Several kinds of test were carried out by using the three-fourth scale model of a Seaplane "PX-S".
In this report pressure distribution data are presented and their differences between two cases of BLC on-and-off also discussed.

抄録全体を表示

The many informations about the performances of the gun tunnel had been obtained theoretically and experimentally by the pilot gun tunnel which was constructed at Kyoto University in 1962. By these data, a large-sized hypersonic gun tunnel at Uji Campus in Kyoto University was new-built on March in 1967.
In this paper, its mechanisms and performances are discussed. The peculiar mechanisms are adopted as follows; i) Double diaphragm type, ii) Automatic operating system, iii) Central control system, etc.
The experimental results of the performances give the followings; i) Mach numbers of 9.515.6, ii) Duration time of 0.070.86 sec, iii) Stagnation temperature of 1, 0001, 300°K and so on.

抄録全体を表示

This paper proposes the method of synthesizing linear flight control systems by applying optimnl control theory associated with quadratic performance index. For this problem, the method of utilizing the root-square-locus technique has been developed by RYNASKI and others. In the present method, instead, the synthesis is done by evaluating quantitatively the performance of the transient responses with the aid of digital and analog computers. The design procedure is illustrated on an attitude-control system for the conventional aircraft and an automatic stabilization equipment for the VTOL aircraft. A comparison is made of the results obtained by classical root-locus method, the root-square-locus method and the present method. Thus, it is shown that the present method yields an excellent control system design.

抄録全体を表示