ケイゾクテキ ジカン カンケイ ト ジュウゾクセツ ノ アスペクト

従来、時間節の事態と主節の事態が継起的である場合、q 時間節の述語動詞のアスペクト形式が同一でその形式が表すアスペクト的な意味も同じだと考えられる立場と、w「(スル)前」節と「(シタ)後」 節のアスペクト形式がスルかシタかをとり、それぞれ違うアスペクト的な意味を表し、その違いをスルとシタのアスペクト的対立と考える立場がある。本稿では、「(する)まで」節や「(し)てから」節などをも考察し、時間節のスルもシタもシテも同じく完成相形式で、そのアスペクト的な意味の違いを含め、 それぞれの時間節のアスペクトの異なったあり方は後続・先行関係や先行・後続関係などといった時間関係と関連するということを論じる。 具体的には次のような事実を指摘する。(1)後続・先行関係を表す「前(に)」複文と先行・後続関係を表す「後(で)」 複文や「(して)から」複文とで時間節の述語動詞の完成相の表すアスペクト的な意味やその他のアスペクト的な性格が異なっている。(2)「前(に)」節や 「まで」節の述語動詞の完成相が 〈終了限界達成≠ひとまとまり〉 を表す場合、無限界動詞に制限が見られ、「後(で)」節や「(して)から」節の述語動詞の完成相が 〈開始限界達成≠ひとまとまり〉 を表す場合、 多くの動詞に制限が見られる。(3) この種の制限は継起的時間関係が捉えられる他の従属節(「(しない)うち(に)」節や「するのを待つ」の「するのを」節)にも見られる。This present article intends to point out the following facts:(1) In mae (ni) clauses referring to precedence and in ato (de) clauses and (shite) kara clauses referring to subsequence, the meanings of the perfective and other aspectual features of both are different.(2)When the perfective of mae (ni) clauses and made clauses does not refer to the action as a whole, but only to its end point, atelic verbs are restricted in use, and the perfective of ato (de) clauses and (shite) kara clauses does not refer to the action as a whole, but only to its initial phase, and many verbs are restricted in use.(3)Such restrictions can be found in other complex sentences referring to sequential temporal relation

Preliminary Step Towards Wire-Driven Parallel Suspension Systems for Static and Dynamic Derivatives of the Aircraft in Low-Speed Wind Tunnels

The wind tunnel test is one important way to obtain the aerodynamic derivatives of aircrafts. These derivatives are necessary when the guidance and control systems of the aircraft are designed and when the dynamic quality of the aircraft is analyzed as well. The results of experiments of the static derivatives and dynamic derivatives of the aircraft in low-speed wind tunnels have revealed that there are some unavoidable drawbacks such as the interference of the streamline flow brought about by the strut in the traditional strut suspension system. A cable-mounted system is very suitable for experiments of the static derivatives of an aircraft, but it cannot be used in the experiments of dynamic derivatives. In order to use the same wire-driven parallel suspension system to realize the static and dynamic derivates experiments in low-speed wind tunnels, a survey of the research work addressed within the Wire-Driven Parallel Suspension Systems (WDPSS-8) project is presented in this paper. The results show that WDPSS-8 can be successfully used in experiments of static derivatives, and that it has potentiality to be used in experiments of dynamic derivatives. In the issues in the theoretical aspect the issues have been handled. However, much work should be done in the experimental aspects. The research outcomes of WDPSS-8 will help the Chinese set up Chinese brands in the field of wind tunnel tests of aircrafts

A Wire-Driven Parallel Suspension System with 8 Wires (WDPSS-8) for Low-Speed Wind Tunnels

Based on researching into WDPSS-8, after analysing and comparing 3 support systems in wind tunnel including the strut suspension system, cable mounted system and wire-driven parallel suspension system, the following conclusions can be acquired. 1) Till now the strut support systems and rotary balances can be used in measuring the dynamic derivatives of the aircraft in low-speed wind tunnels successfully, wire-driven parallel suspension system has a great potentiality, but it is still under investigation. 2) The cable mounted system is one of suitable method for measuring the static derivatives of the aircraft in LSWT. Though it allows a large supporting stiffness, small interference of the streamline flow and a high measuring precision for large attack angle, it can not be used in measuring the dynamic derivatives. 3) Wire-driven parallel suspension system has opened a new horizon for measuring the static and dynamic derivatives of the aircraft in LSWT. Using the same system based on position control and force control in robotics, it allows to realize the free flight of the aircraft model and to obtain the static and dynamic derivatives. However, the results given in this Chapter can only be considered as a preliminary step in establishing feasibility，although the wire-driven parallel suspension system is a very interesting design, and it may be sufficiently developed into a routine practical system