control. The concept and method proposed were verified by flight tests 27 years ago and applied to three models of airplanes, including the Zero Fighter. This paper describes how the afore-mentioned concept and idea were born and proved, and deals with the demonstration of their effects by theoretical analyses and by comparison of the results of numerical calculations with those of the flight tests, and with counterproofs against apprehensions for adverse effects. It is pointed out that the method is applicable to normally designed subsonic airplanes and is especially effective for those operated over wide ranges of speed and normal acceleration. Comparison is made with the results of recent research.
著者
太田 豊彦 福島 幸夫 上條 謙二郎
出版者
一般社団法人 日本航空宇宙学会
雑誌
日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日
vol.46, no.539, pp.705-711, 1998-12-05 (Released:2010-12-16)
参考文献数
4
被引用文献数
2

National Space Development Agency of Japan (NASDA) started to develop H-II launch vehicle in 1983 and succeeded in the 1st flight on February in 1994. Meanwhile, several troubles were experienced in the development of LE-7 which is the 1st stage engine of H-II. The LE-7 is a staged combustion cycle engine with high pressure and high Isp like SSME. Therefore, high delivery pressure and high performance were required for LH2 turbopump, which is the main key component, and caused several troubles in the development. This paper describes the development of LH2 turbopump containing the design description, the contents of some troubles and their counterplans. In addition, some activities to solve turbopump life and endurance will be introduced.