日本航空宇宙学会誌

気体流レーザーの研究開発の経緯と現状

増田渉

1985 年 33 巻 380 号 p. 499-508
発行日: 1985/09/05
公開日: 2009/05/25

DOIhttps://doi.org/10.2322/jjsass1969.33.499

ジャーナルフリー

PDF形式でダウンロード (4746K)
迎角を有する軸対称物体まわりの流れ

末松良勝, 相原康彦

1985 年 33 巻 380 号 p. 509-515
発行日: 1985/09/05
公開日: 2009/05/25

DOIhttps://doi.org/10.2322/jjsass1969.33.509

ジャーナルフリー

抄録を表示する抄録を非表示にする

This paper describes the experimental study about the aerodymamic forces acting on the 3dimensional body and the flow pattems in incompressible flow. The experiments were carried out setting a spheroidal body inclined up to 30 degrees in a wind tunnel. At low incidence, the surfacepressure distributions are close to that of potential flow, and ring-like separation line is observed at the rear part of the body, At high incidence, a pair of the longitudinal vortices, which steadily stay on the lee side, come into existence and affect the air loads.

抄録全体を表示

PDF形式でダウンロード (1889K)
極超音速大迎角翼について

保原充, 坪井淳, 福田信彦, 櫻井哲司

1985 年 33 巻 380 号 p. 516-524
発行日: 1985/09/05
公開日: 2009/05/25

DOIhttps://doi.org/10.2322/jjsass1969.33.516

ジャーナルフリー

抄録を表示する抄録を非表示にする

Experiments on hypersonic flow around a caret wing and a winged-vehicle are conducted by the shock tunnel with conical nozzle, and Mach number of 8. Three force components and surface pressures are measured for a wide range of attack angle up to 45°, and compared with Newtonian flow theory, giving good comparisons for the present, near flatbottomed models, except pitching moments. The source flow produced by the conical nozzle affects measured pressures and forces, and some corrections are necessary.

抄録全体を表示

PDF形式でダウンロード (2520K)
多層薄膜熱流束センサの試作とそれによる新しい熱流束測定法に関する研究

林正徳, 桜井晃, 麻生茂

1985 年 33 巻 380 号 p. 525-531
発行日: 1985/09/05
公開日: 2009/05/25

DOIhttps://doi.org/10.2322/jjsass1969.33.525

ジャーナルフリー

抄録を表示する抄録を非表示にする

A new method of measuring heat transfer rate with high spatial resolution and fast response is developed to be used in wind tunnels with long flow duration. For the development of the new method a multi-layered thin film heat transfer gauge is proposed. The principle of the sensor is based on measuring the temperature gradient across a thin, heat resistant layer of SiO with two, thin film resistance thermometers on its upper and lower surfaces. These thin films and the heat resistant layer are deposited by vacuum evaporation technique. The design consideration, the accuracy of the sensor, frequency response, and the calibration technique are discussed. The sensor is applied to the measurement of the heat transfer rate in turbulent boundary layer on a flat plate at Mach number 4, T_w/T₀= 0.64, and Re=1.4×10⁷, and shows high sensitivity and fast response. It also shows excellent durability.

抄録全体を表示

PDF形式でダウンロード (3851K)
パイロットによるシステムバラメータ変化の検知

森住昇, 木村春夫

1985 年 33 巻 380 号 p. 532-539
発行日: 1985/09/05
公開日: 2009/05/25

DOIhttps://doi.org/10.2322/jjsass1969.33.532

ジャーナルフリー

抄録を表示する抄録を非表示にする

This paper deals with the detection characteristics of the human pilot, who is engaged in a compensatory control, to a sudden change in the controlled element's characteristics. Taking the case where the change manifests itself as a variance change of the monitored signal, it is shown that the detection time, defined to be the time elapsed until the pilot detects the change since it takes place, obtained in an experiment is related to the monitored signal and its derivative. Then, the detection behavior is modeled by an optimal controller, an optimal estimator, and a variance-ratio test mechanism that is performed for the monitored signal and its derivative. The result of a digital simulation shows that the pilot's detection behavior can be well represented by the model proposed here.

抄録全体を表示

PDF形式でダウンロード (3318K)
有翼飛翔体最適帰還軌道の一計算法

大屋昭男, 加藤寛一郎

1985 年 33 巻 380 号 p. 540-547
発行日: 1985/09/05
公開日: 2009/05/25

DOIhttps://doi.org/10.2322/jjsass1969.33.540

ジャーナルフリー

抄録を表示する抄録を非表示にする

The optimum glide trajectories of a reentry vehicle are computed as an optimal control problem with inequality constraints on functions of the state and control variables. Inequality constraints are used to simulate the stall, pitch trim and load factor limits. Numerical examples contain the three dimensional turns to maximize the terminal velocity with the terminal location prescribed. Results obtained demonstrate a rational way to reflect various flight limitations on the nominal flight-path determinations.

抄録全体を表示

PDF形式でダウンロード (403K)
燃焼・圧力駆動衝撃風洞と二,三の平板熱伝達実験

岩崎松之助, 橋口真宜

1985 年 33 巻 380 号 p. 548-556
発行日: 1985/09/05
公開日: 2009/05/25

DOIhttps://doi.org/10.2322/jjsass1969.33.548

ジャーナルフリー

抄録を表示する抄録を非表示にする

A combustion and/or pressure-driven shock tunnel with a conical nozzle is constructed. The tailoring Mach number M_ST of the combustion tumel is from 6.7 to 7.4. The heat transfer rate of sharp leading edge flat plates with a backward facing step in hypersonic flow of Mach number M_∞=7.05 and 11.1 are measured by use of the pressure tunnel, and it is shown that the magnitude and the location of the peak heat transfer rate at reattachment region behind the step seem to be affected by the magnitude of M∞. The measured heat transfer rate of a sharp flat plate with angle of attack in M_∞=11.1 hypersonic flow from the conical nozzle of the pressure tunnel is in qualitatively proper agreement with the author's analytical result. The behavior of the heat transfer rate near the sharp leading edge of anat plate in M_∞=11.1·high stagnation temperature T_o=7, 900K flow measured by using the combustion tunnel shows tolerable agreement with the existing measured results at lower T_o in the strong viscous interactlon region.

抄録全体を表示

PDF形式でダウンロード (3597K)
Data Sheet

1985 年 33 巻 380 号 p. 557-560
発行日: 1985/09/05
公開日: 2009/05/25

DOIhttps://doi.org/10.2322/jjsass1969.33.557

ジャーナルフリー

PDF形式でダウンロード (885K)

J-STAGEへの登録はこちら（無料）