著者

阿部 達夫

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.33, no.374, pp.173-181, 1985-03-05 (Released:2009-05-25)

参考文献数

4

---

The experimental study was conducted to determine the effects of the pressure distortion on the operation of a turbofan engine. The turbofan engine was tested with three kinds of inlet distortions, i.e., tip radial, circumferential and combined pressure distortions. The each distortion was generated with screens placed in the inlet ducting upstream of the fan face. Their intensity was varied by the screens with different porosity. This paper presents an investigating result of the evaluation method of the stability for the distortions and the experimental results of the effect on the two characteristics, pressure ratio and efficiency, of two stage axial flow fan and five stage axial flow compressor. The new method is to indicate two distortion indices on the orthogonal coordinate, the circumferential distortion index is related to the radial distortion index. This method led to the estimation that the examination of three kinds of the distortion seems to be enough to cover the total patterns of the distortion encountering inflight. The pressure ratio and the efficiency of a fan with distorted inflow decreased as compared with those of the clean inlet flow, however the operation line and the efficiency of a compressor hardly suffered from influence of the distortion.

著者

村井 正

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.47, no.549, pp.172-178, 1999-10-05 (Released:2019-04-09)

参考文献数

5

著者

安東 茂典

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.532, pp.289-295, 1998-05-05 (Released:2010-12-16)

参考文献数

6

---

This paper is an important supplement of the previous one, titled as “A systematic computation scheme for PAR-WIG cruising design point.” The motive is one point—upper limit of aspect ratio of WIG main wing on which sufficient PAR effect can appear at take-off. Previously this fact was described only qualitatively without any FORTRAN computation, and thus aspect ratio of 6.0 was recommended somewhat arbitrarily. The main purpose of this paper is to clarify this point. Accompanying this, some other requirements on geometry of main wing of WIG are obtained.

著者

津田 雄一

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.68, no.1, pp.7, 2020-01-05 (Released:2020-01-09)

著者

小野田 淳次郎 山西 政雄

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.41, no.474, pp.426-427, 1993-07-05 (Released:2010-12-16)

参考文献数

1

---

In order to avoid the potential risk of damage caused by the hammering during the assembling operation of Marman Clamp, an alternative method to unify the tension in the Marman Clamp bands is proposed. The method is to eliminate the effects of friction, which is the cause of the tension nonuniformity, by slightly sliding the clamp block when the band pre-tension is set. In order to confirm the effectiveness of the method, the Marman Clamp of an upper-stage inter-stage joint of Mu-3SII satellite launcher was assembled with and without the application of the present method, and the stain distribution was measured. The comparison of the data clearly indicated the effectiveness of the proposed method.

著者

今井 功

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.8, no.79, pp.237-240, 1960 (Released:2009-07-09)

著者

久保田 勇希 佐々木 駿 向後 保雄 青木 卓哉 小笠原 俊夫 石田 雄一 山田 哲哉

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.64, no.2, pp.104-112, 2016 (Released:2016-04-05)

参考文献数

29

被引用文献数

3

---

A new lightweight ablator was fabricated by the infiltration of a polyimide resin into a porous carbon material having three-dimensional network and open cell structure. In order to evaluate the performance of the ablator, the thermal response and recession resistance were evaluated using an arc wind tunnel. These properties were discussed from the viewpoint of the cell sizes of porous carbon material. With a decrease in the cell size, internal temperature of the ablator became lower. Microstructural observations revealed that the three-dimensional network structure of the ablator, which originates from the porous carbon preform, was maintained after the heating tests. Consequently, the recession resistance was better than those of existing ablators fabricated from carbon-fiber-based preform.

著者

近藤 恭平

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.51, no.589, pp.32-41, 2003-02-05 (Released:2019-04-15)

参考文献数

16

著者

荻野 三郎 大嶋 壮夫

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.405, pp.460-467, 1987

著者

黒田 健 今度 史昭

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.56, no.653, pp.256-261, 2008 (Released:2008-07-01)

参考文献数

5

---

Optimal aircraft maneuver against two missiles are studied. In this paper, the problem is formulated as a nonlinear optimal control problem and solved by the steepest ascent method. In order to maximize the miss distance against two missiles simultaneously, a special type of criterion function is employed by introducing a window function. Some examples obtained by our method show reasonable aircraft optimal controls, and verify the validity of our method. Our method will be applied to pursuit-evasion and collision avoidance problems with multi-vehicles.

著者

土島 平次郎

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.1, no.1, pp.47-51, 1953-06-30 (Released:2009-07-09)

著者

西田 進

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.22, no.243, pp.200-207, 1974 (Released:2009-05-25)

参考文献数

4

被引用文献数

1 1

著者

島 文雄

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.42, no.487, pp.462-465, 1994-08-05 (Released:2010-12-16)

著者

寺井 勝雄

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.24, no.275, pp.600-606, 1976-12-05 (Released:2009-05-25)

参考文献数

4

著者

辻 猛三

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空學會誌 (ISSN:18835422)

巻号頁・発行日

vol.11, no.107, pp.215-228, 1944-03-05 (Released:2009-07-09)

著者

上野 和之 鷲見 裕太 田坂 昂大 内山 順史

出版者

一般社団法人 日本航空宇宙学会

雑誌

航空宇宙技術 (ISSN:18840477)

巻号頁・発行日

vol.12, pp.25-30, 2013 (Released:2013-02-20)

参考文献数

15

---

Airships with small horizontal cross-section and tall height are proposed. Such vertical airships have a remarkable advantage with respect to available locations for landing and mooring. Flight tests and wind tunnel tests of vertical airships were carried out using scale models. Drag coefficient of vertical airships is discussed.

著者

鷹尾 洋保 磯崎 弘毅 戸田 憲雄

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.38, no.434, pp.111-123, 1990

被引用文献数

1

著者

富樫 史弥 中橋 和博 伊藤 靖 森野 裕行 岩宮 敏幸

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.48, no.556, pp.142-147, 2000-05-05 (Released:2009-07-09)

参考文献数

6

---

The use of overset concept for the unstructured grid method is relatively unexplored. However, the overset approach can extend the applicability of the unstructured grid method for real engineering problems without much efforts in code developments. Multiple moving-body problem is one of those applications. In this paper, the overset unstructured grid method is applied to a flow simulation about an experimental supersonic airplane separation from a rocket booster. Two unstructured grids, each of which covers the airplane and the rocket booster respectively, are used for the simulation. The grid around the rocket booster moves with time in the stationary grid about the airplane. The computed result clearly simulates the shock wave patterns between two bodies. Comparisons with the experimental results show good agreements in the lift and pitching moment coefficients of the airplane and booster during the separation process.

著者

上村 常治 鈴木 真二 柄沢 研治

出版者

一般社団法人 日本航空宇宙学会

雑誌

航空宇宙技術

巻号頁・発行日

vol.12, pp.107-109, 2013

---

The aircraft descent profile has many factors, such as selected airspeed, flight weight, wind, initial altitude, and outside temperature even if fixed idle thrust was assumed. This article tries to prove a rule of thumb that "Even if the wind changes at lower altitude during descent, the flight path will converge at a lower altitude". This may be useful information for flight operation, if it is correct. In addition idle thrust descents are a useful method for fuel economy operation. This paper tries to support this rule of thumb by numerical simulations of flight paths with different wind conditions.

著者

井上 恭一

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.66, no.7, pp.201-204, 2018

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<p>航空自衛隊救難ヘリコプターUH-60Jは,シコルスキー・エアクラフト社製救難専用ヘリコプターHH-60Aの改造機である.本稿では平成2年度から運用が開始されているUH-60Jを母機として,今後の長きに亘る救難任務に対応するために行った装備の近代化について述べる.(平成27年度以降,航空救難団にて運用中)</p>