著者

香山 寛人 汪 運鵬 小澤 啓伺 土井 克則 中村 佳朗

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 = Journal of the Japan Society for Aeronautical and Space Sciences (ISSN:13446460)

巻号頁・発行日

vol.60, no.2, pp.74-79, 2012-04-05

参考文献数

12

被引用文献数

1

---

The space transportation system will need advanced abort systems to secure crew against serious accidents. Here this study deals with the capsule-type space transportation systems with a Launch Abort System (LAS). This system is composed of a conic capsule as a Launch Abort Vehicle (LAV) and a cylindrical rocket as a Service Module (SM), and the capsule is moved away from the rocket by supersonic aerodynamic interactions in an emergency. We propose a method to improve the performance of the LAV by installing fences at the edges of surfaces on the rocket and capsule sides. Their effects were investigated by experimental measurements and numerical simulations. Experimental results show that the fences on the rocket and capsule surfaces increase the aerodynamic thrust force on the capsule by 70% in a certain clearance between the capsule and rocket. Computational results show the detailed flow fields where the centripetal flow near the surface on the rocket side is induced by the fence on the rocket side and the centrifugal flow near the surface on the capsule side is blocked by the fence on the capsule side. These results can confirm favorable effects of the fences on the performance of the LAS.

著者

安東 茂典 加藤 三千代

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.39, no.455, pp.675-679, 1991-12-05 (Released:2010-12-16)

参考文献数

4

---

A quick automatic method is presented for computing performance of nonducted propeller with constant revolutional speed. This study is motivated by usefulness for developing WIG vehicles, namely in order to predict propeller data to be used. Results of computation examples show that constant-speed-propellers are considerably robust, viz. insensitive to change of some parameters such as diameter, solidity and rotational speed. It is noteworthy that these well-known properties are confirmed easily and quickly by the present method.

著者

稲谷 芳文 石井 信明 山田 哲哉 平木 講儒

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.53, no.619, pp.248-255, 2005-08-05 (Released:2019-04-17)

参考文献数

22

被引用文献数

1

著者

村尾 麟一 竹内 貞男 稲葉 稔

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.39, no.448, pp.242-250, 1991-05-05 (Released:2010-12-16)

参考文献数

5

被引用文献数

1

著者

中村 治光

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.7, no.61, pp.49-50, 1959

著者

田中 稟三

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.9, no.86, pp.85-91, 1961

著者

石澤 和彦

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.59, no.693, pp.297-303, 2011

参考文献数

8

著者

武田 真司 小出 紗英 大本 圭祐 坂本 啓 田中 宏明 石村 康生 大熊 政明

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.19, pp.151-158, 2020 (Released:2020-10-29)

参考文献数

10

---

For the observation of microwave in space over 100 GHz by radio astronomical satellites, this study develops shape-deformable antenna reflectors. When a certain portion of the antenna reflector prototype is deformed, the entire reflector is affected by the partial deformation. The purpose of this study is firstly clarifying the effect of coupling in reflector displacement. Secondly, this study tries the performance evaluation of hysteresis elimination by a piezoelectric strain feedback system under the effect of the displacement coupling. To achieve these objectives, this study quantifies the displacement coupling, the relations between piezoelectric strain and reflector displacement, and the residual reflector displacement error under the feedback control when multiple actuators are driven simultaneously. As a result, this study clarifies that there is a non-negligible coupling effect and the stress history dependence in the reflector surface deformation, causing the limit in the accuracy of the feedback system. Based on these experimental observations, this paper presents three design improvement plans that will possibly solve these problems.

著者

山名 正夫 伊藤 光

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.23, no.255, pp.251-257, 1975-04-05 (Released:2009-05-25)

参考文献数

2

---

The generation of a kind of circulatory flow in the separated-flow region of a stalled sweptback wing was noticed. Observation on the circulatory flow was made for a model airplane by using evaported-gas-oil smoke. The presence of a strong lateral outward flow was observed in the considerable range behind the trailing edge of wing-root portions. The effect of the angle of sweep back and taper ratio of a wing on the intensity and direction of the circulatory flow were also investigated.

著者

榊 和樹 角銅 洋実 中谷 辰爾 津江 光洋 五十地 輝 鈴木 恭兵 牧野 一憲 平岩 徹夫

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.63, no.6, pp.271-278, 2015

---

The pintle injector is one of the most promising candidate for propellant injection systems of liquid rocket engine combustors due to the throttling capability and simple structure. However, combustion characteristics of pintle injectors are still unclear. Therefore, combustion experiments are conducted for an ethanol/liquid oxygen rocket engine combustor with a planar pintle injector which simulates the injection configuration of a pintle injector and enables optical measurements at <I>Pc</I>=0.40MPa and O/F=1.08-1.56. Direct images of the flame structure and CH chemiluminesence are observed through an optical window using high speed imaging techniques. Backlit images of the spray structure are observed. Strong CH chemiluminescence is observed in the vicinity of the impinging point of the two propellants. Luminous flames are observed in the vicinity of the faceplate and the upper wall of the combustor. It is observed that atomization process of the planar pintle injector proceeds two-dimensionally unlike conventional impinging injectors. A periodic atomization behavior is observed with the frequency of approximately 700Hz, being equal to the frequency of the Kelvin-Helmholtz instability.

著者

李家 賢一

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.59, no.695, pp.403-406, 2011-12-05 (Released:2017-09-22)

参考文献数

2

著者

小幡 茂男

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.19, pp.71-80, 2020 (Released:2020-03-14)

参考文献数

57

---

SHSI, Supersonic Hot Streak Ignition, as a new concept of ignition system for supersonic combustion of hydrocarbon fuel in SCRAM jet engine installed on the small size hypersonic vehicle has been proposed. SHSI fuel of slight amount of hydrogen supplied into compressible turbulent boundary layer at forebody of the vehicle fuselage starts exothermic chemical reaction induced by high temperature at viscous sublayer, then during passing through intake and isolator the cold streak of pilot fuel is transformed to the hot streak as heat source for ignition and flame-holding at main combustor. Analytical research have been conducted to examine the potential for practical operation of SHSI. Damkohler number defined by the ratio between characteristic times of chemical reaction and flow is used to assess the possibility of forming of the hot streak, and it is found that the flight condition of Mach number around 5 at the relatively low altitude in the stratosphere is the limit to achieve auto-ignition of the anterior fuel. Also, compound compressible flow analysis based on one-dimensional stream-tube theory is applied to the validation of capability to avoid the fatal risk of engine unstart at the convergent part of intake, and it is confirmed that the biased distribution towards the downstream of heat release by the hot streak is effective to successfully suppress occurrence of the danger compound choking.

著者

守屋 富次郎 河村 竜馬 木村 秀政 久保 富夫 北野 純 菊原 静男 渋谷 厳 萱場 嘉郎 箕田 芳郎 疋田 遼太郎

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.5, no.39, pp.100-114, 1957

著者

河邉 博康

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.54, no.629, pp.250-256, 2006 (Released:2006-07-20)

参考文献数

18

---

The wings formation flight is studied by means of theoretical aerodynamics. Each wing is modeled using the horseshoe vortex. In formation flight each wing flies in an upwash field generated by all other wings of the formation, and consequently its flight power decreases. In V formation flight the wing in a central position has a smaller local flight power reduction, while in U formation flight the local flight power reduction of each wing remains equal. In the case of a long range flight, the optimum shape is not V formation, but U formation flight. It has turned out that the value of a local flight power reduction in V formation flight is equal to that in U formation flight when the leader wing of V formation shifts to the position of a follower wing.

著者

中村 治光

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.7, no.61, pp.49-50, 1959-02-28 (Released:2009-07-09)

著者

石澤 和彦

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.59, no.693, pp.297-303, 2011-10-05 (Released:2017-09-22)

参考文献数

8

著者

木村 秀政 内藤 晃

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.32, no.360, pp.15-22, 1984

著者

古川 徹 簑原 和彦 中村 則之 真杉 京一 松島 雄一郎

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.68, no.1, pp.6, 2020-01-05 (Released:2020-01-09)

著者

三宅 司朗

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.57, no.665, pp.161-169, 2009

著者

矢口 裕之 三堀 健 本橋 多喜男

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.23, no.260, pp.492-505, 1975-09-05 (Released:2009-05-25)

参考文献数

7